A heat exchanger includes a core defining a first passageway for a first fluid flow and a second passageway for a second fluid flow. The core includes an assembly of a plurality of unit cells coupled together. Each unit cell defines a first passageway portion within an interior volume and a second passageway portion at an exterior surface. Each unit cell includes a plurality of first openings into the interior volume and forms the second passageway in volumes between the plurality of unit cells. The assembly is shaped to combine and divide the first fluid in the first passageway portion and combine and divide the second fluid in the second passageway portion during exchange of heat between the first fluid and the second fluid. Each second passageway portion receives the second fluid from three other second passageway portions. The heat exchanger further includes at least one baffle in at least one of the first passageway or the second passageway to route the first fluid flow independently from the second fluid flow.
F28D 7/16 - 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 arranged in parallel spaced relation
F28F 9/22 - Arrangements for directing heat-exchange media into successive compartments, e.g. arrangements of guide plates
Techniques for using a pyrometer to measure one or more operating characteristics of a target are provided. In one example aspect, a pyrometer is oriented relative to a target having target elements spaced from one another such that, as the target is rotated, the pyrometer alternately i) senses a target element for a period of time; and ii) then does not sense any of the target elements for a period of time as no appreciable signal is received. The pyrometer generates an output signal having alternating target pulse widths and null widths. The target and null widths have different amplitudes. The amplitude of the null signal provides an amplitude baseline for which the amplitudes of the target widths or signals may be compared to so that a temperature or other operating characteristic associated with the target can be determined.
A bearing assembly includes a bearing, an outer race located radially outward of the bearing and supporting the bearing, a bearing housing located radially outward of the outer race and supporting the bearing and the outer race, and a bearing lubricant drain including a multi-directional passage formed in one or both of the outer race or the bearing housing, the lubricant drain arranged to cause a lubricant to flow from a first location to a second location. The second location is radially outward and axially offset from the first location. A gas turbine engine includes a shaft configured to rotate about a centerline axis of the gas turbine engine and the bearing assembly configured to facilitate the rotation of the shaft.
F16C 33/66 - Special parts or details in view of lubrication
F16C 19/06 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly with a single row of balls
4.
SYSTEM AND METHOD FOR DETERMINING PROBABILISTIC BURST
Systems and methods are provided herein that are useful to determining probabilistic burst for a component. In particular, the systems and methods generate an overspeed distribution for the component, the overspeed distribution being indicative of a probability that various overspeed values will be obtained. The method involves receiving field analytics data indicative of time the component spends in at least one operating condition and receiving overspeed data indicative of overspeed values for the component as a function of the at least one operating condition. The method further includes generating an overspeed distribution for the component based on the field analytics data and the overspeed data. A probability of burst for the component may then be determined based on the overspeed distribution.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
A gas turbine engine includes an aft frame and a forward frame disposed upstream from the aft frame. The forward frame includes an outer ring. The outer ring includes an inner surface that is radially spaced from an outer surface. A first indention is defined in the outer surface, and a first engine mount flange protrudes radially outwardly from the first indention.
Example pump systems having dual-function annular heat exchangers are disclosed. An example pump system to pressurize a fluid within a closed loop transport bus includes a pump to move the fluid, a conduit in fluid connection with the pump, a heat exchanger positioned around at least a portion of the conduit, the heat exchanger to receive a first electrical signal transmitted in a first direction at a first time and a second electrical signal transmitted in a second direction at a second time different from the first time, the second direction opposite the first direction.
A system is provided with a controller configured to receive a computer model of a mold configured to cast a part. The computer model has a variable wall thickness of the mold thermally tailored to a geometry of the part. The controller is configured to control a manufacturing system to produce the mold based on the computer model.
B28B 1/00 - Producing shaped articles from the material
B28B 17/00 - SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER - Details of, or accessories for, apparatus for shaping the material; Auxiliary measures taken in connection with such shaping
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B33Y 80/00 - Products made by additive manufacturing
8.
IMAGING SYSTEM ISOLATION ENCLOSURE FOR PATHOGEN CONTAINMENT DURING MEDICAL IMAGING PROCEDURES
Systems are provided for an imaging system isolation enclosure for use with a medical imaging system includes a pathogen impermeable enclosure for use with one or more of radiation imaging systems and magnetic resonance imaging systems, the pathogen impermeable enclosure is configured to provide a barrier between the imaging system and at least one of a patient user and an imaging room, and an air filtration system including an inlet to supply a cooling air flow to an interior of the imaging system isolation enclosure and an outlet to output exhaust air from an interior of the imaging system isolation enclosure.
An approach for facilitating mechanical and electrical connection of electric machines and electrical components in an electrical system using connectors with quick connect/disconnect electrical connectors is disclosed. Each quick connect/disconnect electrical connector can be placed on the end of an electrical power distribution cable that connects with an electric machine or electrical component. The electric machines and electrical components and the electrical power distribution cables can have hollow coolant passages formed therein to receive cooling fluid from a cooling device for direct cooling of the electric machines, electrical components and the electrical power distribution cables.
H01R 24/28 - Coupling parts carrying pins, blades or analogous contacts and secured only to wire or cable
H01R 13/00 - ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS - Details of coupling devices of the kinds covered by groups or
H01R 13/52 - Dustproof, splashproof, drip-proof, waterproof, or flameproof cases
H01R 24/20 - Coupling parts carrying sockets, clips or analogous contacts and secured only to wire or cable
H01R 24/66 - Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure with pins, blades or analogous contacts and secured to apparatus or structure, e.g. to a wall
H01R 24/76 - Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure with sockets, clips or analogous contacts and secured to apparatus or structure, e.g. to a wall
H02J 3/38 - Arrangements for parallelly feeding a single network by two or more generators, converters or transformers
10.
COATED ARTICLE FOR HOT HYDROCARBON FLUID AND METHOD OF PREVENTING FUEL THERMAL DEGRADATION DEPOSITS
A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.
C23C 2/04 - Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shape; Apparatus therefor characterised by the coating material
B05D 1/18 - Processes for applying liquids or other fluent materials performed by dipping
B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
B32B 15/18 - Layered products essentially comprising metal comprising iron or steel
C09D 1/00 - Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances
C23C 4/04 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
C23C 20/00 - Chemical coating by decomposition of either solid compounds or suspensions of the coating forming compounds, without leaving reaction products of surface material in the coating
C23C 20/06 - Coating with inorganic material, other than metallic material
C23C 20/08 - Coating with inorganic material, other than metallic material with compounds, mixtures or solid solutions, e.g. borides, carbides, nitrides
C23C 24/00 - Coating starting from inorganic powder
The present approaches are generally directed to facilitating healing of wounds, including chronic wounds typically associated with slow heal times or which are persistent. In one embodiment, a method of promoting wound healing comprises positioning an ultrasound transducer at a stimulation site on a subject having a wound. Pulsed focused ultrasound (pFUS) is non-invasively applies using the transducer to cause modulation of a target anatomic site containing resident or circulating immune cells. Modulation of the target anatomic site of the subject causes migration of one or more of monocytes, macrophages, or neutrophils to a wound bed of the wound.
A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
General Electric Company Polska Sp. z o.o. (Poland)
Inventor
Kuropatwa, Michal Tomasz
Deskiewicz, Adam Wojciech
Kaminski, Robert
Kunicki, Adam
Kray, Nicholas Joseph
Abstract
A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
A gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath. The gas turbine engine also includes a turbine rear frame extending through the core air flowpath at a location downstream of the turbine section and defining a leading edge within the core air flowpath. The gas turbine engine also includes a waste heat recovery system operable to separate, at or upstream of the leading edge of the turbine rear frame, a core airflow exiting the turbine section into a primary exhaust airflow and a waste heat recovery airflow. The waste heat recovery system comprises a heat source exchanger positioned to receive the waste heat recovery airflow.
A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.
Phosphor materials and devices containing such phosphor materials are disclosed. An ink composition of in accordance with the present disclosure comprises a phosphor material comprising a Mn4+ doped phosphor of formula 1, Ax[MFy]:Mn4+ (I), and at least one rare earth containing Garnet phosphor, the at least one rare earth Garnet phosphor is present in the phosphor material in an amount of at least about 80 wt % based on the weight of the phosphor material, wherein the at least one rare earth containing a Garnet phosphor has a D50 particle size from about 0.5 microns to about 15 microns, where A is Li, Na, K, Rb, Cs, or a combination thereof; M is Si, Ge, Sn, Ti, Zr, Al, Ga, In, Sc, Y, La, Nb, Ta, Bi, Gd, or a combination thereof; x is the absolute value of the charge of the [MFy] ion; and y is 5, 6 or 7.
C09D 11/50 - Sympathetic, colour-changing or similar inks
C09D 11/037 - Printing inks characterised by features other than the chemical nature of the binder characterised by the pigment
C09D 11/107 - Printing inks based on artificial resins containing macromolecular compounds obtained by reactions only involving carbon-to-carbon unsaturated bonds from unsaturated acids or derivatives thereof
C09K 11/02 - Use of particular materials as binders, particle coatings or suspension media therefor
C09K 11/61 - Luminescent, e.g. electroluminescent, chemiluminescent, materials containing inorganic luminescent materials containing fluorine, chlorine, bromine, iodine or unspecified halogen elements
A method of imaging a turbine engine test component with a first surface and a second surface that is spaced from the first surface. The turbine engine test component includes a plurality of film holes with inlets formed in the second surface or interior that are fluidly coupled to outlets formed in the first surface or exterior. The method includes flowing airflow through the plurality of film holes of the turbine engine test component, obtaining thermographic data, determining a test dataset, and calculating a performance score.
An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (α) and a layback surface defining a second angle (β).
Methods, apparatus, systems, and articles of manufacture to produce cryo-compressed hydrogen are disclosed. An example cryo-compressed hydrogen production system includes a compressor to compress an input of hydrogen, at least one heat exchanger to cool the hydrogen, and a conduit to convey the hydrogen at least partially to a storage tank for storage at a temperature less than or equal to a first threshold and greater than a second threshold, the first threshold defined by an upper temperature limit for cryo-compressed hydrogen, the second threshold defined by a hydrogen liquefaction temperature.
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
22.
GRADIENT WITHIN A THERMAL BARRIER COATING AND METHODS OF THEIR FORMATION
Methods are provided for forming a thermal barrier coating having a non-linear compositional gradient and/or a non-linear porosity gradient, along with coated components formed therefrom. The method includes spraying a deposition mixture of a first composition and a second composition via a solution precursor plasma spray apparatus onto a surface of a substrate; while spraying the deposition mixture, adjusting at least one deposition parameter such that the thermal barrier coating is formed with the non-linear gradient.
A distributed control system includes an electronic control unit to establish secure communication with a distributed control module. Upon determination that a previously negotiated session key is stored on the electronic control unit, the electronic control unit transmits encrypted communications with the distributed control module using the previously negotiated session key, negotiates a new session key with the distributed control module, and stores the new session key. Upon determination that the previously negotiated session key is not stored on the electronic control unit, the electronic control unit negotiates the new session key with the distributed control module. After negotiating the new session key with the distributed control module, the electronic control unit ceases transmission of unencrypted communications with the distributed control module, transmits encrypted communications with the distributed control module using the new session key, and stores the new session key.
An apparatus and method for a degassing apparatus with a degassing chamber and a container. The container is located within the degassing chamber and defines a holding chamber with an opening. An insert for being received in the opening. The insert including at least one conduit extending between an inlet and an outlet.
A system includes a hydrogen sensor configured to generate data indicative of a level of hydrogen present within the compartment and a computing system. The computing system configured to determine at least one of the level of hydrogen present within the compartment or a rate of change of the level of hydrogen present within the compartment and compare the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment to an associated threshold value. Furthermore, when the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment exceeds the associated threshold value, the computing system is configured to initiate a control action associated with reducing the level of hydrogen present within the compartment.
A heat exchanger includes an inlet plenum chamber, an outlet plenum chamber fluidly coupled to the inlet plenum chamber, and a plurality of intermediate plenum chambers disposed downstream from the inlet plenum chamber and upstream from the outlet plenum chamber. The plurality of intermediate plenum chambers includes a first intermediate plenum chamber, at least one tube bundle, and a first bypass valve fluidly coupled to the first intermediate plenum chamber. The first bypass valve is configured to control fluid flow rate from the first intermediate plenum chamber to the outlet plenum chamber.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.
A gas turbine engine is provided. The gas turbine engine includes: a fan; a turbomachine drivingly coupled to the fan and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, the turbomachine defining an annular cooling passage extending between a CP inlet and a CP outlet, the CP inlet in airflow communication with the working gas flowpath and the CP outlet in airflow communication with the bypass passage; and a variable bleed assembly including a variable bleed duct extending between a VB inlet and a VB outlet, the VB inlet in airflow communication with the working gas flowpath at a location downstream of the CP inlet and the VB outlet in airflow communication with the annular cooling passage for urging an airflow through the cooling passage.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
An additive manufacturing apparatus includes a support configured to support a resin and a constituent material. A support plate includes a window. A stage is configured to hold one or more composite layers of the resin and the constituent material to form a composite component positioned opposite the support plate. A radiant energy device is positioned on an opposite side of the support from the stage and is operable to generate and project radiant energy in a patterned image through the window. An actuator assembly is configured to move the stage in a Z-axis direction and a Y-axis direction.
Dual-phase magnetic components include an intermixed first region and second region formed from a single material, wherein the first region includes a magnetic ferrous composition, and wherein the second region includes a non-magnetic austenite composition and a dispersion of nitride precipitates.
A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
33.
DEVICES, SYSTEMS, AND METHODS FOR SECURELY LOADING EMBEDDED SOFTWARE USING A MANIFEST
A method for initializing an engine control system of an aircraft may include authenticating a boot loader, authenticating a manifest in response to authentication of the boot loader wherein the manifest contains hashes of one or more software components, and in response to authentication of the manifest, loading a first set of software components from among the one or more software components onto a non-transitory computer-readable medium, calculating a hash of each software component of the first set of software components, authenticating the first set of software components by comparing the calculated hash of each software component of the first set of software components to the hash of a corresponding software component in the manifest, and executing the first set of software components in response to authentication of the one or more software components. Devices and systems are also provided for initializing an engine control system of an aircraft.
G06F 21/57 - Certifying or maintaining trusted computer platforms, e.g. secure boots or power-downs, version controls, system software checks, secure updates or assessing vulnerabilities
A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (LT) along the axial direction, a circumference span (CS) along the circumferential direction, and a radial height (ΔrT) along the radial direction, and wherein these parameters are related by a tank sizing factor (TSF) equal to the effective length (LT) times the circumference span (CS) divided by the radial height (ΔrT) squared LT×CS/ΔrT2), wherein the tank sizing factor (TSF) is between 20 and 2200.
A rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along a central axis of the rotary component and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the rotary component. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Further, at least one feature of the plurality of features is a slot having an acoustic liner feature integrated therein to reduce operational noise of the rotary component.
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
A gas turbine engine includes a rotatably driven engine component including a shaft coupling. The shaft coupling defines a first axial centerline and includes an inner surface. The inner surface includes a plurality of internal splines extending radially inwardly from the inner surface with respect to the first axial centerline. The engine further includes a driving member having a driving end portion and defining a second axial centerline. The driving end portion includes an outer surface and a plurality of external splines extending radially outwardly from the outer surface with respect to the second axial centerline. The plurality of external splines is drivingly engaged with the plurality of internal splines. The plurality of internal splines or the plurality of external splines comprises bowed splines.
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 (f1) 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.
A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
An additive manufacturing apparatus includes a feed module and a take-up module that are configured to operably couple with a foil. A stage is configured to hold one or more cured layers of a resin that form a component. A radiant energy device is positioned opposite to the at least one stage. The radiant energy device is operable to generate and project radiant energy in a predetermined pattern. An actuator is configured to change a relative position of the at least one stage and the foil. An accumulator is positioned between the feed module and the take-up module. The accumulator is configured to retain an intermediate portion of the foil to allow a first portion of the foil upstream of the accumulator to move at a first speed and a second portion of the foil downstream of the accumulator to move at a second speed during a defined time period.
B29C 64/236 - Driving means for motion in a direction within the plane of a layer
B29C 64/124 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified
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
B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
B33Y 50/00 - Data acquisition or data processing for additive manufacturing
A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.
F23R 3/34 - Feeding into different combustion zones
F02C 3/20 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
An apparatus relating to a component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow. The component having a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. At least one cooling hole including a connecting passage extending from a first inlet located at the cooled surface, to a first outlet located at the heated surface, the connecting passage defining a downstream flow direction from the first inlet to the first outlet, the connecting passage comprising a metering section fluidly coupled to the first inlet and defining a metered centerline and a diffusing section, downstream of the metering section, defining a diffused centerline, and fluidly coupling the metering section to the first outlet.
The present application provides a container for use in manufacturing a metal billet from a metal powder in a hot isostatic pressing process. The container may include a top, a bottom, a wall extending between the top and the bottom, an enhanced directional consolidation feature in the wall, and a sleeve positioned about the enhanced directional consolidation feature.
A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.
Provided is a system and method that can safely generate and execute an outage plan for a power grid based on severe weather-driven events. In one example, the method may include receiving predicted or current operational power system state data from a power grid and weather conditions associated with the power grid, identifying one or more nodes on the power grid to de-energize based on the operational state data and the current weather conditions, determining a sequence of instructions to perform to de-energize the one or more identified nodes based on the operational state data and the current weather conditions associated with the power grid, and generating an outage plan including mitigation steps for ensuring the stability and security of the power grid which includes the determined sequence of instructions to be executed and store the outage plan in the memory.
H02J 3/14 - Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
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
An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.
This disclosure provides systems, methods and apparatuses for foreign object detection (FOD) in a wireless power transfer (WPT) system. Some implementations relate generally to the use of detection coils that are excited to measure and compare a differential current through a coil pair that includes at least two detection coils. A foreign object may cause a change in impedance for one or more detection coils compared to one or more other detection coils. By detecting the differential current of the coil pair, a detection apparatus may determine that a foreign object is in proximity to one of the detection coils of the coil pair. This disclosure provides several options for the design, construction, layout, and operations of detection coils to improve foreign object detection.
G01V 3/10 - Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination or deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices using induction coils
H02J 50/60 - Circuit arrangements or systems for wireless supply or distribution of electric power responsive to the presence of foreign objects, e.g. detection of living beings
A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft.
A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B60L 50/16 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with provision for separate direct mechanical propulsion
B64C 21/06 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
B64D 27/12 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, wing
B64D 27/18 - Aircraft characterised by the type or position of power plant of jet type within, or attached to, wing
F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
F02K 3/04 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type
General Electric Deutschland Holding GmbH (Germany)
Inventor
Vitt, Paul Hadley
Simonetti, Michael
Sharma, Ashish
Abstract
A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.
A system for spacing and fastening tubular structures, and a related method. The system includes a spacer element configured to engage a plurality of tubular structures, to spatially separate the plurality of tubular structures from one another, and to distribute stress in the plurality of tubular structures. The system further includes a fastening element configured to extend around at least a portion of an outer surface of the plurality of tubular structures, and to fasten the plurality of tubular structures to the spacer element in an adaptively spaced configuration.
F16L 3/22 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets specially adapted for supporting a number of parallel pipes at intervals
F16L 3/10 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing divided, i.e. with two members engaging the pipe, cable or protective tubing
F16L 3/233 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets specially adapted for supporting a number of parallel pipes at intervals for a bundle of pipes or a plurality of pipes placed side by side in contact with each other by means of a flexible band
A motorized apparatus for use in maintaining a pipe having a sidewall defining an interior cavity is provided. The motorized apparatus includes a body assembly extending along a longitudinal axis, at least one maintenance device coupled to the body assembly, and a plurality of leg assemblies coupled circumferentially around the body assembly. The motorized apparatus also includes a plurality of drive mechanisms coupled to the plurality of leg assemblies. The plurality of drive mechanisms are configured to interact with the sidewall. The plurality of drive mechanisms include at least two wheels. The plurality of drive mechanisms are arranged to move the body assembly in a first direction parallel to the longitudinal axis, move the body assembly in a second direction perpendicular to the longitudinal axis, and rotate the body assembly around the longitudinal axis.
A hybrid-electric gas turbine engine and method of operating includes independently controlling a first electric machine providing torque to a first shaft to maintain a desired clearance between a first set of blades rotatably coupled to the first shaft, and a casing.
F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
F02C 6/00 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02C 9/56 - Control of fuel supply conjointly with another control of the plant with power transmission control
53.
CLOSED-LOOP COOLING SYSTEM FOR A GAS TURBINE ENGINE
A closed-loop cooling system for a gas turbine engine, comprising: a pump having a pump inlet and a pump outlet; a first plurality of stator vanes defining first cooling cavities therein; and a second plurality of stator vanes, defining second cooling cavities therein, wherein the pump drives a working fluid from the pump outlet, through the first cooling cavities of the first plurality of stator vanes, through the cooling cavities of the second plurality of stator vanes and back to the pump inlet.
Systems and methods for high bandwidth control of thrust response for turbofan or turboprop engines are provided. Such systems and methods include an engine control system that processes a rate command and a feedback signal from an engine to generate separate fuel and electric machine control signals that respectively control fuel and electric machine dynamics of the engine to produce engine dynamics that result in desired thrust response.
Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.
F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
F01D 11/10 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
56.
MATERIAL SYSTEMS FOR REPAIR OF THERMAL BARRIER COATING AND METHODS THEREOF
Methods for repairing a thermal barrier coating deposited on a component with localized spallation of the thermal barrier coating includes depositing a primer slurry on a thermally grown oxide of the component exposed by the localized spallation, depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes at least one of a metal and a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond between the primer and the thermally grown oxide and a second chemical bond between the primer and the ceramic material.
Flow-metering fuel systems and related methods are disclosed. An example apparatus includes a pipe defining a flow path for fuel, the pipe fluidly coupled to a combustor, a first portion of the pipe having a first cross-sectional area, a second portion of the pipe having a second cross-sectional area smaller than the first cross-sectional area, the second portion downstream of the first portion, and an actuator to adjust a flow rate of the fuel in the pipe based on a first pressure of the fuel in the first portion of the pipe, a second pressure of the fuel in the second portion of the pipe, and a temperature of the fuel.
A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.
Apparatus, systems, and articles of manufacture are disclosed to dynamically support axial thrust in pumps. Examples disclosed herein include a thrust bearing system including a thrust disc coupled to an impeller shaft; a first thrust pad coupled to a body of the pump, the first thrust pad positioned on a forward side of the thrust disc; a second thrust pad coupled to the body of the pump, the second thrust pad positioned on an aft side of the thrust disc; and a spring-loaded assembly integrated into the first and second thrust pads, the spring-loaded assembly connected to a pump outlet via a first flowline, the first flowline to transmit a working fluid from the pump outlet to the forward side of the thrust disc or the aft side of the thrust disc based on a position of the spring-loaded assembly.
F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
F01D 3/04 - Machines or engines with axial-thrust balancing effected by working fluid axial thrust being compensated by thrust-balancing dummy piston or the like
F01D 15/08 - Adaptations for driving, or combinations with, pumps
60.
Gas turbine engine having a heat exchanger located in an annular duct
i), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:
1 is equal to 13,200 inches per second during the high power operating condition.
A turbine system includes a foam generating assembly having an in situ foam generating device at least partially positioned within the fluid passageway of the turbine engine, such that the in situ foam generating device is configured to generate foam within the fluid passageway of the turbine engine.
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
B01F 23/235 - Mixing gases with liquids by introducing gases into liquid media, e.g. for producing aerated liquids for making foam
B01F 25/31 - Injector mixers in conduits or tubes through which the main component flows
B01F 25/312 - Injector mixers in conduits or tubes through which the main component flows - Details thereof
B01F 25/313 - Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
B01F 25/314 - Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced at the circumference of the conduit
Hybrid composite components, such as gas turbine engine containment assemblies, a hybrid composite component having an annular composite shell and an annular metallic shell joined with the composite shell. A containment assembly including a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes a first composite shell joined with a metallic shell. The metallic shell defining a first portion of the inner surface and the first composite shell defining a second portion of the inner surface.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
63.
HEAT EXTRACTION OR RETENTION DURING DIRECTIONAL SOLIDIFICATION OF A CASTING COMPONENT
A method of forming a directionally-solidified casting component using a casting system is provided. The casting system includes a chamber having a heating zone and a cooling zone separated by a baffle plate. The method includes pouring an alloy in a liquid state into a mold shell. The mold shell is positioned on a chill plate within the heating zone. The method further includes moving the mold shell from the heating zone into the cooling zone. The alloy transfers from the liquid state to a solid state within the mold shell while moving the mold shell from the heating zone to the cooling zone. The method further includes contacting the mold shell with a heat transfer member.
The present disclosure generally relates to methods and apparatuses for chemical vapor deposition (CVD) during additive manufacturing (AM) processes. Such methods and apparatuses can be used to embed chemical signatures into manufactured objects, and such embedded chemical signatures may find use in anti-counterfeiting operations and in manufacture of objects with multiple materials.
C23C 16/50 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating using electric discharges
B22F 7/02 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers
B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
B22F 10/14 - Formation of a green body by jetting of binder onto a bed of metal powder
B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B22F 10/50 - Treatment of workpieces or articles during build-up, e.g. treatments applied to fused layers during build-up
B22F 10/62 - Treatment of workpieces or articles after build-up by chemical means
B28B 1/00 - Producing shaped articles from the material
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
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
B29C 64/20 - 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
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
B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/52 - Controlling or regulating the coating process
A sensor for a flexible sensor assembly includes a drive coil, a first set of sensing coils, a second set of sensing coils, and a configuration for sensing for discontinuities in a structure desired to be sensed. A method of operating the sensor can include positioning the sensor proximate to the structure, energizing the drive coil, and sensing eddy currents with the sensing coils.
G01N 27/90 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.
A ducted fan engine is deiced using a ground support deicing apparatus having a support structure, a plurality of sonic wave transmitters, an imaging device, and a controller that controls the sonic wave transmitters to emit sonic waves at varying frequencies. A deicing program causes the controller to control (a) providing imaging signals to obtain image data from imaging sensors, (b) receiving image data provided by each of the imaging sensors, and generates images of at least one component part of the engine, (c) detecting a presence or an absence of ice on the at least one component part of the engine, and (d) controlling the plurality of sonic wave transmitters to emit sonic waves in a given frequency range so as to remove the ice from the component part of the engine.
B08B 7/02 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass by distortion, beating, or vibration of the surface to be cleaned
B08B 13/00 - Accessories or details of general applicability for machines or apparatus for cleaning
A gas turbine engine is provided. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement; and an air-to-air heat exchanger having an air-to-air heat exchanger potential defined by a product raised to a half power, the product being an effectiveness associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine, and wherein the air-to-air heat exchanger potential is between 0.028 and 0.067 for a bypass ratio associated with the gas turbine engine between 3 and 10 and the effectiveness being between 0.5 and 0.9 and is between 0.015 and 0.038 for a bypass ratio associated with the gas turbine engine between 10 and 20 and the effectiveness being between 0.3 and 0.9.
General Electric Deutschland Holding GmbH (Germany)
Inventor
Huh, Kum Kang
Osama, Mohamed
Abstract
An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.
B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
B60L 50/13 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines using AC generators and AC motors
B64D 27/18 - Aircraft characterised by the type or position of power plant of jet type within, or attached to, wing
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
Methods for reducing a concentration of hexavalent chromium within a first aluminum slurry by adding a reducing agent to form a second aluminum slurry are provided. The reducing agent causes a chemical reduction reaction with the hexavalent chromium compound of the first aluminum slurry to form a trivalent chromium compound within the second aluminum slurry such that a first weight ratio of hexavalent chromium to trivalent chromium in the first aluminum slurry is decreased to a second weight ratio of hexavalent chromium to trivalent chromium in the second aluminum slurry, with the second weight ratio being less than the first weight ratio.
B22F 9/18 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using chemical processes with reduction of metal compounds
B22F 1/145 - Chemical treatment, e.g. passivation or decarburisation
71.
GAS CONTROL SYSTEMS FOR PURGING A PRINTHEAD MANUFACTURING APPARATUS
A gas control system including a positive pressure vessel, a negative pressure vessel, a first pressure control valve configured to control a flow of gas to and from a first manifold of a printhead assembly, and a second pressure control valve configured to control a flow of gas to and from a second manifold of the printhead assembly. During a normal positive pressure mode, gas flows from the positive pressure vessel to the first manifold and the second manifold through a respective one of the first pressure control valve and the second pressure control valve. During a positive pressure purge mode, gas from the positive pressure vessel bypasses the first pressure control valve and the second pressure control valve to flow to the first manifold and the second manifold.
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
B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
72.
ICE PROTECTION SYSTEMS FOR AIRCRAFT FUELED BY HYDROGEN
A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.
A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.
An apparatus and method for an inspection apparatus for inspecting a component. The inspection apparatus including a robotic arm. A micro-XRF instrument having an instrument head coupled to the robotic arm. A seat supporting the component within a scanning area during inspection; and a computer in communication with the robotic arm and the micro-XRF instrument.
G01N 23/223 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by measuring secondary emission from the material by irradiating the sample with X-rays or gamma-rays and by measuring X-ray fluorescence
G01N 35/00 - Automatic analysis not limited to methods or materials provided for in any single one of groups ; Handling materials therefor
An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells each extending between an inlet end and an outlet end. Each fuel cell of the plurality of fuel cells includes an air channel and a fuel channel each fluidly coupled to the combustion chamber.
A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure having a plurality of first-dome vortex driver airflow openings for providing a first vortex generating mid airflow therethrough to a trapped vortex cavity. A second dome structure is arranged downstream of the first dome structure and includes a plurality of second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, and a plurality of primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity.
F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
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
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.
Active clearance control valves and related methods are disclosed. An example apparatus includes a pipe defining a flow path between (i) at least one of a fan section, a bypass airflow passage, or a compressor section and (ii) a turbine section of the gas turbine, the pipe including an inlet fluidly coupled to at least one of the fan section, the bypass airflow passage, or the compressor section, a valve coupled to the pipe and positioned downstream of the inlet, the valve including swing wings, the swing wings positioned around an opening in the pipe defined by the second valve when the second valve is at least partially open.
A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.
A power generation system for an aircraft includes a first power source, a second power source, and a power dispatch module communicatively coupled with the first and second power sources. The power dispatch module includes a controller having one or more processors configured to perform a plurality of operations, including but not limited to receiving a plurality of loading data associated with the power generation system, predicting a future power demand due to future load changes using the loading data, determining first and second power setpoints for the first and second power sources, respectively, based on the future power demand due to the future load changes, and controlling first and second power outputs of the first and second power sources based on the first and second power setpoints such that the future power demand of the power generation system is shared by the first and second power sources.
A method of producing a computer-generated image of a component part includes receiving scan data of the component part. The scan data includes a plurality of slices that change direction about a normal vector. The method further includes registering the scan data of the component part and transforming the scan data of the component part into a set of slices arranged in an x-y plane. Further, the method includes aligning the set of slices aligned along the axis along an axis in the x-y plane. In addition, the method includes adjusting the set of slices aligned along the axis using a background model for the component part, the scan data, or both. Thus, the method includes applying a directional filter to the set of slices aligned along the axis and generating the computer-generated image of the component part using the filtered set of slices aligned along the axis.
A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
(
D
1
eq
min
D
2
eq
min
)
(
R
D
2
eq
min
)
.
Methods, apparatus, systems, and articles of manufacture are disclosed. An example apparatus includes a tubular or cylindrical body including a shaft, a shoulder, and a neck, the shaft coupled to the shoulder, the shoulder coupled to the neck, the shoulder having a greater diameter than respective diameters of the shaft and the neck. The example apparatus includes a plug coupled to the shoulder at a first plug edge and coupled to a first fastener at a second plug edge, the first fastener including a hole. The example apparatus includes a second fastener coupled to the first fastener, the second fastener extending through the tubular body, the plug, and the first fastener.
Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.
B64D 27/26 - Aircraft characterised by construction of power-plant mounting
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
86.
PITCH CHANGE MECHANISM FOR A FAN OF A GAS TURBINE ENGINE
A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.
The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
B22D 25/02 - Special casting characterised by the nature of the product of works of art
B22C 1/22 - 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 of organic agents of resins or rosins
B22C 9/02 - Sand moulds or like moulds for shaped castings
B22C 9/10 - Cores; Manufacture or installation of cores
B22C 9/12 - Treating moulds or cores, e.g. drying, hardening
B22C 9/24 - Moulds for peculiarly-shaped castings for hollow articles
B22C 13/08 - Moulding machines for making moulds or cores of particular shapes for shell moulds or shell cores
B22C 13/12 - Moulding machines for making moulds or cores of particular shapes for cores
B22C 21/14 - Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
B22D 29/00 - Removing castings from moulds, not restricted to casting processes covered by a single main group; Removing cores; Handling ingots
B28B 1/00 - Producing shaped articles from the material
B29C 64/124 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified
B29C 64/129 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified characterised by the energy source therefor, e.g. by global irradiation combined with a mask
B29C 64/135 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified characterised by the energy source therefor, e.g. by global irradiation combined with a mask the energy source being concentrated, e.g. scanning lasers or focused light sources
F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
G03F 7/00 - Photomechanical, e.g. photolithographic, production of textured or patterned surfaces, e.g. printed surfaces; Materials therefor, e.g. comprising photoresists; Apparatus specially adapted therefor
An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.
Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.
Methods, apparatus, systems, and articles of manufacture are disclosed herein that include a cryogenic pump system comprising: a cryogenic liquid tank; a cryogenic pump including a suction adapter, the suction adapter connected to the cryogenic liquid tank via a liquid supply line and a gaseous return line; and a phase separator connected downstream of the cryogenic liquid tank and upstream of the cryogenic pump, the phase separator including a filtration structure integrated into the liquid supply line to separate vapor from cryogenic liquid, the phase separator connected to the gaseous return line to direct the vapor to the cryogenic liquid tank.
A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.
F02K 3/08 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
A fuel cell assembly includes a plurality of fuel cells. The fuel cell includes a bipolar separator plate disposed between each fuel cell of the plurality of fuel cells. The bipolar separator plate includes one or more fuel cell sub-units each comprising a plurality of unit-cells. Each unit-cell in the plurality of unit-cells has an outer surface and defines an internal volume that extends in multiple directions between a plurality of openings defined on the outer surface. Each unit-cell in the plurality of unit-cells is disposed adjacent to a neighboring unit-cell in the plurality of unit-cells such that the plurality of unit-cells collectively define one or more channels.
H01M 8/0258 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
H01M 8/0267 - Collectors; Separators, e.g. bipolar separators; Interconnectors having heating or cooling means, e.g. heaters or coolant flow channels
H01M 8/0247 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the form
H01M 8/2483 - Grouping of fuel cells, e.g. stacking of fuel cells - Details of groupings of fuel cells characterised by internal manifolds
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04014 - Heat exchange using gaseous fluids; Heat exchange by combustion of reactants
A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
A cascade thrust reverser assembly is provided for a turbofan engine. The turbofan engine includes a nacelle assembly defining a bypass passage, and the cascade thrust reverser assembly includes at least one cascade assembly configured to be at least partially enclosed by the nacelle assembly. The cascade assembly may further include a plurality of cascade segments and an actuation assembly operably connected to the plurality of cascade segments, wherein the actuation assembly is configured to increase an axial extent of the cascade assembly and rotate the plurality of cascade segments.
F02K 1/76 - Control or regulation of thrust reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
A joined part comprises a first portion and a second portion. The first portion comprises a guide slot at least partially defined by a porous structure. A joint material is disposed within the porous structure. The second portion is disposed within the guide slot and contacts the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion. A method of manufacturing the joined part includes disposing a joint material into a porous structure of a guide slot of a first portion, inserting a second portion into the guide slot, and contacting the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion.
B23K 20/00 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
B23K 35/00 - Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
B23K 35/36 - Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest
C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
96.
CLEANING SOLUTION AND METHODS OF CLEANING A TURBINE ENGINE
A cleaning solution for a turbine engine includes water; a first organic acidic component that comprises citric acid; a second organic acidic component that comprises glycolic acid; isopropylamine sulphonate; alcohol ethoxylate; triethanol amine; and sodium lauriminodipropionate. The cleaning solution has a pH value between about 2.5 and about 7.0.
An additive manufacturing apparatus includes a support plate defining a window and a resin support configured to support an uncured layer of resin. A stage is configured to hold one or more cured layers of the resin to form a component positioned opposite a support plate. A radiant energy device is positioned on an opposite side of the resin support from the stage and is operable to project radiant energy in a grid through the window. The grid and/or pixels thereof are intelligently shifted to efficiently print one or more layers of a component.
B29C 64/124 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B29C 64/282 - Arrangements for irradiation using multiple radiation means, e.g. micromirrors or multiple light-emitting diodes [LED] of the same type, e.g. using different energy levels
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
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
An additive manufacturing apparatus includes a stage configured to hold a component. A radiant energy device is operable to generate and project radiant energy in a patterned image. An actuator is configured to change a relative position of the stage relative to the radiant energy device. A resin management system includes a material deposition assembly upstream configured to deposit a resin on a resin support. The material deposition assembly includes a reservoir configured to retain a first volume of the resin and define a thickness of the resin on the resin support as the resin support is translated in an X-axis direction. The material deposition assembly further includes a vessel positioned above the reservoir in a Z-axis direction and configured to store a second volume of the resin. In addition, the material deposition assembly includes a conduit configured to direct the resin from the vessel to the reservoir.
B29C 64/124 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using layers of liquid which are selectively solidified
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
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
A turbofan engine is provided. The turbofan engine includes a low pressure spool; a fan mechanically coupled with the low pressure spool; a high pressure spool; an accessory gearbox mechanically coupled with the high pressure spool; a hydraulic pump mechanically coupled with the accessory gearbox; and one or more heat exchangers tied to the accessory gearbox, the one or more heat exchangers having a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying an average heat exchanger effectiveness of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a hydraulic pump power of the hydraulic pump, a fan diameter of the fan, an engine length of the turbofan engine, and an overall pressure ratio of the turbofan engine.
patents
