Abstract

An electric machine of a gas-turbine engine, the electric machine comprising: a stator; and a rotor configured to rotate around the stator, the rotor comprising: a rotor body having an inner surface and an outer surface; magnets; and one or more retention rings attached to the rotor body and configured to radially retain the magnets to the inner surface of the rotor body.

IPC Classes  ?

• H02K 1/2786 - Outer rotors
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• 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 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans

Abstract

A gas turbine engine system adapted for use with an aircraft includes a gas turbine engine. The gas turbine engine system includes a gas turbine engine and an auxiliary compressor operably coupled with the gas turbine engine. The auxiliary compressor arranged to receive air from an inlet that faces away from a direction of travel of the aircraft such that the air flowing to the auxiliary compressor has a lower mass flow rate of air at an inflight airspeed than a mass flow rate of air of a forward facing inlet so that the auxiliary compressor consumes less work from the turbine inflight.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
• F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

Abstract

A climatic test conditioning apparatus for conditioning a machine for climatic testing comprises a base and an inflatable wall connected to the base. The inflatable wall has at least one port for at least partial inflation and deflation of the inflatable wall. The at least partially inflated inflatable wall and base define a volume that envelopes the machine. Also disclosed is a system and method for climatic test conditioning a machine.

IPC Classes  ?

• G01N 17/00 - Investigating resistance of materials to the weather, to corrosion or to light
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Abstract

A power-generation system includes an electrical system, a turbine engine, and a fluid control system. 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 drive rotation of the compressor, 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 fluid control system fluidly is connected with the electrical system and the turbine engine to circulate the working fluid through the electrical system and the turbine engine.

IPC Classes  ?

• F01K 25/00 - Plants or engines characterised by use of special working fluids, not otherwise provided forPlants operating in closed cycles and not otherwise provided for
• F01K 3/18 - Plants characterised by the use of steam or heat accumulators, or intermediate steam heaters, therein having heaters
• F01K 13/02 - Controlling, e.g. stopping or starting

Abstract

A nosecone for a gas turbine engine includes a nosecone body substantially symmetrical around a central axis. The nosecone body includes a side wall which defines a diameter of the nosecone body that increases from a forward side to an aft side of the nosecone body. The nosecone further includes an attachment assembly which attaches the nosecone body to the gas turbine engine. The nosecone includes a plurality of airstream protrusions attached to or integral with the nosecone body. A first airstream protrusion of the plurality of airstream protrusions is positioned upstream of a first fan blade to prepare an airstream flowing over the nosecone body for interaction with the first fan blade. The attachment assembly includes a plurality of attachment locations, and a first attachment location of the plurality of attachment locations is collocated with the first airstream protrusion of the plurality of airstream protrusions.

IPC Classes  ?

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

Abstract

A nosecone for a gas turbine engine includes a nosecone body. The nosecone body is substantially symmetrical around a central axis. The nosecone body includes a side wall which defines a diameter of the nosecone body that increases from a forward side of the nosecone body to an aft side of the nosecone body. The nosecone includes an attachment assembly. The attachment assembly is configured to attach the nosecone body to the gas turbine engine. At least one of the nosecone body or the attachment assembly comprises a tear-resistant fiber.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

A turbine engine includes at least one compressor, combustion equipment, and at least one turbine. A stage is positioned aft of the at least one turbine, the stage comprising a plurality of blades. The turbine engine includes an electrical generator. The electrical generator includes a rotor carried on an outer diameter of the plurality of blades of the stage and mechanically rotated by the plurality of blades of the stage, the rotor configured to rotate about a longitudinal axis of the turbine engine, and a stator.

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 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A gas turbine engine system includes an enclosure, a compressor assembly located at least partially within the enclosure, and a bleed-duct joint. The compressor assembly includes a compressor and a bleed-air collector having a bleed-air manifold configured to receive a portion of air compressed by the compressor and a bleed-air duct extending through an aperture in the enclosure to direct the portion of the air outside of the enclosure. The bleed-air duct includes a first pipe coupled to the compressor for movement with the compressor and a second pipe extending through the aperture in the first wall and arranged around the first pipe. The bleed-duct joint is configured to couple the bleed-air duct with the enclosure to locate the second pipe relative to the first pipe.

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• 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 27/02 - Surge control
• F04D 29/08 - Sealings

Abstract

A cyber security data recorder may be provided that includes: a data recorder controller; a data recorder memory; and a data recorder input interface configured to receive a signal from an embedded system. The data recorder controller may read forensic data from the embedded system via the data recorder input interface. The data recorder controller may read samples of the signal at intervals that are random and unknown to the embedded system. Alternatively or in addition, the forensic data may be determined as a rate of jump instructions, a ratio of jump to non-jump instructions, and/or an instruction rate from the signal. The data recorder controller may store the forensic data in the data recorder memory.

IPC Classes  ?

• G06F 21/55 - Detecting local intrusion or implementing counter-measures
• G06F 21/56 - Computer malware detection or handling, e.g. anti-virus arrangements

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
• F02C 7/262 - Restarting after flame-out
• F02C 7/268 - Starting drives for the rotor
• F02C 7/277 - Mechanical drives the starter being a turbine

Abstract

A fan case assembly includes an annular case including a first circumferentially-extending slot formed therein, and a tip treatment segment arranged within the first slot and retained therein. The tip treatment segment includes a radially inwardly-facing segment surface having a tip treatment groove formed therein. The tip treatment segment is selectively removable from and insertable into the first slot and is slidable within and along the first slot such that the tip treatment segment is configured to be selectively positioned within the first slot so as to alter the portion of a flow path across the annular case in order to control stall margin of the gas turbine engine and optimize performance of the gas turbine engine.

IPC Classes  ?

• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F01D 5/14 - Form or construction
• 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 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers

Abstract

A fan case assembly includes an annular case and a fan track liner. The fan track liner includes a variable wall assembly having a stationary portion defining a circumferentially extending groove therein and a movable segment arranged in the groove. The movable segment can be selectively radially translatable within the groove. Radially inwardly facing surfaces of the movable segment and the stationary portion define a portion of a flow path across the fan track liner, and the movable segment can be radially translated within the groove to alter the portion of the flow path across the fan track liner in order to control stall margin of the engine and optimize performance of the engine.

IPC Classes  ?

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

Abstract

A power-generation system includes an electrical system, a turbine engine, and a fluid control system. 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 drive rotation of the compressor, 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 fluid control system fluidly is connected with the electrical system and the turbine engine to circulate the working fluid through the electrical system and the turbine engine.

IPC Classes  ?

• 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
• F02C 1/05 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
• F02C 1/10 - Closed cycles
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A fan containment case includes a barrel that includes a case structure and a nanocrystalline metal coating overlying the case structure. The case structure includes a plurality of carbon fiber bands, in which at least an outermost carbon fiber band and an innermost carbon fiber band include a fire resistant polymer matrix. The case structure also includes at least one cut resistant polymer band between the outermost and the innermost carbon fiber bands.

IPC Classes  ?

• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• 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

Abstract

A gas turbine engine system includes an enclosure, a compressor located within the disclosure, and a bleed-air collector coupled to the compressor. The compressor includes an outer case and a bleed-air valves fluidly coupled with the outer case of the compressor and configured to direct a portion of the air through the outer case. The bleed-air collector is fluidly coupled to the bleed-air valve and includes a bleed-air manifold configured to collect the portion of the air bled from the primary flow path and a first bleed-air duct fluidly coupled to the first bleed-air manifold to receive the collected bleed air and direct the first portion of the air through one of the plurality of walls and out of the enclosure.

IPC Classes  ?

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

Abstract

An exhaust nozzle includes an outer nozzle case having an outer surface and an inner surface, a nozzle plug, and a thrust reverser coupled to the outer nozzle case and including a first thrust reverser panel coupled to the outer nozzle case and an actuator system coupled with the first thrust reverser panel and configured to move the first thrust reverser panel between and including a stored configuration and a reverse-thrust configuration. In the stored configuration, the first thrust reverser panel and a portion of the actuator system provide a portion of an exterior surface of the exhaust nozzle.

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

Systems and methods for fluid flow control are provided. A coarse valve and a fine valve are connected in parallel in a conduit. A coarse valve controller controls the coarse valve in a feedback loop in which an error signal is feedback to the coarse valve controller and a coarse valve setting is an output of the coarse valve controller. The error signal is a difference between the property of the fluid flow and a set point. The coarse valve controller operates as a proportional-integral controller. A fine valve controller controls the fine valve in the same feedback loop as the coarse valve controller. The fine valve controller has a center-seeking control scheme and operates as a proportional controller or a proportional-integral controller depending on whether the coarse valve setting is in a saturation range.

IPC Classes  ?

• F02C 7/057 - Control or regulation
• F02C 9/16 - Control of working fluid flow
• G05D 7/06 - Control of flow characterised by the use of electric means

Abstract

A turbine engine includes at least one turbine, combustion equipment, and at least one compressor. The at least one compressor includes a compressor stage. The compressor stage includes a plurality of compressor blades configured to input work into a core airflow flowing through the turbine engine. The turbine engine includes an electrical generator. The electrical generator includes a rotor carried on an outer diameter of the plurality of compressor blades of the compressor stage and mechanically rotated by the plurality of compressor blades of the compressor stage and configured to rotate about a longitudinal axis of the turbine engine. The electrical generator further includes a stator.

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

An aircraft includes a duct system, a gas turbine engine, and an inlet flow regulation system. The duct system includes a main duct, a first inlet duct in fluid communication with the main duct, and a second inlet duct in fluid communication with the main duct. The inlet flow regulation system includes an inlet flow regulator configured to manage different flow characteristics of a flow of air entering the first and second inlet ducts to form a substantially uniform flow distribution through the main duct and into the gas turbine engine and a control unit in communication with the inlet flow regulator and configured to selectively move the inlet flow regulator.

IPC Classes  ?

• F01D 17/00 - Regulating or controlling by varying flow
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes

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 a valve seal configured to block bleed air from passing between the piston and the manifold when the piston is in a closed position.

IPC Classes  ?

• 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 test apparatus for a ceramic matrix composite (CMC) component. The test apparatus includes a first support member configured to mechanically support a CMC component from a first side. The CMC component includes a T-joint and a pinhole. The test apparatus includes a second support member configured to mechanically support the CMC component from a second side opposite the first side. The first support member and the second support member are configured to be forced toward each other to cause the CMC component to fail at the pinhole and not at the T-joint.

IPC Classes  ?

• G01N 3/08 - Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces

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

An example aircraft includes a plurality of gas-turbine engines mounted external to a fuselage of the aircraft, each gas-turbine engine of the plurality of gas-turbine engines including a respective hydraulic pump of a plurality of hydraulic pumps; a hydraulic motor disposed within the fuselage of the aircraft; a hydraulic distribution network configured to carry hydraulic fluid between the hydraulic motor and the plurality of hydraulic pumps to drive the hydraulic motor; and an electrical generator disposed within the fuselage of the aircraft and configured to be driven by the hydraulic motor.

IPC Classes  ?

• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• B64D 27/14 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, fuselages
• F15B 1/04 - Accumulators
• F15B 1/26 - Supply reservoir or sump assemblies
• F15B 11/17 - Servomotor systems without provision for follow-up action with two or more servomotors using two or more pumps
• F15B 15/18 - Combined units comprising both motor and pump

Abstract

An example method includes pressurizing, by a plurality of engine driven hydraulic pumps respectively attached to a plurality of gas-turbine engines of an aircraft, hydraulic fluid; generating, by a hydraulic motor disposed within a fuselage of the aircraft and using combined pressurized hydraulic fluid received from the plurality of engine driven hydraulic pumps, rotational mechanical energy; and generating, by an electrical generator disposed within the fuselage of the aircraft and using the rotational mechanical energy, electrical energy.

IPC Classes  ?

• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64D 27/40 - Arrangements for mounting power plants in aircraft

Abstract

A method includes receiving, by a computing device, a raw image indicative of a cross-section of a thermally-sprayed layer. The image includes a matrix of pixels, and each respective pixel in the matrix of pixels defines a luminance value. The method may further include determining, based on the luminance values, at least one pixel that corresponds to an oxide component in the layer and removing the at least one pixel that corresponds to the oxide component in the layer to generate a modified matrix of pixels. The method may further include generating an oxide-filtered image based on the modified matrix of pixels. The method may further include converting, by the computing device and based on the luminance values, the oxide-filtered image into a binary image and determining, by the computing device and based at least partially on the binary image, a porosity of the coating layer.

IPC Classes  ?

• G01N 15/08 - Investigating permeability, pore volume, or surface area of porous materials
• G06T 5/20 - Image enhancement or restoration using local operators
• G06T 7/13 - Edge detection
• G06V 10/60 - Extraction of image or video features relating to illumination properties, e.g. using a reflectance or lighting model
• H04N 23/76 - Circuitry for compensating brightness variation in the scene by influencing the image signals

Abstract

A method includes receiving, by a computing device, an image indicative of a cross-section of a thermally-sprayed layer. The thermally-sprayed layer includes a microstructure. The image comprises a matrix of pixels, each pixel in the matrix of pixels defining a respective luminance value. The method includes determining, by the computing device and based on the luminance values of the matrix of pixels, a quantification of a layering of the microstructure of the thermally-sprayed layer.

IPC Classes  ?

• G06T 7/00 - Image analysis
• G06T 5/92 - Dynamic range modification of images or parts thereof based on global image properties
• G06T 7/60 - Analysis of geometric attributes
• G06V 10/24 - Aligning, centring, orientation detection or correction of the image
• G06V 10/77 - Processing image or video features in feature spacesArrangements for image or video recognition or understanding using pattern recognition or machine learning using data integration or data reduction, e.g. principal component analysis [PCA] or independent component analysis [ICA] or self-organising maps [SOM]Blind source separation

Abstract

A method includes receiving, by a computing device, an image indicative of a cross-section of a thermally-sprayed layer. The thermally-sprayed layer defines a porosity comprising a void volume of the thermally-sprayed layer. The image comprises a matrix of pixels, each pixel in the matrix of pixels defining a respective luminance value of a plurality of luminance values. The method includes identifying, based on the luminance values, at least one pixel that is indicative of a void volume in the thermally-sprayed layer. The method includes calculating, based on the at least one pixel that is indicative of the void volume in the thermally-sprayed layer, a total porosity of the thermally-sprayed layer. The method includes determining, by the computing device and based on the at least one pixel that corresponds to a void volume in the thermally-sprayed layer, a quantification of a spatial homogeneity of the porosity of the thermally-sprayed layer.

IPC Classes  ?

• G01N 15/08 - Investigating permeability, pore volume, or surface area of porous materials
• C23C 4/06 - Metallic material
• G06V 10/60 - Extraction of image or video features relating to illumination properties, e.g. using a reflectance or lighting model

Abstract

A multi-piece heat exchanger for transferring heat between a hot working fluid and a coolant according to the disclosure includes a multi-piece shell, a core, and first and second expansion joints. The multi-piece shell is arranged around an axis and receives coolant therein. The core is located within the shell and direct a hot working fluid therethrough.

IPC Classes  ?

• F28F 9/02 - Header boxesEnd plates

Abstract

A multi-piece radial turbine rotor includes a hub and a bladed crown manufactured via additive layer manufacturing. A bond is formed between the hub and the bladed crown to fix the components together for rotation.

IPC Classes  ?

• F04D 29/28 - Rotors specially adapted for elastic fluids for centrifugal or helico-centrifugal pumps
• F04D 17/00 - Radial-flow pumps specially adapted for elastic fluids, e.g. centrifugal pumpsHelico-centrifugal pumps specially adapted for elastic fluids
• F04D 29/02 - Selection of particular materials
• F04D 29/58 - CoolingHeatingDiminishing heat transfer

Abstract

A heat exchanger for transferring heat between a hot working fluid and a coolant according to the disclosure includes a shell, a core, and an expansion joint. The shell is arranged around an axis and receives a coolant therein. The core is located within the shell and directs a hot working fluid therethrough.

IPC Classes  ?

• F28F 9/02 - Header boxesEnd plates

Abstract

An example electric machine of a gas-turbine engine having a longitudinal axis includes a stator; a rotor configured to rotate around the stator and about the longitudinal axis of the gas-turbine engine, the rotor comprising: a rotor body having an inner surface and an outer surface; and magnets on the inner surface of the rotor body, wherein axial edges of the magnets perpendicular to the longitudinal axis are profiled to include a shoulder that corresponds to a geometry of a radial retention structure of the rotor.

IPC Classes  ?

• H02K 1/2791 - Surface mounted magnetsInset magnets
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02K 1/28 - Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures
• 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 electric machine of a gas-turbine engine, the electric machine comprising: a stator; and a rotor configured to rotate around the stator, the rotor comprising: a rotor body having an inner surface and an outer surface; magnets; and one or more retention rings attached to the rotor body and configured to radially retain the magnets to the inner surface of the rotor body.

IPC Classes  ?

• H02K 1/2786 - Outer rotors
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• 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 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans

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 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 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 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 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 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, a plurality of turbine blades, and a flowpath ring that couples the turbine blades to the hub. The flowpath ring is coupled with each of the plurality of turbine blades and the hub to locate the flowpath ring radially between the hub and each of the plurality of turbine blades. The flowpath ring is formed to include a plurality of apertures spaced apart from one another about the flowpath ring and extending radially through the flowpath ring. Each of the plurality of apertures receives a corresponding one of the plurality of turbine blades therein. The hub is fixed to the flowpath ring by a friction weld joint and each of the plurality of turbine blades is fixed to the flowpath ring by a blade joint.

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

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 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

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
• F01D 5/04 - Blade-carrying members, e.g. rotors for radial-flow machines or engines
• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 1/08 - Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor traversed by the working-fluid substantially radially having inward flow

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

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  ?

• F16K 31/126 - Operating meansReleasing devices actuated by fluid the fluid acting on a diaphragm, bellows, or the like
• F16K 1/36 - Valve members

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 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

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
• 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
• 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

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 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 25/14 - Casings modified therefor

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  ?

• G01K 7/026 - Arrangements for signalling failure or disconnection of thermocouples
• G01K 1/02 - Means for indicating or recording specially adapted for thermometers
• G01K 15/00 - Testing or calibrating of thermometers

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 7/026 - Arrangements for signalling failure or disconnection of thermocouples
• G01K 1/02 - Means for indicating or recording specially adapted for 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
• G01K 13/08 - Thermometers specially adapted for specific purposes for measuring temperature of moving solid bodies in rotary movement

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 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
• 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 7/14 - 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
• 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
• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

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
• F02C 7/268 - Starting drives for the rotor
• F02C 7/262 - Restarting after flame-out
• F02C 7/277 - Mechanical drives the starter being a turbine

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

A heat exchanger may include a first coolant path for circulating a first coolant and a second coolant path for circulating a second coolant, where the first coolant path including a plurality of first cooling tubes, where the second coolant path including a plurality of second cooling tubes, where the first coolant path is fluidly isolated from the second coolant path in the heat exchanger, and where the first cooling tubes and the second cooling tubes are arranged in series and such that the first cooling tubes alternate with the second cooling tubes in an airflow direction.

IPC Classes  ?

• F28D 1/04 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid with tubular conduits
• F28D 7/00 - 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
• F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

Abstract

A cooling system for an electronics cabinet includes a controller configured to operate at least one of a pump or a condenser of a two-phase cooling loop. The cooling system includes a high temperature mode where the setpoint is set to a high setpoint setting, and a low temperature mode where the setpoint is set to a low setpoint setting. The controller is configured to select between the high temperature mode and the low temperature mode based on an evaluation of a power outage.

IPC Classes  ?

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

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