Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an atomization system performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
• B01D 1/00 - Evaporating
• B01D 1/18 - Evaporating by spraying to obtain dry solids
• G01H 17/00 - Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the other groups of this subclass

Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a cold spray system performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• G01N 29/44 - Processing the detected response signal
• B33Y 50/00 - Data acquisition or data processing for additive manufacturing
• C23C 24/04 - Impact or kinetic deposition of particles

Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an additive manufacturing system performing a process possessing a plurality of process attributes. The process includes depositing material by interaction of an energy beam and a material stream on a build target to form a structure. The system includes a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may further include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• B29C 64/386 - Data acquisition or data processing for additive manufacturing
• B29C 64/209 - HeadsNozzles
• B29C 64/268 - Arrangements for irradiation using laser beamsArrangements for irradiation using electron beams [EB]
• B29C 64/321 - Feeding
• B33Y 50/00 - Data acquisition or data processing for additive manufacturing

Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a system performing a fluid transport process possessing a plurality of process attributes. The fluid transport process may include a flow of a fluid along at least one path. The system may further include a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• G01N 29/024 - Analysing fluids by measuring propagation velocity or propagation time of acoustic waves
• G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis

Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an engine performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• G01N 29/44 - Processing the detected response signal
• F02D 41/22 - Safety or indicating devices for abnormal conditions

Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a system performing a powder transport process possessing a plurality of process attributes. The powder transport process may include a flow of a powder stream along at least one path. The system may further include a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• G01N 29/44 - Processing the detected response signal

Abstract

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an nuclear power plant performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

IPC Classes  ?

• G01N 29/14 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object using acoustic emission techniques
• G01N 29/34 - Generating the ultrasonic, sonic or infrasonic waves
• G01N 29/44 - Processing the detected response signal
• G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis

Abstract

A system includes a hydrogen fuel delivery system for an engine that pumps hydrogen from a tank in a liquid state and an evaporator configured to convert at least some of the hydrogen to a gaseous state. The system includes a heat source thermally coupled with the system and fluidly uncoupled from the system. The system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen. The system further includes a coolant loop that circulates coolant between the heat source and the evaporator. The coolant loops includes a valve that splits the coolant flowing from the evaporator into a first portion that flows to a heater and a second portion that flows to the heat source. The first and second portions are directed to the evaporator after having passed through the heater and the heat source.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 7/22 - Fuel supply systems
• F02C 7/224 - Heating fuel before feeding to the burner

Abstract

A method includes creating a first image of a software system, creating a second image of the software system including a second code level layout different than the first code level layout, verifying and validating the first and second images of the software system, certifying the first and second images, deploying the first image of the software system on a first operating system, and automatically detecting a first cyberattack being executed on the first image of the software system operating in the first operating system. In response to detecting the first cyberattack being executed on the first image of the software system operating on the first operating system, deploying the second image of the software system on the first operating system in order to disrupt the first cyberattack on the first image of the software system.

IPC Classes  ?

• G06F 21/55 - Detecting local intrusion or implementing counter-measures
• G06F 16/11 - File system administration, e.g. details of archiving or snapshots
• G06F 21/64 - Protecting data integrity, e.g. using checksums, certificates or signatures

Abstract

The present disclosure teaches a turbine-powered system with a thermoelectric cooler configured to selectively cool powered electronics in the system. In examples provided, the thermoelectric cooler including a cooling plate coupled to the powered electronics and a heat sink integrated into aero surfaces of a gas turbine engine.

IPC Classes  ?

• F01D 25/12 - Cooling

Abstract

A vane assembly adapted for a gas turbine engine includes a first vane segment that extends circumferentially about an axis and a second vane segment. The second vane segment includes a band that extends circumferentially about the axis and a plurality of vanes coupled to the band and extending radially from the band.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A thermal system includes a tank storing a cooling fluid in a liquid state and a gas state, a first heat exchanger releasing heat into the tank, a second heat exchanger fluidly downstream of the fluid storage tank and exchanging heat between the cooling fluid and a heat load, a turbine fluidly downstream of the second heat exchanger and extracting mechanical energy from the cooling fluid, and a combustor fluidly upstream of the turbine and fluidly downstream of the second heat exchanger. The cooling fluid that has been heated by the second heat exchanger passes through the first heat exchanger and thereby heats upstream cooling fluid resident in the fluid storage tank, and the combustor is configured to ignite the cooling fluid flowing from the second heat exchanger such that combusted cooling fluid flows through and drives the turbine.

IPC Classes  ?

• F01K 25/10 - Plants or engines characterised by use of special working fluids, not otherwise provided forPlants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
• F01K 3/02 - Use of accumulators and specific engine typesControl thereof
• F01K 3/16 - Mutual arrangement of accumulator and heater
• F01K 9/02 - Arrangements or modifications of condensate or air pumps
• F01K 27/00 - Plants for converting heat or fluid energy into mechanical energy, not otherwise provided for
• F17C 7/04 - Discharging liquefied gases with change of state, e.g. vaporisation

Abstract

A vane assembly includes an outer case, a plurality of vanes, and an inner body assembly. The outer case defines an outer boundary of a flow path of the vane assembly. The plurality of vanes extend radially inward from the outer case relative to a central axis. The inner body assembly is configured to secure the plurality of vanes radially relative to the central axis. The inner body assembly includes an inner case arranged circumferentially about the central axis, a band coupled with the inner case, and a retainer ring that extends into the band and into each of the plurality of vanes.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

An airfoil adapted for use in a gas turbine engine includes a base and an airfoil body that extends radially outward from the base relative to an axis to a tip of the airfoil body. The airfoil body has a leading edge, a trailing edge, a suction side, and a pressure side. The airfoil body is formed to include notches that extend into the airfoil body to reduce a weight of the airfoil.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

A multi-piece radial turbine rotor includes a hub, turbine blades, and a flowpath ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

IPC Classes  ?

• F01D 5/04 - Blade-carrying members, e.g. rotors for radial-flow machines or engines
• B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 5/08 - Heating, heat-insulating, or cooling means
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.

IPC Classes  ?

• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
• B60L 50/52 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells characterised by DC-motors
• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 11/33 - Drive circuits, e.g. power electronics

Abstract

A power-generation system includes an electrical system, a turbine engine, and a pump. The turbine engine includes a compressor configured to receive and compress a working fluid, a heat source that transfers heat to the compressed working fluid, a turbine fluidly connected with the compressor to extract work from the heated working fluid, and a first heat-exchanger fluidly connected with the turbine to transfer heat away from the heated working fluid to provide a cooled working fluid. The pump conducts a portion of the cooled working fluid from the first heat-exchanger to the electrical system to cool components of the electrical system.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 9/10 - Arrangements for cooling or ventilating by gaseous cooling medium flowing in closed circuit, a part of which is external to the machine casing

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• 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
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F04D 29/58 - CoolingHeatingDiminishing heat transfer

Abstract

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

IPC Classes  ?

• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
• F01D 17/12 - Final actuators arranged in stator parts
• F02C 9/16 - Control of working fluid flow
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• F04D 29/52 - CasingsConnections for working fluid for axial pumps

Abstract

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine. The exhaust nozzle includes a thrust reverser configured to be retained by the inner plug.

IPC Classes  ?

• F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• F02K 1/76 - Control or regulation of thrust reversers

Abstract

A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 7/22 - Fuel supply systems
• F02C 7/224 - Heating fuel before feeding to the burner

Abstract

Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section includes a low pressure turbine that drives a low pressure spool that rotates about a longitudinal axis of the turbine engine, a high pressure turbine that drives a high pressure spool, and a compressor rotated by the high pressure spool. The fan is connected to the low pressure spool and rotated by the low pressure spool. Rotation of the fan may provide thrust to a vehicle that includes the turbine engine. The electrical generator is positioned between the fan and the compressor. The electrical generator comprises a rotor concentric with and rotated via the low pressure spool, the rotor configured to rotate about the longitudinal axis, and a stator positioned radially within the rotor and configured to electromagnetically interact with the rotor to generate power.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage

Abstract

A gas turbine engine includes a combustor and a valve coupled to the combustor. The valve includes a valve body, a valve stem, and an actuator. The valve body is formed to define an air chamber. The valve stem is movable between a closed position and an open position. The actuator is configured to move selectively the valve stem between the closed position and the open position.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor

Abstract

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include a dovetail shape retention features for coupling the ceramic matrix composite turbine blades to a central hub.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include an axially-extending lug features for coupling the ceramic matrix composite turbine blades to a central hub.

IPC Classes  ?

• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 5/04 - Blade-carrying members, e.g. rotors for radial-flow machines or engines
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section comprises at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine, wherein the at least one turbine drives at least one spool, and an oil sump positioned to collect oil used to lubricate rotational elements for one or more of the at least one compressor and the at least one turbine. The fan rotated by the at least one spool. The electrical generator integrated into the core section and positioned outside of the oil sump, wherein the electrical generator comprises a rotor rotated via the at least one spool about the longitudinal axis, and a stator configured to electromagnetically interact with the rotor to generate power.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 21/22 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating around the armatures, e.g. flywheel magnetos

Abstract

An example electric machine includes a rotor and a stator. The stator includes a stator core defining a longitudinal axis and a plurality of stator end windings extending from the stator core along the longitudinal axis. Adjacent end windings of the plurality of stator end windings define a radial gap, and the radial gap is configured to allow a cooling fluid to flow within the radial gap and in contact with the adjacent stator end windings.

IPC Classes  ?

• H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
• H02K 15/08 - Forming windings by laying conductors into or around core parts

Abstract

An example electric machine of a gas-turbine engine includes a stator; a rotor configured to rotate around the stator, the rotor comprising: a rotor body having an inner surface and an outer surface; magnets on the inner surface of the rotor body, the magnets having an inner surface and an outer surface; and a retention band on the inner surface of the magnets and configured to retain the magnets to the rotor body.

IPC Classes  ?

• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 1/2791 - Surface mounted magnetsInset magnets

Abstract

A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and one or more shims located between the valve housing and the piston.

IPC Classes  ?

• F04D 27/02 - Surge control

Abstract

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and a tip clearance system. The tip clearance system includes a tip clearance sensor located in an annular plenum defined between an inner case and an outer case included in the case assembly. The tip sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

IPC Classes  ?

• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components
• F01D 17/02 - Arrangement of sensing elements
• G01B 21/16 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance or clearance between spaced objects

Abstract

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a axis, a second ring arranged circumferentially around the axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

IPC Classes  ?

• F02K 1/82 - Jet pipe walls, e.g. liners

Abstract

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an actively-cooled tip clearance system. The tip clearance system includes a tip clearance sensor located radially outward of an inner case of the case assembly. The actively-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

IPC Classes  ?

• F01D 11/20 - Actively adjusting tip-clearance
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

A vortex particle separator adapted for use with a gas turbine engine includes a vortex tube, a plurality of swirl vanes, and an outlet tube. The vortex tube receives atmospheric air laden with particles. The plurality of swirl vanes are arranged within the vortex tube and separate the atmospheric air into a first flow of air having the particles and a second flow of air that is relatively free of the particles. The outlet tube extends into the vortex tube to define a scavenge passageway between the outlet tube and the vortex tube that receives the first flow of air. The outlet tube defines an intake passageway that receives the second flow of air. The vortex particle separator further includes a layer of material having a low coefficient of restitution on at least one of an interior surface of the vortex tube and a surface of the swirl vanes.

IPC Classes  ?

• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
• B01D 45/16 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by the winding course of the gas stream
• B04C 3/00 - Apparatus in which the axial direction of the vortex remains unchanged

Abstract

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

IPC Classes  ?

• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 17/12 - Final actuators arranged in stator parts
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Abstract

A stator housing assembly includes a stator housing and a stator sleeve. The stator sleeve including a combination of composite layers with different high strength fibers. The stator housing includes a first end section and a second end section that define a stator cavity configured to contain a pressurized cooling fluid. The stator sleeve defines a longitudinal axis and includes a plurality of layers of composite materials that include more than one high strength fiber material. High strength fibers may include carbon and glass fibers. Portions of the stator sleeve may have different combinations of high strength fiber materials and fiber orientations to optimize sleeve properties.

IPC Classes  ?

• H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
• F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
• H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
• H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 15/12 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines

Abstract

A cooling system may comprise a vapor cycle system. The cooling system may comprise a gas turbine engine. The vapor cycle system may include a compressor, a heat exchanger downstream from the compressor, and a heat load downstream from the heat exchanger and upstream of the compressor. The cooling system may comprise a bleed air conduit. The bleed air conduit may be configured to receive bleed air from the gas turbine engine. The cooling system may comprise a bleed turbine driven by the bleed air supplied from the bleed air conduit. The bleed turbine may be configured to drive the compressor of the vapor cycle system. The compressor may be connected to a bleed turbine via a shaft. The cooling system may comprise a throttle valve to control a flow of the bleed air through the bleed air conduit.

IPC Classes  ?

• F02C 7/12 - Cooling of plants
• 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
• 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

Abstract

An example propulsion engine includes at least one radial support structure (RSS) radially disposed about an engine centerline. A power cable is at least partially contained within a cavity of a first RSS or a cavity fluidically coupled to the cavity of the first RSS. The first RSS defines at least one cooling aperture fluidically coupling the cavity of the first RSS to an exterior surface of the first RSS. The at least one cooling aperture is configured to allow cooling fluid to flow into or out of the cavity of the first RSS to cool the power cable.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F02C 7/12 - Cooling of plants
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• H01B 7/42 - Insulated conductors or cables characterised by their form with arrangements for heat dissipation or conduction
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H05K 9/00 - Screening of apparatus or components against electric or magnetic fields
• F01D 25/12 - Cooling
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• F02C 7/20 - Mounting or supporting of plantAccommodating heat expansion or creep
• H01B 9/00 - Power cables

Abstract

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include a dovetail shape retention features for coupling the ceramic matrix composite turbine blades to a central hub.

IPC Classes  ?

• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A method of monitoring a fuel system in a gas turbine engine. The method may comprise pumping fuel to a combustor from a fuel tank with a pump. The method may comprise controlling a flow of the fuel to the combustor with a metering valve disposed downstream of the pump and closing a spill valve disposed downstream of the pump, wherein the spill valve is closed in fixed increments and closing the spill valve increases a pressure in the fuel system. The method may comprise opening a pressure valve in response to the pressure in the fuel system being equal to or greater than a predetermined value, and capturing a degree of closing of the spill valve when the pressure valve opens.

IPC Classes  ?

• F02C 9/26 - Control of fuel supply
• F02C 7/22 - Fuel supply systems
• F02C 7/26 - StartingIgnition
• F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed

Abstract

A method of mitigating uncommanded or uncontrollable high thrust in a gas turbine engine is provided. The method may comprise pumping fuel to a combustor from a fuel tank, controlling a flow rate of the fuel to the combustor with a metering valve, spilling a portion of the fuel pumped by the pump with a primary spill valve, controlling a pressure of the fuel flowing to the combustor via a pressure valve, detecting a pressure differential across the pressure valve with a pressure transducer, determining the flow rate of the fuel based on the detected pressure differential and the positional feedback of the pressure valve opening, comparing the determined flow rate with a demand flow rate, and opening a secondary spill valve when the determined flow rate exceeds the demand flow rate.

IPC Classes  ?

• F02C 9/26 - Control of fuel supply
• F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
• F02C 7/22 - Fuel supply systems

Abstract

A gas turbine engine includes a bypass duct, a rotating detonation augmentor, and a flow valve. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase thrust for propelling the gas turbine engine. The flow valve is configured to vary selectively the portion of the air flowing into the rotating detonation augmentor to control a magnitude of the thrust increase provided by the rotating detonation augmentor during operation of the rotating detonation augmentor.

IPC Classes  ?

• F02K 3/02 - 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

Abstract

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.

IPC Classes  ?

• F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• F02K 1/76 - Control or regulation of thrust reversers

Abstract

A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight is located in a space radially between the first rotor and the second rotor.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors

Abstract

Various aspects of the techniques are directed to a turbine engine that includes a core section comprising a compressor and a turbine that both rotate about a longitudinal axis of the turbine engine. The turbine engine also includes a fan comprising radially distributed blades, the fan connected to the core section and configured to be rotated by the turbine, and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor. The electrical generator comprises a stator, a turbine configured to extract work from a core fluid flow, the turbine configured to rotate about the longitudinal axis, and a combined rotor rotationally coupled to the fan, the combined rotor formed from a single component that incorporates a blade retainer for retaining at least one of the plurality of radially distributed blades.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

A gas turbine engine includes a bypass duct including an outer wall, a flow wall arranged within the bypass duct so as to bifurcate a flow path of the bypass duct into radially outer and inner flow paths, and a heat exchanger. The outer wall includes a segmented wall portion that is removable from the outer wall. The heat exchanger is arranged within the radially outer flow path and is coupled to the segmented wall portion such that the heat exchanger is configured to be removed from the bypass duct via removal of the segmented wall portion from the outer wall.

IPC Classes  ?

• F02C 7/12 - Cooling of plants
• 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

Abstract

A heat-exchanger assembly includes a shroud, a heat exchanger, and a mounting system. The shroud is configured to direct a flow of air through the heat-exchanger assembly. The heat exchanger is configured to transfer heat. The mounting system is configured to couple the shroud with the heat exchanger.

IPC Classes  ?

• F01D 25/12 - Cooling
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

A gas turbine engine includes a bypass duct and a heat-exchanger assembly. The bypass duct is configured to direct air through a flow path. The heat-exchanger assembly is configured to receive a first portion of the air flowing through the flow path of the bypass duct and to divert a second portion of the air flowing through the flow path around the heat-exchanger assembly.

IPC Classes  ?

• F01D 25/14 - Casings modified therefor
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A gas turbine engine including an auxiliary compressor for pressuring cooling air delivered to turbine section components is disclosed. The auxiliary compressor is configured to increase the pressure of compressed air received from a primary compressor prior to movement of the compressed air to cooling air passageways of the turbine system.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

A method of monitoring a health of a temperature system may comprise selecting a temperature sensor of a plurality of temperature sensors arranged in an array, where each temperature sensor corresponds to an address within the array. The method may comprise identifying the address corresponding to the single temperature sensor, sending the address to a multiplexer, and selecting the single temperature sensor using the identified address. The method may comprise testing the selected single temperature sensor calculating an average temperature detected by the plurality of temperatures sensors.

IPC Classes  ?

• G01J 5/90 - Testing, inspecting or checking operation of radiation pyrometers
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• F01D 21/12 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to temperature
• G01J 5/00 - Radiation pyrometry, e.g. infrared or optical thermometry
• G01J 5/14 - Electrical features thereof

Abstract

A system for detecting a failure in a thermocouple array may comprise the thermocouple array. The thermocouple array may comprise a plurality of thermocouples. The system may comprise an impedance determination circuit. The impedance determination circuit may include a capacitor that has a capacitance equal to an expected capacitance of one of the plurality of thermocouples. The one of the plurality of thermocouples may be connected to test nodes of the impedance determination circuit. The system may comprise a comparator circuit connected to the impedance determination circuit, where the comparator circuit includes an amplifier and a comparator. The system may comprise an excitation circuit connected to the impedance determination circuit, where the excitation circuit includes a waveform generator and an amplifier.

IPC Classes  ?

• G01K 15/00 - Testing or calibrating of thermometers
• G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples

Abstract

A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly.

IPC Classes  ?

• F02K 3/075 - 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 controlling flow ratio between flows

Abstract

A gas turbine engine includes a bypass duct, an inlet cowl, and a heat-exchanger assembly. The bypass duct is configured to direct air through a flow path to provide thrust to propel the gas turbine engine. The inlet cowl is located in the bypass duct and configured to collect a portion of the air flowing in the bypass duct. The heat-exchanger assembly is removably coupled with the inlet cowl and configured to receive the portion of the air from the inlet cowl.

IPC Classes  ?

• F02C 7/28 - Arrangement of seals
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A gas turbine engine includes a bypass duct including an outer wall, a heat exchanger arranged within the bypass duct, and a turnbuckle assembly. The outer wall includes a main body and an access panel removably coupled to the main body. The turnbuckle assembly couples the heat exchanger to the access panel, and includes a first rod coupled to the access panel and a second rod coupled to the first rod and to the heat exchanger. The outer end of the first rod is threadably received in a socket of a socket housing removably coupled to the access panel such that the first rod is fixedly coupled to the socket housing to increase lateral stiffness of the heat exchanger and the turnbuckle assembly such that the lateral dynamic mode is outside of a fan rotor operating range.

IPC Classes  ?

• F02C 7/20 - Mounting or supporting of plantAccommodating heat expansion or creep
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A gas turbine engine includes a heat exchanger and an inlet shroud. The heat exchanger is configured to transfer heat. The inlet shroud is configured to be coupled with the heat exchanger upstream of the heat exchanger.

IPC Classes  ?

• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid

Abstract

A method of assembling a radial turbine rotor includes manufacturing turbine blades, a flowpath ring, and a hub. The method includes fixing the turbine blades circumferentially around the flowpath ring by a blade joint between the turbine blades and the flowpath ring to form a ring assembly. The method includes spinning the hub and moving the hub into engagement with the flowpath ring to locate the hub radially inwardly of the flowpath ring and to form a hub joint between the flowpath ring and the hub.

IPC Classes  ?

• B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 5/04 - Blade-carrying members, e.g. rotors for radial-flow machines or engines
• F01D 5/08 - Heating, heat-insulating, or cooling means
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

IPC Classes  ?

• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F04D 27/02 - Surge control
• F04D 29/52 - CasingsConnections for working fluid for axial pumps

Abstract

A system includes a gas turbine engine configured to provide propulsion to an aircraft and a starter system configured to start the gas turbine engine. The starter system comprises a motor controller and a closed-loop cooling system configured to cool the motor controller during an emergency in-flight restart operation of the gas turbine engine. The closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid. The cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine.

IPC Classes  ?

• F02C 7/262 - Restarting after flame-out
• F02C 7/12 - Cooling of plants

Abstract

An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising: a first air-turbine starter, the first air-turbine starter configured to rotate a spool of the first gas-turbine engine; and a first electric starter, the first electric starter configured to rotate the spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, during a time period, the first-air turbine starter and the first electric starter to start the first gas-turbine engine while the aircraft is on the ground; measure, during the time period, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.

IPC Classes  ?

• F02C 7/262 - Restarting after flame-out
• F02C 7/275 - Mechanical drives

Abstract

A starting apparatus for a gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes a fuel supply system, a combustor, and a controller. The controller is configured to cause fuel to be introduced to the combustor of the gas turbine engine at a first threshold rotational speed of the gas-turbine engine during a normal starting operation in which the aircraft is on the ground. The controller is configured to cause fuel to be introduced to the combustor at a second threshold rotational speed of the gas-turbine engine during an emergency in-flight restarting operation in which the aircraft is in-flight. The second threshold rotational speed is lower than the first threshold rotational speed. Introducing fuel at the second threshold rotational speed results in a higher temperature in a turbine of the gas turbine engine than introducing fuel at the first threshold rotational speed.

IPC Classes  ?

• F02C 7/26 - StartingIgnition
• F02C 9/46 - Emergency fuel control

Abstract

A starting apparatus for a first gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes an air turbine starter, an electric machine, and a controller. The controller is configured to receive an emergency restart command for the first gas turbine engine while the aircraft is in-flight, determine whether the first gas turbine engine is in operation, determine whether at least a second gas turbine engine of the plurality of gas turbine engines is in operation, and, responsive to receiving the emergency restart command and determining that at least the second gas turbine engine of the plurality of gas turbine engines is in operation and that the first gas turbine engine is not in operation, perform an emergency restart of the first gas turbine engine.

IPC Classes  ?

• F02C 7/26 - StartingIgnition

Abstract

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

IPC Classes  ?

• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F02C 9/16 - Control of working fluid flow
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F04D 29/52 - CasingsConnections for working fluid for axial pumps

Abstract

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

IPC Classes  ?

• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• F04D 29/52 - CasingsConnections for working fluid for axial pumps

Abstract

A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.

IPC Classes  ?

• F01D 25/02 - De-icing means for engines having icing phenomena
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F02C 7/047 - Heating to prevent icing

Abstract

A gas turbine engine includes a bypass duct, a heat exchanger, and an inlet shroud. The bypass duct is configured to direct air through a flow path. The heat exchanger is configured to receive a portion of the air flowing through the flow path of the bypass duct. The inlet shroud is coupled with the heat exchanger and configured to adjust a direction of the portion of the air entering the heat exchanger.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F01D 25/12 - Cooling
• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
• 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

Abstract

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a central axis, a second ring arranged circumferentially around the central axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

IPC Classes  ?

• F02K 1/82 - Jet pipe walls, e.g. liners

Abstract

An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising a first electric starter, the first electric starter configured to rotate a spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, following operation of the first gas-turbine engine, the first electric starter to perform barring of the first gas-turbine engine; measure, during the barring of the first gas-turbine engine, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.

IPC Classes  ?

• F02C 7/268 - Starting drives for the rotor
• F01D 19/00 - Starting of machines or enginesRegulating, controlling, or safety means in connection therewith

Abstract

A method of forming a ceramic matrix composite having a smooth surface includes laying up a plurality of plies, where some or all of the plies include an arrangement of spread tows comprising carbon fibers, thereby forming a fiber preform. Each spread tow has a height-to-width aspect ratio of less than about 0.1. The fiber preform is infiltrated with a ceramic matrix material and/or ceramic matrix precursor to embed the carbon fibers in a ceramic matrix. Thus, a ceramic matrix composite comprising a smooth and/or flat surface devoid of undulations from rounded tows is formed.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/565 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching

Abstract

A power electronic assembly includes a power electronic and a cold plate. The power electronic is configured to be powered by electric energy and to generate waste heat from the electric energy. The cold plate include polymeric material and is configured to elastically deform to uniformly cover the power electronic and transfer away the waste heat generated by the power electronic.

IPC Classes  ?

• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

A multi-piece radial turbine rotor includes a hub, turbine blades, and an intermediate ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

IPC Classes  ?

• F01D 5/04 - Blade-carrying members, e.g. rotors for radial-flow machines or engines
• B23K 1/00 - Soldering, e.g. brazing, or unsoldering
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

IPC Classes  ?

• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F04D 27/02 - Surge control
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Abstract

A turbine engine includes a core section comprising at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine; a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine; and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor, wherein the electrical generator comprises: a turbine configured to extract work from a core fluid flow, the turbine configured to rotate about the longitudinal axis; a rotor mechanically rotated by the turbine of the electrical generator, the rotor configured to rotate about the longitudinal axis; and a stator. The rotor of the electrical generator maybe rotationally decoupled from the fan.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• 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

Abstract

A centrifugal air-oil separator system for a gas turbine engine system is described. The air-oil separator system has a rotatable shaft and the shaft includes an axially extending bore formed at least partially through the shaft. A gear is integral to or mounted on an outer surface of the shaft. The air-oil separator system also includes a bolt-on breather mounted on the shaft and independent from and in contiguous contact with the gear to assist in separating the oil from the air. Various types of materials may be utilized in the construction of the air-oil separator system.

IPC Classes  ?

• F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
• B01D 45/14 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by rotating vanes, discs, drums or brushes
• B04B 5/00 - Other centrifuges
• B04B 5/08 - Centrifuges for separating predominantly gaseous mixtures
• B04B 9/08 - Arrangement or disposition of transmission gearing

Abstract

A fan duct assembly includes a bypass duct, an outlet guide vane assembly, and a flow control system. The bypass duct has an outer wall and an inner wall that define a gas path for bypass air therebetween. The outlet guide vane assembly is coupled with the bypass duct and includes a plurality of vanes. The flow control system is configured to direct selectively a portion of the bypass air flowing through the gas path radially into each of the plurality of vanes.

IPC Classes  ?

• F01D 17/10 - Final actuators
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

Scavenge systems for a gas turbine engine including a valve positioned at a first drainage outlet of an enclosure to selectively open and evacuate liquid from the cavity through the first drainage outlet in response to the valve being submerged in liquid are provided. Methods of reducing suction of air from an enclosure of a cavity of a gas turbine engine are further provided.

IPC Classes  ?

• F01M 11/04 - Filling or draining lubricant of or from machines or engines
• F01M 11/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, groups
• F01M 11/06 - Means for keeping lubricant level constant or for accommodating movement or position of machines or engines
• F01M 11/12 - Indicating devicesOther safety devices concerning lubricant level

Abstract

A rotor assembly for an electric machine includes a rotor segment configured to rotate about an axis and having a rotor body, a side wall and an outer band that cooperate to form a cavity, a plurality of magnets located in the cavity, and an end plate configured to block the plurality of magnets within the cavity.

IPC Classes  ?

• H02K 1/2706 - Inner rotors
• H02K 1/02 - Details of the magnetic circuit characterised by the magnetic material

Abstract

A power distribution system for an aircraft includes a wing, a power supply circuit, and a controller. The supply circuit includes a DC power bus having a voltage, a resistive heating element electrically connected with the DC power bus and coupled with the wing, and a voltage manipulation element configured to selectively adjust an amount of voltage that is directed to the heating element. The controller is connected to the manipulation element and is configured to regulate the voltage of the DC power bus. The controller is programmed to control the manipulation element when the voltage of the DC power bus is greater than a threshold voltage to vary an amount of voltage that is directed to the heating element to cause the heating element to convert the amount of the voltage into heat and thereby regulate overvoltage of the voltage of the DC power bus.

IPC Classes  ?

• H02J 1/08 - Three-wire systemsSystems having more than three wires
• H02J 1/14 - Balancing the load in a network

Abstract

An example system includes a thermal energy system configured to transport thermal energy harvested from a first portion of a gas turbine engine to a second portion of the gas turbine engine after the gas turbine engine was in operation, wherein the transported thermal energy minimizes or prevents undesired contact or seizing of a rotor with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The thermal energy system includes a cavity configured to flow a fluid, wherein the fluid is configured to transport thermal energy from the first portion to the second portion.

IPC Classes  ?

• F02C 9/00 - Controlling gas-turbine plantsControlling fuel supply in air-breathing jet-propulsion plants
• F01D 25/10 - Heating, e.g. warming-up before starting

Abstract

An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.

IPC Classes  ?

• F01D 25/10 - Heating, e.g. warming-up before starting
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 19/02 - Starting of machines or enginesRegulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine casing
• F02C 9/00 - Controlling gas-turbine plantsControlling fuel supply in air-breathing jet-propulsion plants

Abstract

In some examples, a method of forming an article for a gas turbine engine, the method comprising depositing a powder to form a protective coating on a leading edge of an airfoil substrate. The deposited powder includes carbide particles in a metal matrix and the carbide particles in the powder have an average particle size of about 1 micron or less. The protective coating on the leading edge of the airfoil substrate includes the carbide particles in the metal matrix.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C23C 24/00 - Coating starting from inorganic powder

Abstract

An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from at least one of the one or more electrical busses.

IPC Classes  ?

• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• 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

Abstract

A heat exchanger assembly for a gas turbine engine includes an access panel configured to be removably coupled with an outer wall of a bypass duct arranged circumferentially around a central axis of the gas turbine engine. A heat exchanger is adapted to receive cooling fluid therein and is coupled with the access panel. A shroud extends between the access panel and the heat exchanger to collect a first portion of a flow of air through the bypass duct and direct the first portion through the heat exchanger.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an internally-cooled tip clearance system. The internally-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

IPC Classes  ?

• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components
• F01D 17/02 - Arrangement of sensing elements
• G01B 21/16 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance or clearance between spaced objects

Abstract

A forced air supply system is provided to deliver forced air to fluid or a mixture of fluid and air in an enclosure of a cavity of a gas turbine engine when the gas turbine engine experiences a negative-gravity force event. Methods are also provided for removing fluid and/or air from the enclosure when the gas turbine engine experiences the negative-gravity force.

IPC Classes  ?

• F02C 7/06 - Arrangement of bearingsLubricating

Abstract

A turbine engine includes a core section comprising at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine; a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify core fluid flow; a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine; and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor, wherein the electrical generator comprises: a rotor mechanically rotated via the fan or a shaft that is rotationally coupled to the fan, wherein the rotor rotates about the longitudinal axis; and a stator.

IPC Classes  ?

• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes two unique actuation assemblies each configured to rotate one of the tip and hub segments.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes two unique actuation assemblies each including a cam rod and cams located thereon that are configured to rotate a respective tip or hub segment.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F01D 17/00 - Regulating or controlling by varying flow

Abstract

A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes an actuation assembly having a pass through actuation rod enabling the single actuation assembly to rotate both of the tip and hub segments.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes an air manipulating member arranged radially between the tip and hub segments and at least one actuation assembly configured to rotate one of the tip and hub segments.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes two unique gear assemblies each configured to rotate one of the tip and hub segments.

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids

Abstract

A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes a single actuation assembly includes a cam rod and cams arranged thereon that is configured to rotate the tip and hub segments via the cams.

IPC Classes  ?

• F01D 7/00 - Rotors with blades adjustable in operationControl thereof

Abstract

A gas turbine engine includes: a manifold arrangement; a plurality of inlet guide vanes located radially inward of the manifold arrangement, wherein each inlet guide vane of the plurality of guide vanes includes an anti-ice cavity for directing a flow of an anti-ice air; and a plurality of crossover ducts located radially inside the manifold arrangement, wherein each crossover duct of the plurality of crossover ducts provides fluid communication between two adjacent inlet guide vanes.

IPC Classes  ?

• 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
• F02C 7/047 - Heating to prevent icing

Abstract

Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

IPC Classes  ?

• F02C 7/12 - Cooling of plants
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis to define a plurality of inlet openings in fluid communication with the plenum.

IPC Classes  ?

• 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
• F02C 7/057 - Control or regulation

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a fan case and a fan track liner. The fan case that extends circumferentially about an axis. The fan track liner extends circumferentially at least partway about the axis and is coupled with the fan case. The fan track liner includes an abradable section and a core section located radially outward of the abradable section. The core section defines a triply periodic minimal surface geometry.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, 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 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• F04D 29/52 - CasingsConnections for working fluid for axial pumps

Abstract

A thermal management system for a gas turbine engine includes an inlet, a compressor, a mixing unit, and a fuel source. The compressor includes a low pressure stage and a high pressure stage. The mixing unit includes a first valve port fluidically connected to a low pressure bleed line of the compressor and a high pressure bleed line of the compressor and having an adjustable inlet gate on each of these lines and an outlet fluidically connected to the inlet of the engine to prevent ice accretion in the inlet or de-ice the inlet. The fuel source is configured to provide fuel to the mixing unit to actuate the adjustable inlet gates to regulate the amounts of low pressure bleed air and high pressure bleed air directed to the outlet.

IPC Classes  ?

• F02C 7/047 - Heating to prevent icing
• 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
• 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

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits

Abstract

A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly. The inlet cowl includes a cowl duct configured to collect a first portion of the bypass air and conduct the first portion of the bypass air into the heat exchanger and a flow diverter that guides a second portion of the bypass air around the heat exchanger.

IPC Classes  ?

• F02K 3/075 - 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 controlling flow ratio between flows

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.

IPC Classes  ?

• 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
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers

Abstract

A gas turbine engine includes a bypass duct and a rotating detonation augmentor. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine to provide thrust for propelling the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase the thrust for propelling the gas turbine engine.

IPC Classes  ?

• F02K 3/11 - Heating the by-pass flow by means of burners or combustion chambers
• F02C 5/00 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
• F02K 3/02 - 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
• F02K 3/075 - 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 controlling flow ratio between flows
• F23R 7/00 - Intermittent or explosive combustion chambers

Abstract

In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.

IPC Classes  ?

• F02C 7/268 - Starting drives for the rotor
• F01D 25/36 - Turning or inching gear using electric motors
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F16D 11/14 - Clutches in which the members have interengaging parts with clutching members movable only axially