A method for detecting and reducing edgewise vibrations in a rotor blade of a wind turbine includes, for a given wind speed, determining a frequency or frequency band at which edgewise vibrations are producible in the rotor blade. The method determines an electrical characteristic of the pitch actuator that correlates to an increased torque required to hold a pitch angle of the rotor blade constant at the frequency or frequency band. During an operational power-production mode of the wind turbine, the electrical characteristic of the pitch actuator is monitored. Upon the electrical characteristic reaching a predefined limit value indicative of edgewise vibrations in the rotor blade, corrective action is initiated by the wind turbine controller to reduce or prevent the edgewise vibrations.
A method for damping oscillations in a tower of a wind turbine includes determining a primary rotational frequency of the rotor (fp) that correlates to a tower resonance frequency (fr). The method defines an exclusion zone between a first rotational frequency of the rotor (fl) that is less than the primary rotational frequency (fp) and a second rotational frequency of the rotor (f2) that is greater than the primary rotational frequency (fp). At rotor frequencies below the exclusion zone, a first tower-damping force strategy is applied. At rotor frequencies above the exclusion zone, a second tower-damping force strategy is applied that is different from the first tower-damping force strategy.
3.
COMPOSITE COMPONENTS AND METHODS OF DENSIFYING COMPOSITE COMPONENTS
Composite components and methods of densifying composite components are provided. For example, a composite component includes a first ply having a first plurality of unidirectional arrays of fiber tows extending in a first direction and a second ply having a second plurality of unidirectional arrays of fiber tows extending in a second direction. A first fluid pathway is defined in the first ply that has a first length greater than a first width, and a second fluid pathway is defined in the second ply that has a second length greater than a second width. The first and second fluid pathways may improve densification of the composite component by improving penetration of a densification fluid in the composite component.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
C08J 5/06 - Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
B32B 3/10 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
4.
INSULATED EARTHING SWITCH FOR AN AIR INSULATED OR MIXED SWITCHGEAR
The invention concerns an air insulated or mixed air and gas insulated switchgear assembly (1) comprising a switchgear (2) and an earthing switch (10). The switchgear (2) comprises a switchgear housing (3). The earthing switch (10) comprises a switch housing (13). According to the invention, the earthing switch (10) comprises an insulator flange (16) comprising a metallic body and a dielectric insulating layer on the metallic body. The switch housing (13) is mechanically connected to the switchgear housing (3) through the insulator flange (16).
H01H 33/78 - Switches with separate means for directing, obtaining, or increasing flow of arc-extinguishing fluid wherein arc-extinguishing gas is evolved from stationary parts; Selection of material therefor wherein the break is in gas
An apparatus comprises a tool having a first portion and a second portion that are separated by at least a first area of articulation. A first inertial measurement unit is affixed with respect to that first portion and a second inertial measurement unit is affixed with respect to that second portion. A control circuit operably couples to those inertial measurement units and receives corresponding information regarding those portions of the tool. The control circuit can then process that received information to generate positional proprioception information as regards those monitored tool portions. By one approach, the control circuit generates that positional proprioception information by first determining an absolute orientation of each of the tool portions independent of one another and then calculating a differential pose as a function of the determined absolute orientation of those tool portions.
A robotic arm is inserted into a passage of a part to be examined. Operator instructions defining a tip motion for a tip of the robotic arm, sensor readings, and an environmental map are received. The operator instructions, the environmental map and sensor readings are applied to a previously trained machine learning model to produce control signals. The control signals to an actuator on the arm to control a movement of the robotic arm allowing the robotic arm to automatically gain traction in the passage and automatically move according to the movement.
Systems and methods are provided herein useful to analyzing weld quality. In some embodiments, the systems and methods identify or predict weld characteristics such as surface discontinuities and/or subsurface discontinuities based on surface topology data and/or welding process parameters. The systems and methods described herein leverage machine learning algorithms to identify relationships between historic weld characteristics and historic pre-weld surface topology, historic post-weld surface topology, and/or historic welding process parameters. Thus, the systems and methods described herein may identify weld characteristics for a weld based on the relationships and the pre-weld surface topology, post- weld surface topology, and/or welding process parameters for the weld. Further, the systems and methods described herein may also identify weld as conforming or not confonning to one or more weld standards based on the relationships and the pre-weld surface topology, post- weld surface topology, and/or welding process parameters for the weld.
B23K 31/12 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups relating to investigating the properties, e.g. the weldability, of materials
8.
BOND COAT INCLUDING METAL OXIDES AND OXYGEN GETTERS
Coated components and their methods of formation are provided. The coated component includes: a ceramic matrix composite substrate comprising silicon carbide and having a surface; a bond coat on the surface of the substrate; and an environmental barrier coating on the bond coat. The bond coat includes a plurality of discrete particles dispersed within a matrix phase that includes mullite. The plurality of discrete particles includes an oxygen getter and a transition metal oxide.
A coated component (100), along with methods of its fon-nation, are provided. The coated component (100) may include a ceramic matrix composite substrate (102) comprising silicon carbide and having a surface (103), a bondcoat (104) on the surface (103) of the substrate (102), and an environmental barrier coating (108) on the bondcoat (104). The bondcoat (104) includes a plurality of discrete particles (110) dispersed within a matrix phase (112), with the matrix phase (112) formed from mullite and defining 60% to 98% by volume of the bondcoat (104). The plurality of discrete particles (110) include an oxygen getter and has 50% of its volume or greater formed from particles having an average size of 10 [tm to 100 i.tm.
A system and method are provided for reducing vibrations and loads in one or more rotor blades of a wind turbine when the rotor hub is locked against rotation, The method detects that the rotor blades are vibrating above a threshold limit, and determines one or more wind parameters for wind impacting the rotor blades. An initial orientation of the blades is also determined. Based on the wind parameters and initial blade orientation, a first angle of attack for the rotor blades is determined that will reduce the vibrations in the rotor blades. The method then determines if expected loads induced at one or more wind turbine components will exceed a threshold limit at the first angle of attack for the rotor blades. The first angle of attack is modified when the expected loads exceed the threshold limit to reduce the expected loads to below the threshold limit. A controller pitches the rotor blades to achieve the first angle of attack.
A proactive method prevents vibrations in one or more rotor blades of a wind turbine when the wind turbine is in a standstill idling state with a rotor hub free to rotate. The method determines a minimum revolution rate of the rotor blades that prevents vibrations of the rotor blades and that the actual revolution rate of the rotor blades is below the minimum revolution rate. A wind parameter is detected and determined to be above a threshold limit. The method also detects if grid power is available for pitching the rotor blades. Based on the wind parameter, a controller determines a pitch angle for one or more of the rotor blades to increase rotation of the blades to at least the minimum revolution rate. The controller initiates pitching the rotor blades to increase the revolution rate of the rotor blades prior to vibrations being induced in the rotor blades.
An coated component is provided. The coated component includes a component substrate and bond coat layer comprising silicon deposited on the component substrate. A composite layer is deposited on the bond coat layer. The composite layer includes a rare earth disilicate and a second phase material. The composite layer has a thickness (T) from about 0.05 mm to about 2.25 mm, and a coefficient of thermal expansion that is different by a value of about 0 to about 2.25 from a coefficient of thermal expansion of the component substrate upon which the bond coat layer is deposited. Coated gas turbine engine components are also provided.
B28B 19/00 - Machines or methods for applying the material to surfaces to form a permanent layer thereon
C04B 35/50 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare earth compounds
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
A first nest structure and a second nest structure are brought into alignment. When the alignment of the first nest structure and second nest structure is obtained, the operation of at least one vacuum pump is controlled such that a bearing element is released from the first nest structure and secured in the second nest structure. Movement of the bearing element from the first nest structure to the second nest structure occurs without slippage resulting in preservation of a common frame of reference used when the bearing element is in the first nest structure and the second nest structure.
A method and system of additively-manufacturing a structure having a reinforced access opening includes printing, via an additive printing device having at least one printer head, a portion of the structure adjacent to a support surface. The portion of the structure is printed of a cementitious material, and the printed portion of the structure defines an access opening for the structure. Moreover, the method includes providing a void of the cementitious material at a top boundary of the access opening, placing one or more reinforcement members in the void such that the one or more reinforcement members extend across the void, and continuing to print the printed portion of the structure around the void to build up the structure. Thus, the method also includes backfilling the void with a backfill material to incorporate the one or more reinforcement members within the void into the printed portion of the structure.
A method for controlling an inverter-based resource (IBR) connected to an electrical grid includes receiving grid parameter(s) and applying a droop function to the grid parameter(s) to determine a power droop signal. Further, the method includes receiving a power reference signal. Moreover, the method includes determining a power command signal as a function of the power droop signal and the power reference signal to allow for a fast response in a power output of the IBR to the grid parameter(s). The method also includes applying power constraint(s) to the power command signal to limit how much the power output of the IBR can be changed due to the grid parameter(s). Further, the method includes determining one or more control commands for the IBR based, at least in part, on the power command signal. Thus, the method includes controlling the IBR based, at least in part, on the power command signal.
H02J 3/38 - Arrangements for parallelly feeding a single network by two or more generators, converters or transformers
H02J 3/12 - Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
H02M 1/00 - APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF - Details of apparatus for conversion
H02M 7/44 - Conversion of dc power input into ac power output without possibility of reversal by static converters
16.
SYSTEM AND METHOD FOR POWER CONTROL OF AN INVERTER-BASED RESOURCE WITH A GRID-FORMING CONVERTER
A method for controlling an inverter-based resource (IBR) having a power converter connected to an electrical grid includes receiving a first power limit signal for the IBR from an external controller, receiving a second power limit signal for the IBR, and determining a constrained power limit signal based on the first and second power limit signals. The method also includes applying a first frequency droop function to the constrained power limit signal and determining at least one of a power reference signal or a pitch reference signal for the IBR as a function of an output of the first frequency droop function and the constrained power limit signal. Further, the method includes determining one or more control commands for the IBR based on at least one of the power reference signal or the pitch reference signal and controlling the IBR based on the control command(s) so as to support a grid frequency of the electrical grid within power available at the IBR.
A system for coating ceramic fibers for use in manufacturing a ceramic matric composite (CMC) article includes a frame having a plurality of frame members arranged so as to create a void therebetween. At least one of frame members includes a hollow body and at least one perforated hole defined in the hollow body. Thus, the ceramic fibers are securable at respective ends of the frame and extend across the void. The frame also includes an inlet in fluid communication with the perforated hole(s) so as to allow a coating material to flow into and through the hollow body and out of the perforated hole(s) at a location of at least a portion of one of the ceramic fibers. As such, the coating material is configured to cause the portion of one of the ceramic fibers to separate from the frame such that the portion is uniformly coated with the coating material.
A system for imaging a component defining a negative space is provided comprising a component imaging assembly, a bolus insert, and an imaging device. The bolus insert is positionable in the component's negative space vvhen the component is positioned within an imaging device imaging field to produce a component image. A method is provided comprising positioning a bolus insert within a component's negative space and scanning the component having the bolus insert to create an image of the component. A component imaging assembly is provided comprising a component including a first portion having a first thickness that is greater than a second thickness of a second portion; and a bolus insert positioned adjacent the second portion that has a bolus thickness substantially similar to a difference between the first and second thicknesses. The bolus insert has a bolus material density within fifteen percent (15%) of a component material density.
G01N 23/04 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material
Extension tools and methods of inserting extension tools within components are provided. For example, an extension tool has a proximal end and a distal end and comprises a plurality of sequentially arranged links moveable relative to one another and a support member defining the distal end and including a first wheel disposed at the distal end and a second wheel spaced apart from the first wheel. Additionally, or alternatively, an extension tool may comprise a plurality of windows defined in the plurality of sequentially arranged links. The windows are defined periodically along the plurality of sequentially arranged links such that a periodicity of the windows corresponds to a periodicity of a plurality of features of the component.
Systems and methods of laser ablating a component to form a cavity are provided. In one aspect, a laser system laser ablates a component to remove a slice of material therefrom so that at least a portion of a section of the cavity is formed. With the slice of material removed, the laser system laser ablates the component along an outline of the section to remove excess sidewall material therefrom to form one or more sidewalls of the section. This removes tapering of the sidewalls. This process can be iterated to form the depth of the cavity. The laser system then laser ablates the component to remove excess end wall material therefrom to form an end wall of the cavity to a predetermined depth.
A cable tensioning system including: a body defining a balance point; a cable receiving area having gripping elements configured to grip and bias a cable relative to the cable tensioning system; and a sensor configured to sense changes to a balance of the body about the balance point, wherein the cable tensioning system is configured to maintain the cable within a preset range of tensions
An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body including: a first hinge; a second hinge, the first and second hinge members pivotally coupling adjacent segments of the plurality of segments together; and a cavity extending along the body of the segment, the cavity exiting the body at a plurality of exit locations, wherein at least one of the plurality of exit locations is disposed adjacent to the first hinge; and a selectively rigidizable strength member disposed within the cavity.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
B25B 33/00 - Hand tools not covered by any other group in this subclass
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
An insertion tool for performing an operation on equipment, the insertion tool including: a plurality of segments, each segment of the plurality of segments including a body comprising: a first hinge; and a second hinge, the first hinge of a first segment being coupled to the second hinge of a second segment adjacent to the first segment through an interface, wherein the interface comprises a powder gap, a multi-modal interface, a compliance feature, a displace-to- lock configuration, an interference fit, or any combination thereof, wherein the insertion tool is configured to be selectively rigidizable using a strength member interfacing with the plurality of segments.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
B25B 33/00 - Hand tools not covered by any other group in this subclass
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
A tool system for inserting into a cavity, the tool system including a first continuum having a flexible body defining a connection interface; and a second continuum having a flexible body defining a connection interface; and an engagement mechanism configured to couple the connection interfaces of the first and second continua together to form the tool.
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
B64F 5/60 - Testing or inspecting aircraft components or systems
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
Systems and methods of servicing engines including a method of servicing an engine, the method including navigating at least a portion of a robotic assembly to a location associated with the engine; applying, from the robotic assembly, a medium to one or more adjustable components of the engine while the engine is at an elevated temperature; waiting a duration of time; and with the robotic assembly, operating on the one or more adjustable components.
B64F 5/60 - Testing or inspecting aircraft components or systems
B25J 5/00 - Manipulators mounted on wheels or on carriages
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
F16N 3/00 - Devices for supplying lubricant by manual action
26.
PROBABILISTIC FATIGUE AND BLEND LIMIT ASSESSMENT AND VISUALIZATION METHODS FOR AIRFOILS
A method of analyzing a blended airfoil that includes generating a plurality of simulated blended airfoil designs each including one of a plurality of blend geometries, training surrogate models representing the plurality of simulated blended airfoil designs based on natural frequency, modal force, and Goodman scale factors, determining a likelihood of operation failure of each of the plurality of blended airfoil designs in response to one or more vibratory modes, determining which of the plurality of simulated blended airfoil designs violate at least one aeromechanical constraint and generating, a blend parameter visualization including a blend design space, where the blend design space includes one or more restricted regions indicating blended airfoil designs where at least one aeromechanical constraint is violates and one or more permitted regions indicating blended airfoil designs where no aeromechanical constraints are violated.
The present disclosure relates to systems and methods for improved anomaly detection for rotating machines. An example method may include determining a rotational speed of a rotating machine; determining, using a frequency domain transform of a signal, a frequency domain signal; determining, based on the rotational speed, a first frequency band within the frequency domain signal for identifying a fault frequency; determining a fault frequency within the first frequency band; determining, based on the fault frequency, a second frequency band within the first frequency band, wherein the second frequency band includes the fault frequency; determining, based on the second frequency band, a first fault index and a baseline of the first fault index; determining, based on a deviation of a second fault index from the baseline, a fault condition; and providing an alert based on the fault condition.
A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.
B64F 5/60 - Testing or inspecting aircraft components or systems
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
G01N 21/954 - Inspecting the inner surface of hollow bodies, e.g. bores
508352-2 AB STRACT An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom. Date Recue/Date Received 2021-06-02
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
30.
CONSUMABLE COATINGS AND METHODS OF PROTECTING A HIGH TEMPERATURE COMPONENT FROM DUST DEPOSITS
A coated component may have a consumable coating that protects the component from dust. A coated component may include a silicon containing substrate defining a substrate surface, a barrier coating on the substrate surface, with the barrier coating defining a barrier surface, and a consumable coating on the barrier surface. The consumable coating may include a ceramic oxide that includes a silicate. A component, such as a component of a turbomachine, may be protected from dust by applying a consumable coating on the component.
C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
31.
METHOD FOR MANUFACTURING WIND TURBINE TOWER STRUCTURE WITH EMBEDDED REINFORCEMENT ELEMENTS
A system for manufacturing a structure includes a supporting frame assembly (104) moveable in a vertical direction of the structure. Further, the system includes an additive printing assembly (118) secured to the supporting frame assembly. The additive printing assembly includes at least one printer head (120,122,130) configured to dispense a first cementitious material. The system also includes a reinforcement dispensing assembly (136) supported by the supporting frame assembly. Thus, the reinforcement dispensing assembly is configured to automatically and continuously dispense a plurality of reinforcing members as the structure is printed and built up via the at least one printer head and as the supporting frame assembly moves in the vertical direction.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B28B 23/02 - Arrangements specially adapted for the production of shaped articles with elements wholly or partly embedded in the moulding material wherein the elements are reinforcing members
E04G 21/04 - Devices for both conveying and distributing
32.
METHODS OF MANUFACTURING DISPERSION STRENGTHENED MATERIALS
A method for producing a dispersion strengthened material is presented. The method includes exposing a plurality of first metal particles to a suspension of dispersoid forming particles to form metal particles having the dispersoid forming particles thereon. The metal particles having the dispersoid forming particles there are subjected to an energy process to form a dispersion strengthened material. Also provided is a method of manufacturing a dispersion strengthened material or metal component that contains nano- sized dispersoids in a metal-based matrix.
Methods and apparatus for forming an aperture in a composite component are provided, to help reducing defects and/or non-conforming components. Provided is a method for forming an aperture in a ceramic matrix composite (CMC) component comprises, based on a final dimension of the aperture, selecting a tool having a tool size and a cutting surface; selecting an angle at which to cut the cornponent with the tool; cutting a back surface of the cornponent with the tool, the cutting surface positioned at the angle; repositioning the tool relative to the component; and cutting the aperture through to its final dimension from a front surface, the front surface opposite the back surface. In some embodiments, the tool is a core drill with a diarneter within a range of 60% to 90% of the aperture final dimension, and/or the angle is within a range of 100 to 60 with respect to the back surface.
506735-2 AB STRACT An insertion apparatus includes an insertion end positionable within a cavity and configured to travel through the cavity, a steering end opposite the insertion end, and a body extending from the insertion end to the steering end and sized to fit within the cavity. The body includes a plurality of members flexibly coupled together and individually actuated. Each member of the plurality of members includes at least one actuator strand. At least one member of the plurality of members has a first configuration in which the at least one member of the plurality of members has a first stiffness and a second configuration in which the at least one member of the plurality of members has a second stiffness greater than the first stiffness. At least a portion of the body is flexible to facilitate travel of the body through the cavity when the at least one member of the plurality of members is in the first configuration. The at least a portion of the body is configured to maintain a selected shape when the at least one member of the plurality of members is in the second configuration. Date Recue/Date Received 2020-12-22
G01M 99/00 - Subject matter not provided for in other groups of this subclass
G02B 23/24 - Instruments for viewing the inside of hollow bodies, e.g. fibrescopes
G12B 1/00 - Sensitive elements capable of producing movement or displacement for purposes not limited to measurement; Associated transmission mechanisms therefor
H02K 15/00 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
35.
METHODS OF FORMING CERAMIC MATRIX COMPOSITES USING SACRIFICIAL FIBERS AND NON-WETTING COATING
328251-2 AB STRACT Methods for preparing ceramic matrix composites using melt infiltration are provided as well as the resulting ceramic matrix composites. The methods and products include the incorporation of a non-wetting coating to one or more sacrificial fibers. The one or more sacrificial fibers are removed, such as decomposed during pyrolysis, resulting in the formation of a plurality of functional features, in the form of regular and elongate channels along the ceramic matrix composite. During the removing of the one or more sacrificial fibers, the non-wetting coating remains on an interior surface of the plurality of functional features to block infiltration of an infiltrant to the plurality of functional features and deposition thereon. Alternatively, the sacrificial fibers may be removed subsequent to melt infiltration. Date Recue/Date Received 2020-12-09
C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
328243-2 AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component. Date Recue/Date Received 2020-12-09
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
328241-2 AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration. Date Recue/Date Received 2020-12-09
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 3/24 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an apertured layer, e.g. of expanded metal
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
506107-2 AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features in the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet in fluid communication with a source of a cooling fluid flow. The CMC component further includes one or more bores cutting through the plurality of longitudinally extending ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite to form a cooling channel. The component may optionally include one or more film cooling throughholes cutting through the plurality of longitudinally extending ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component. Date Recue/Date Received 2020-12-09
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 3/24 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an apertured layer, e.g. of expanded metal
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
328237-2 AB STRACT A method of producing a ceramic matrix composite component. The method includes positioning a first plurality of ceramic matrix composite plies on top of one another, disposing a filler pack on the first plurality of ceramic matrix composite plies, and positioning a second plurality of ceramic matrix composite plies on top of the filler pack. One of the first plurality of ceramic composite plies or the second plurality of ceramic composite plies includes a bend angle, to define an interstice between the plurality of ceramic matrix composite plies with the filler pack disposed in the interstice. The filler pack includes one or more sacrificial fibers disposed therein, that subsequent to removal provide a functional feature, such as a cooling manifold in the filler pack. The method further includes forming one or more channels coupled to the one or more functional features for the flow of a cooling fluid therethrough. A ceramic matrix composite is also disclosed. Date Recue/Date Received 2020-12-09
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
A ceramic matrix cornposite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features The CMC component includes a plurality of longitudinally extendin5.4 ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of el muted functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
B28B 1/48 - Producing shaped articles from the material by removing material from solid section preforms for forming hollow articles, e.g. by punching or boring
B28B 23/02 - Arrangements specially adapted for the production of shaped articles with elements wholly or partly embedded in the moulding material wherein the elements are reinforcing members
B32B 3/24 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an apertured layer, e.g. of expanded metal
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
41.
CERAMIC MATRIX COMPOSITE COMPONENT INCLUDING COOLING CHANNELS AND METHOD OF PRODUCING
A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features in the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet in fluid communication with a source of a cooling fluid flow. The CMC component further includes one or more bores cutting through the plurality of longitudinally extending ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite to fomi a cooling channel. The component may optionally include one or more film cooling throughholes cutting through the plurality of longitudinally extending ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component.
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 3/24 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by an apertured layer, e.g. of expanded metal
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
An insertion apparatus for use with a rotary machine includes a body extending from an insertion end to a steering end and sized to fit within an annular cavity. The body has a first stiffness and curves along a circumference of the annular cavity as the insertion end travels through the annular cavity. The insertion apparatus also includes a stiffener coupled to the body and extending from the steering end to the insertion end. The stiffener has a second stiffness greater than the first stiffness. The insertion apparatus further includes at least one maintenance device coupled to the insertion end of the insertion apparatus and a displacement mechanism configured to adjust a position of the at least one maintenance device relative to the body.
G01M 99/00 - Subject matter not provided for in other groups of this subclass
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
43.
KNOWLEDGE-DRIVEN FEDERATED BIG DATA QUERY AND ANALYTICS PLATFORM
A system to query a federated store containing disparate data types and stores, the system including a UI or API to specify query details, a metadata knowledge graph with metadata describing the contents of the data stores, the relationships among them, and how to programmatically query the data stores, a predefined constrainable query ('nodegroup') store containing nodegroups providing a template to search the data stores, the querying layer including services and libraries to process nodegroups and generate a set of queries, a query and analysis platform providing the set of queries to at least one data store for execution at the federated stores and return a result, a scalable analytic execution layer applying machine learning/artificial intelligence techniques to analyze the query results and presenting data analysis result visualizations. A method and a non-transitory medium are also disclosed.
A system for querying a federated data store includes a metadata knowledge graph describing the contents and relationships among one or more underlying data stores, an interactive user interface receiving requests from a data consumer, a predefined constrainable query ('nodegroup') store containing predefined constrainable queries that define data subsets of interest across one or more of the underlying data repositories, a knowledge-driven querying layer generating and executing queries against the federated data store and merging responsive results, a scalable analytic execution layer receiving the search results from the federated data store and applying machine learning/artificial intelligence techniques to analyze the results, and a user interface presenting visualizations of raw or analyzed results to the consumer. A method and a non-transitory computer-readable medium are also disclosed.
A system to generate and run federated queries against a plurality of data stores storing disparate data types, the system including a user interface receiving query details from a data consumer, a metadata knowledge graph containing metadata for links and relationships of the data stores, a knowledge-driven querying layer accessing the graph and selecting predefined constrainable queries from a nodegroup store and applying the metadata links/relationships to the predefined constrainable queries to assemble subqueries, a query and analysis platform providing the subqueries to some of the data stores for execution, a scalable analytic execution layer receiving and aggregating search results from the data stores into a merged search result and/or obtaining analytic results by applying machine learning and artificial intelligence techniques to the distributed data, the user interface presenting visualizations generated from the merged search results, and/or the analytic results. A system and a non-transitory computer-readable medium are also disclosed.
A coated component, along with methods of its formation and use, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a mullite bondcoat on its surface. The mullite bondcoat includes an oxygen getter phase contained within a mullite phase. For example, the mullite bondcoat may include 60% to 98% by volume of the mullite phase. An environmental barrier coating is on the mullite bondcoat.
A coated component, along with methods of making and using the same, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a surface; a mullite/NOSC bondcoat on the surface of the substrate; and an environmental barrier coating on the mullite/NOSC bondcoat. The mullite/NOSC bondcoat comprises a non-oxide silicon ceramic (NOSC) phase contained within a mullite phase, with the mullite/NOSC bondcoat comprising 60% to 95% by volume of the mullite phase, such as 65% to 93% by volume of the mullite phase.
A method includes applying an infiltration coating on a thermal barrier coating of an article. The infiltration coating infiltrates at least some pores of the thermal barrier coating. The infiltration coating decomposes within the at least some pores of the thermal barrier coating to coat a portion of the at least some pores of the thermal barrier coating. The infiltration coating reduces a porosity of the thermal barrier coating. The method also includes applying a reactive phase spray formulation coating on the thermal barrier coating. The reactive phase spray formulation coating reacts with dust deposits on the thermal barrier coating.
An inspection system includes one or more imaging devices and one or more processors. The imaging devices generate a first set of images of a work piece at a first position relative to the work piece and a second set of images of the work piece at a second position relative to the work piece. At least some of the images in the first and second sets are acquired using different light settings. The processors analyze the first set of images to generate a first prediction image associated with the first position, and analyze the second set of images to generate a second prediction image associated with the second position. The first and second prediction images include respective candidate regions. The processors merge the first and second prediction images to detect at least one predicted defect in the work piece depicted in at least one of the candidate regions.
An inspection system includes one or more processors that obtain a first image of a work piece that has a fluorescent dye thereon in an ultraviolet (UV) light setting and a second image of the work piece in a visible light setting. The first and second images are generated by one or more imaging devices in the same position relative to the work piece. The one or more processors identify a candidate region of the first image based on a light characteristic of one or more pixels, and determine a corresponding candidate region of the second image that is at an analogous location as the candidate region of the first image. The one or more processors analyze both candidate regions to detect a potential defect on a surface of the work piece and a location of the potential defect relative to the surface of the work piece.
An inspection system includes an imaging device, visible light source, ultraviolet light source, and at least one processor. The imaging device generates a first image set of a work piece while the ultraviolet light source illuminates the work piece with ultraviolet light to cause fluorescent dye thereon to emit light, and generates a second image set of the work piece while the visible light source illuminates the work piece with visible light. The first and second image sets are generated at the same positions of the imaging device relative to the work piece. The processor maps the second image set to a computer design model of the work piece based on features depicted in the second image set and the positions of the imaging device. The processor determines a defect location on the work piece based on an analysis of the first image set and the computer design model.
A tool assembly includes a first selectively flexible tool including a first plurality of sequentially arranged links moveable between a slacked position and a tensioned position; and a second selectively flexible tool including a second plurality of sequentially arranged links moveable between a slacked position and a tensioned position, the second plurality of sequentially arranged links moveable over or through the first plurality of sequentially arranged links.
A selectively flexible extension tool includes a line assembly; and a plurality of sequentially arranged links, the line assembly operable with the plurality of sequentially arranged links to move the plurality of sequentially arranged links between a slacked position and a tensioned position, the plurality of sequentially arranged links spaced from one another when in the slacked position to allow the plurality of sequentially arranged links to pivotably move relative to one another, the plurality of sequentially arranged links pressed against one another when in the tensioned position to rigidly fix the plurality of sequentially arranged links to one another.
A grommet assembly for mounting to a component of a turbine engine is provided. In one exemplary aspect, the grommet assembly includes a grommet that is removably mounted within a pass-through opening defined by the component. The component may be formed of a composite material. A locking member may be mounted to a body of the grommet. A flange projects from the body. When the grommet is mounted to the component and the locking member is mounted to the body, the body is received by the pass-through opening of the component and the locking member is mounted to the body such that the locking member and the flange clamp the component to secure the grommet to the component. An interface member, such as a pin, may be received by a hole defined by the grommet.
F16L 5/00 - Devices for use where pipes, cables or protective tubing pass through walls or partitions
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
A porous tool includes a mold body and an additively-manufactured film attached to a surface of the mold body. The film includes a porous layer and a nonporous support layer. The porous layer may include a surface having an array of surface pore openings, a network of interconnected passages in fluid communication with the surface pore openings, and one or more lateral edges that have an array of edge pore openings in fluid communication with the interconnected passages. Methods of forming a porous tool include depositing additive material on a build surface using a directed energy deposition system to form a film while simultaneously subtracting selected portions of the additive material from the film using laser ablation. Methods of forming a molded component include conforming a moldable material to a shape using a porous tool that includes a mold body and an additively-manufactured film, and evacuating outgas from the moldable material through a porous layer of the film.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
56.
SYSTEM AND METHOD FOR PERFORMING OPERATIONS ON AN ENGINE
A system is provided for performing an operation on a component of an engine. The component includes a first side positioned within an interior of the engine. The system includes a first robotic arm defining a first distal end and including a first utility member positioned at the first distal end, the first robotic arm moveable to the interior of the engine to a location operably adjacent to the first side of the component; and a second robotic arm defining a second distal end and including a second utility member positioned at the second distal end, the second robotic arm also moveable to the interior of the engine to facilitate the first and second utility members performing the operation on the component of the engine.
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
B23B 39/14 - General-purpose boring or drilling machines or devices; Sets of boring or drilling machines with special provision to enable the machine or the drilling or boring head to be moved into any desired position, e.g. with respect to immovable work
A robotic arm assembly includes a robotic arm including a link, a control rope operable with the link, and an attachment section, the control rope extending at least partially through the attachment section. The robotic arm assembly also includes an actuator pack attached to, or positioned adjacent to, the attachment section of the robotic arm, the actuator pack including an actuator, the actuator operable with the control rope and including a motor defining a pivot axis, the motor configured to move about the pivot axis to displace the control rope.
A method is provided for constructing a robotic arm including a plurality of links and a rope assembly. The method includes providing the rope assembly having a rope with a plurality of rope bearings threaded thereon; and attaching the plurality of rope bearings of the rope assembly to the plurality of links of the robotic arm.
A method for constructing a robotic arm includes positioning a wire in a formation zone for the robotic arm; and forming a body of the robotic arm in the formation zone around the wire such that the body of the robotic arm encloses at least a portion of the wire.
A robotic arm assembly includes a robotic arm, a base, and a utility member, the robotic arm extending between a root end attached to the base and a distal end including the utility member. A method for controlling the robotic arm assembly includes: determining a position of the base, the root end, or both relative to the environment; determining a task position and orientation for the utility member within the environment; determining a three-dimensional constraint of the environment; and determining a path for the robotic arm through the environment based on each of the position of the base, the root end, or both relative to the environment, the task position and orientation for the utility member within the environment, and the three-dimensional constraint of the environment.
G05D 3/12 - Control of position or direction using feedback
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
A tool for inspecting an annular section of an engine includes a first segment extending along a first lengthwise direction between a forward end and an aft end; and a second segment extending along a second lengthwise direction between a forward end and an aft end, the forward end of the first segment pivotably coupled to the aft end of the second segment and the first segment moveable relative to the second segment between a bent position and a coupled position, the first lengthwise direction defining a coupled angle with the second lengthwise direction when the first segment is in the coupled position relative to the second segment. The tool also includes an adjustment member operable with the first segment, the second segment, or both to adjust the coupled angle defined by the first lengthwise direction with the second lengthwise direction.
The present disclosure is directed to methods for manufacturing wind turbine rotor blades and components thereof. In one embodiment, the method includes forming an outer surface of a rotor blade panel from one or more fiber-reinforced outer skins. The method also includes printing and depositing at least one reinforcement structure onto an inner surface of the one or more fiber-reinforced outer skins to form the rotor blade panel, wherein the reinforcement structure bonds to the one or more fiber-reinforced outer skins as the reinforcement structure is being deposited.
B33Y 80/00 - Products made by additive manufacturing
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
A probe driver may have a coupling that interfaces with a conduit section at a first position of the conduit section. The probe driver also may have an input structure that actuates in response to a user input indicating a second position of the conduit section. The probe driver may also have one or more positioning elements to reposition the conduit section to interface with the coupling at the second position of the conduit section in response to the user input.
Dual sided shot peening system includes pressurized air supply in communication with independently controllable first and second air pressure regulators in communication with first and second shot supplies and independently controlled first and second shot flow control valves disposed between first and second nozzles and the shot supplies. Computer may be in control of regulators and valves. Nozzle supports may fixedly or movably support nozzles during shot peening. The system may be used for simultaneously shot peening first and second sides of a portion of a workpiece such as airfoils of a BLISK. First and second streams from first and second nozzles may have different properties and may be varied during shot peening.
B24C 1/10 - Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
B24C 3/32 - Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
B24C 7/00 - Equipment for feeding abrasive material; Controlling the flowability, constitution, or other physical characteristics of abrasive blasts
Tooling assemblies and methods for using a tooling assembly to shape an article are provided. For example, a tooling assembly has a forward end and an aft end and comprises a first tool segment, a second tool segment, a forward cam portion near the forward end, and an aft cam portion near the aft end. The forward cam portion defines a follower surface, and at least a portion of the follower surface has a curvilinear profile. The aft cam portion defines a first surface extending at a first angle and a second surface extending at a second angle. The first and second tool segments define a cavity for shaping an article. An exemplary method comprises positioning an article preform within the cavity and inserting a fastener within the aft end of the tooling assembly until the fastener is fully inserted within the tooling assembly.
The present invention relates a method of monitoring an automated radiosynthesizer during a run and the radiosynthesizer having a number of individual activity detectors operably associated therewith. The method comprises the steps of recording S10 activity data from each activity detector; accessing S20 historic data from a data storage; detecting S30 precursor of yield drop in the recorded activity data based on the historic data; predicting (S40 yield when synthesizing a tracer with the radiosynthesizer based on the detected precursor of yield drop; and initiating S50 actions related to a level of predicted yield.
A stator assembly of an electric machine includes a stator core having a slot extending between a first end and a second end, where the slot includes a first slot exit at the first end and a second slot exit at the second end. Also, the stator assembly includes a plurality of windings, where one of the plurality of windings is disposed in the slot and extends from the first slot exit to the second slot exit, and where the plurality of windings includes at least one conductor and an insulation disposed around the at least one conductor. Further, the stator assembly includes a dielectric plate coupled to one of the first slot exit and the second slot exit and configured to suppress surface discharges on windings present at one of the first slot exit and the second slot exit to which the dielectric plate is coupled.
An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
A method includes capturing an image, and performing region detection on the captured image. The region detection includes identifying an object represented in the captured image. The method further includes detecting emissivity of the identified object and determining the temperature of the object based on the detected emissivity of the object.
Composite components having a T or L-shaped configuration that include features that reduce void defects between abutting laminate portions and provide improved mechanical properties are provided. Methods for forming such components are also provided. In one exemplary aspect, a composite component defines a first direction and a second direction and includes a wedged-shaped noodle at a joint interface between an abutting first laminate portion extending along the first direction and a second laminate portion extending along the second direction. The noodle has a first surface that is angled with respect to the second direction. At least one of the plies of the second laminate portion terminate and attach to the angled first surface of the noodle.
B32B 3/06 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
B29C 65/00 - Joining of preformed parts; Apparatus therefor
B32B 3/08 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
A method of forming titanium-based spherical metallic particles includes performing a hydride-dehydride process on a meltless metallic sponge to form a feedstock material including a metallic powder. The method further includes introducing the feedstock material into a microwave plasma discharge to form the titanium-based spherical metallic particles.
B22F 9/14 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using physical processes using electric discharge
A method of forming titanium-based spherical metallic particles includes contacting a feedstock material including a metal halide with a reductant in the presence of a microwave plasma discharge.
B22F 9/14 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using physical processes using electric discharge
B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
73.
HEAT DISSIPATION SYSTEM FOR ELECTRIC AIRCRAFT ENGINE
The example embodiments are directed to a heat dissipation system for an electric aircraft engine. In an example, the aircraft engine includes an electric system configured to power an engine fan to provide thrust to an aircraft, the electric system including cooling channels to receive a coolant to cool one or more components of the electric system, a power source to power the electric system, and one or more guide vanes connected to the cooling channels of the electric system and configured to receive the coolant heated by and output from the cooling channels, wherein the one or more guide vanes are further to cool the heated coolant and transfer the cooled coolant back to the cooling channels of the electric system. By dissipating heat from electric system via the guide vanes, the cooling system can provide sufficient cooling without adding additional drag to the aircraft.
A method for controlling the porosity parameter of porous thermal barrier coatings is presented. The method includes disposing a feedstock material on a substrate to form a porous thermal barrier coating. The feedstock material includes a gas-forming additive and a thermal barrier coating material. The disposing step further includes controlling the porosity parameter of the porous thermal barrier coating by controlling a feedstock material feed rate, an amount of the gas-forming additive in the feedstock material, a temperature of the disposed feedstock material on the substrate, or combinations thereof.
Rotor blade panels, along with methods of their formation, are provided. The rotor blade panel may include one or more fiber-reinforced outer skins having an inner surface; and, a plurality of reinforcement structures on the inner surface of the one or more fiber-reinforced outer skins, where the reinforcement structure bonds to the one or more fiber-reinforced outer skins as the reinforcement structure is being deposited. The reinforcement structure includes, at least, a first composition and a second composition, with the first composition being different than the second composition.
B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
76.
METHODS FOR MANUFACTURING WIND TURBINE ROTOR BLADE PANELS HAVING PRINTED GRID STRUCTURES
A method for manufacturing a rotor blade panel of a wind turbine includes placing one or more fiber-reinforced outer skins into a mold of the rotor blade panel. The method also includes printing and depositing, via a computer numeric control (CNC) device, a plurality of rib members that form at least one three-dimensional (3- D) reinforcement grid structure onto an inner surface of the one or more fiber- reinforced outer skins. Further, the grid structure bonds to the one or more fiber- reinforced outer skins as the grid structure is deposited. Moreover, the method includes printing at least one additional feature into the grid structure.
A method for manufacturing an outer skin of a rotor blade includes forming an outer skin layer of the outer skin from a first combination of at least one of one or more resins or fiber materials. The method also includes forming an inner skin layer of the outer skin from a second combination of at least one of one or more resins or fiber materials. More specifically, the first and second combinations are different. Further, the method includes arranging the outer and inner skin layers together in a stacked configuration. In addition, the method includes joining the outer and inner skin layers together to form the outer skin.
B29C 53/56 - Winding and joining, e.g. winding spirally
B33Y 80/00 - Products made by additive manufacturing
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
A method for manufacturing a rotor blade panel of a wind turbine includes placing a mold of the rotor blade panel relative to a computer numeric control (CNC) device. The method also includes forming one or more fiber-reinforced outer skins in the mold. The method also includes printing and depositing, via the CNC device, printing and depositing, via the CNC device, a plurality of rib members that intersect to form at least one three-dimensional (3-D) reinforcement grid structure onto an inner surface of the one or more fiber-reinforced outer skins before the one or more fiber-reinforced outer skins have cooled from forming. Further, the grid structure bonds to the fiber-reinforced outer skin(s) as the structure is deposited. In addition, the plurality of rib members include, at least, a first rib member extending in a first direction and a second rib member extending in a different, second direction. Moreover, the first rib member has a varying height along a length thereof.
The present disclosure is directed to an apparatus for manufacturing a composite component. The apparatus includes a mold onto which the composite component is formed. The mold is disposed within a grid defined by a first axis and a second axis. The apparatus further includes a first frame assembly disposed above the mold, and a plurality of machine heads coupled to the first frame assembly within the grid in an adjacent arrangement along the first axis. At least one of the mold or the plurality of machine heads is moveable along the first axis, the second axis, or both. At least one of the machine heads of the plurality of machine heads is moveable independently of one another along a third axis.
The present disclosure is directed to an apparatus and method for manufacturing a composite component. The apparatus includes a mold onto which the composite component is formed. The mold is disposed within a grid defined by a first axis and a second axis. The apparatus further includes a first frame assembly disposed above the mold and a plurality of machine heads coupled to the first frame assembly within the grid in an adjacent arrangement along the first axis. At least one of the mold or the plurality of machine heads is moveable along the first axis, the second axis, or both. At least one of the machine heads of the plurality of machine heads is moveable independently of one another along a third axis. A second frame assembly is moveable above the mold along the first axis, the second axis, or both. The second frame assembly includes a holding device. The holding device affixes to and releases from an outer skin to place and displace the outer skin at the mold.
B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component.
A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.
F02C 7/14 - Cooling of plants of fluids in the plant
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
83.
SYSTEMS AND METHOD FOR ROBOTIC INDUSTRIAL INSPECTION SYSTEM
An asset inspection system includes a robot and a server. The server receives a request for data from the robot, wherein the requested data comprises an algorithm, locates the requested data in a database stored on the server, encrypts the requested data, and transmits the requested data to the robot. The robot is configured to collect inspection data corresponding to an asset based at least in part on the requested data and transmit the collected inspection data to the server.
A method of fabricating an object by additive manufacturing is provided. The method includes irradiating a portion of powder in a powder bed, the irradiation creating an ion channel extending to the powder. The method also includes applying electrical energy to the ion channel, wherein the electrical energy is transmitted through the ion channel to the powder in the powder bed, and energy from the irradiation and the electrical energy each contribute to melting or sintering the portion of the powder in the powder bed.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
85.
HIGH TEMPERATURE ENGINEERING STIFFNESS CORE-SHELL MOLD FOR CASTING
A method for fabricating a ceramic mold is provided. The method includes the steps of contacting a cured portion of a workpiece with a liquid ceramic photopolymer, irradiating a portion of the liquid ceramic photopolymer adjacent to the cured portion through a window contacting the liquid ceramic photopolymer, removing the workpiece from the uncured liquid ceramic photopolymer, and repeating the steps until a ceramic mold is formed. The ceramic mold includes a first opening for creating a cast article and a second opening for receiving a support member.
B22C 13/08 - Moulding machines for making moulds or cores of particular shapes for shell moulds or shell cores
B22C 1/16 - Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by the use of binding agents; Mixtures of binding agents
System includes a particle accelerator configured to direct a particle beam of charged particles along a designated path. The system also includes an extraction device positioned downstream from the particle accelerator. The extraction device includes a stripper foil and a foil holder that holds the stripper foil. The foil holder is configured to position the stripper foil across the designated path of the particle beam such that the particle beam is incident thereon. The stripper foil is configured to remove electrons from the charged particles, wherein the stripper foil includes a backing layer and a conductive layer stacked with respect to one another. The backing layer includes synthetic diamond.
H05H 7/00 - PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY- CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS - Details of devices of the types covered by groups
H05H 13/00 - Magnetic resonance accelerators; Cyclotrons
A method for forming a ceramic matrix composite article includes laying up a first group of plies; laying up a second group of plies, the first and second groups of plies being adjacent to each other; compacting the first group of plies and the second group of plies in the same processing step; and performing a first infiltration process on the first group of plies. The method also includes performing a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.
A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.
Methods and apparatus for determining radiation doses based on phantom matching are disclosed. An example apparatus includes an image processor to process a scout image to determine the first dimensions of an anatomical landmark of the scout image file; a comparator to select a phantom model based on the first dimensions, the phantom model including the anatomical landmark with second dimensions substantially similar to the first dimensions; and a dose calculator to calculate a radiation dose for an organ in the anatomical landmark based on the selected phantom.
A turbomachine includes a turbine section including a turbine. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction. The turbomachine also includes a gearbox. The first plurality of turbine rotor blades and the second plurality of turbine rotor blades are each coupled to one of a ring gear, a planet gear, or a sun gear of the gearbox such that the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox. The turbomachine also includes an electric machine assembly including a rotor coupled to one of the ring gear, the planet gear, or the sun gear of the gearbox such that the rotor rotates relative to a stator during operation.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F16H 3/72 - Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion with a secondary drive, e.g. regulating motor, in order to vary speed continuously
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
91.
CONTACT INTERFACE FOR A COMPOSITE COMPONENT AND METHODS OF FABRICATION
Composite components having structurally reinforced contact interfaces are provided. In one example, the component can include an inner laminate formed of one or more inner plies having reinforcement fibers oriented along a reference direction within a matrix material. The component can also include an interface laminated positioned on the inner laminate along at least a portion of a contact surface of the component. The interface laminate is formed of one or more interface plies having reinforcement fibers oriented along a direction offset from the reference direction within a matrix material. Methods for fabricating such components are also provided.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a propulsion system. The propulsion system includes a plurality of electric fans integrated into the wing and oriented to generate thrust along a vertical direction, the plurality of electric fans arranged along a length of the wing and including an outer-most electric fan along a transverse direction relative to the fuselage. The outer- most electric fan is at least one of a variable pitch fan or a variable speed fan to provide increased stability to the aircraft.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 3/32 - Wings specially adapted for mounting power plant
B64C 3/38 - Adjustment of complete wings or parts thereof
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 29/02 - Power-plant nacelles, fairings, or cowlings associated with wings
A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface with a plurality of cavities defined therein, a bond coating (e.g., including a silicon material) on the surface of the substrate within the cavities, and an environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities. Such a coated component may be, in one embodiment, a turbine component, such as a CMC component for use in a hot gas path of a gas turbine engine.
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
C23C 26/02 - Coating not provided for in groups applying molten material to the substrate
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
94.
BOND COATINGS HAVING A SILICON-PHASE CONTAINED WITHIN A REFRACTORY PHASE
A coated component, along with method of forming the same, is provided. The coated component may include a substrate having a surface, a silicon-based bond coating on the surface of the substrate, and an EBC on the silicon-based bond coating. The silicon-based bond coating may include a silicon-phase contained within a refractory phase. The silicon-phase, when melted, is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating. Such a coated component may be, in particular embodiments, a turbine component.
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
C23C 26/02 - Coating not provided for in groups applying molten material to the substrate
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
95.
BOND COATINGS HAVING A MOLTEN SILICON-PHASE CONTAINED BETWEEN REFRACTORY LAYERS
A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface, a first refractory layer on the surface of the substrate, a silicon-based bond coating on the first refractory, and an environmental barrier coating on the silicon-based bond coating. The silicon- based bond coating includes a silicon-phase contained within a refractory phase such that, when melted, the silicon-phase is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating.
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
C23C 26/02 - Coating not provided for in groups applying molten material to the substrate
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
96.
HIGH QUALITY SPHERICAL POWDERS FOR ADDITIVE MANUFACTURING PROCESSES ALONG WITH METHODS OF THEIR FORMATION
Methods for forming a high-quality powder from a feedstock powder of feedstock particles having Irregular shapes are provided. The method Includes exposing the feedstock powder to a plasma field to form a treated powder of treated particles having a more spherical shape than the feedstock particles Prior to the plasma field exposure, the feedstock particles have an oxidized layer thereon as a result from previous exposure to water After exposure to the plasma field, the treated particles are substantially free from an oxidized layer
B22F 9/14 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using physical processes using electric discharge
B33Y 70/00 - Materials specially adapted for additive manufacturing
B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
B22F 9/22 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using chemical processes with reduction of metal compounds starting from solid metal compounds using gaseous reductors
97.
ARTICLES FOR CREATING HOLLOW STRUCTURES IN CERAMIC MATRIX COMPOSITES
The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.
Compounds are generally provided, which may be particularly used to form a layer in a coating system. In one embodiment, the compound may have the formula: A x B b L n1-x-bHf1-t-d Ti t D d MO6, where: A is Al, Ga, In, Sc, Y, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Fe, Cr, Co, Mn, Bi, or a mixture thereof; x is about 0.01 to about 0.99; b is 0 to about 0.5, with 1-x-b being 0 to about 0.99 such that Ln is present in the compound; Ln is a rare earth or a mixture thereof that is different than A; t is 0 to about 0.99; D is Zr, Ce, Ge, Si, or a mixture thereof; d is 0 to about 0.5; the sum of t and d is less than 1 such that Hf is present in the compound; and M is Ta, Nb, or a mixture thereof.
A gas turbine engine having an improved air delivery system that includes features for pressurizing and/or cooling various components of the engine while minimizing the impact to the cycle efficiency of the engine, reducing the weight of the engine, and reducing the specific fuel consumption of the engine is provided.
Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a method for assembling an airfoil with a boundary structure to form a flow path assembly is provided. The method includes machining an opening into the boundary structure. The opening is sized to receive an airfoil or other component. The method also includes machining a cutout into the boundary structure proximate the opening. A locking feature is inserted into the cutout. When the airfoil is inserted into the opening, the locking feature interlocks the airfoil with the boundary structure. To seal the airfoil with the boundary structure, the airfoil is pressed against or into the boundary structure. When the airfoil is pressed, the locking feature is compressed such that a seal is formed between the airfoil and the boundary structure to seal the flow path assembly.
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
F01D 5/32 - Locking, e.g. by final locking-blades or keys
F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
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