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

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  ?

• B04B 9/08 - Arrangement or disposition of transmission gearing
• 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
• F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles

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 11/12 - 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 17/00 - 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
• F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps

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 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 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 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

Abstract

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

Abstract

An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.

IPC Classes  ?

• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes

Abstract

A suspension plasma spray deposition system comprising a suspension plasma spray device configured to deposit coating material on a surface of a component. The surface of the component includes a plurality of apertures. The system further includes a fluid flow system configured to flow fluid through the plurality of apertures in the surface of the component to reduce deposition of coating material in plurality of apertures. The fluid flow through each respective aperture of the plurality of apertures in the surface of the component is between about 0.095 and about 0.200 cubic feet per minute (cfm).

IPC Classes  ?

• B05B 12/18 - Arrangements for controlling deliveryArrangements for controlling the spray area for controlling the spray area using fluids, e.g. gas streams
• B05B 5/03 - Discharge apparatus, e.g. electrostatic spray guns characterised by the use of gas
• B05B 5/053 - Arrangements for supplying power, e.g. charging power
• B05B 12/04 - Arrangements for controlling deliveryArrangements for controlling the spray area for controlling time, or sequence, of delivery for sequential operation or multiple outlets
• B05C 11/10 - Storage, supply or control of liquid or other fluent materialRecovery of excess liquid or other fluent material

Abstract

A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.

IPC Classes  ?

• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector

Abstract

A vane assembly includes a casing, vanes, and an actuator assembly. The vanes are arranged within the casing and are rotatably coupled to the casing for rotation relative thereto and configured to rotate about their pitch axes. The actuator assembly is arranged radially outward of the casing and includes an annular ring surrounding the casing and coupled to the vanes, a magnet arranged on the ring, and a stator spaced apart from the magnet. The ring is configured to rotate the vanes about their pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and ring about the central axis. The stator is configured to create a magnetic field which causes annular movement of the ring via interaction with the magnet.

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
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

Abstract

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment plate. The adjustment plate includes a main plate portion arranged on the ring and including a first adjustment region defined between two walls and a first elongated opening formed through the first adjustment region, and an adjustment fastener removably arranged in the first adjustment region between the first and second walls and including an adjustment head and a fastening pin eccentrically coupled to the adjustment head and removably coupled to the annular ring. The adjustment fastener can be selectively arranged at rotational positions within the first adjustment region so as to selectively arrange the fastening pin at distinct circumferential positions relative to the first and second walls such that the main plate portion can be positioned at distinct circumferential positions.

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
• F02C 9/22 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes by adjusting turbine vanes

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 1/56 - Reversing jet main flow
• F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers

Abstract

A thermal battery system may be provided comprising: a vessel comprising a phase change material and a gas; a heat exchanger configured to transfer heat to and/or from the phase change material; a temperature sensor configured to detect an indication of a temperature of the gas; a pressure sensor configured to detect an indication of a pressure of the gas; and a processor configured to determine a state of charge of the thermal battery system from the indication of the pressure and the indication of the temperature of the gas.

IPC Classes  ?

• F28D 20/02 - Heat storage plants or apparatus in generalRegenerative heat-exchange apparatus not covered by groups or using latent heat
• G01K 17/00 - Measuring quantity of heat

Abstract

A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.

IPC Classes  ?

• F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes
• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
• 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
• B64D 31/06 - Initiating means actuated automatically

Abstract

A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.

IPC Classes  ?

• F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use

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 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

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 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  ?

• F02C 9/22 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes by adjusting turbine vanes
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• 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 29/54 - Fluid-guiding means, e.g. diffusers

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 assembly is configured to balance a weight distribution of the rotor assembly.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A circuit board assembly may include a first printed circuit board having at least one trace plane. The trace plane may have a plurality of traces secured to a core material of the first printed circuit board. A security layer may be included, where the security layer at least partially covers the at least one trace plane such that the security layer forms at least one of a ground shield and an electromagnetic shield over the at least one trace plane. In some implementations, the security layer may be integral with a core material of the circuit board.

IPC Classes  ?

• H05K 1/02 - Printed circuits Details

Abstract

A method of producing or repairing a fiber-reinforced ceramic matrix composite comprises delivering a powder composition comprising SiC particles and chopped coated SiC fibers into or onto a powder receptacle configured for composite fabrication or repair. After delivering the powder composition into or onto the powder receptacle, the SiC particles are densified to form a SiC matrix reinforced with the chopped coated SiC fibers, thereby producing or repairing a fiber-reinforced ceramic matrix composite.

IPC Classes  ?

• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 35/628 - Coating the powders
• C04B 35/64 - Burning or sintering processes
• C04B 35/657 - Processes involving a melting step for manufacturing refractories
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/87 - Ceramics

Abstract

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a base plate coupled to the ring and having a recess, a first collar removably arranged within the recess and having a cavity formed therein, a second collar removably arranged within the cavity, and a roller pin fixedly coupled to the second collar. The cavity is offset relative to the first collar and roller pin is offset relative to the second collar. The first collar can be selectively arranged at rotational positions within the recess and the second collar can be selectively arranged at rotational positions within the cavity such that the roller pin can be positioned at distinct positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

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 vane adjustment assembly includes vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The adjustment assembly includes a base frame mounted on the ring and including a support body having a first cavity, a first collar removably arranged within the first cavity and having a second cavity formed therein, a second collar removably arranged within the second cavity, and a roller pin coupled to the second collar. The second cavity is offset relative to the first collar and the roller pin is offset relative to the second collar. The first and second collars can be selectively arranged at rotational positions within the first and second cavities such that the roller pin can be positioned at distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

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 gas turbine engine including a compressor, a pressure-gain combustor, and a turbine is disclosed. The compressor compresses air drawn into the engine and delivers high pressure air to the pressure-gain combustor. In the pressure-gain combustor, fuel is mixed with the high pressure air and is ignited. Products of the combustion reaction in the pressure-gain combustor are directed into the turbine at a pressure greater than that of the air discharged by the compressor. In the turbine, work is extracted by actively cooled turbine blades to drive the compressor and, sometimes, an output shaft. In illustrated designs, some compressed air from the compressor is diverted around combustion in the combustor to provide active cooling for the turbine blades.

IPC Classes  ?

• F23R 7/00 - Intermittent or explosive combustion chambers
• F01D 9/06 - Fluid supply conduits to nozzles or the like

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 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/268 - Starting drives for the rotor
• H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a first inclined plate and a second inclined plate, the first inclined plate having an inclined surface facing a first inclined surface of the second inclined plate. A roller pin is coupled to a second inclined surface of the second inclined plate opposite the first inclined surface. The second inclined plate is adjustable in the circumferential direction such that the inclined surface of the first inclined plate and the first inclined surface of the second inclined plate slide against each other during adjustment of the second inclined plate so as to adjust an axial position and a circumferential position of the roller pin relative to the annular ring.

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
• F02C 9/22 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes by adjusting turbine vanes

Abstract

A rotor assembly includes a first component, a second component, and a splined balance weight. The first component is arranged circumferentially around a central axis. The second component is arranged circumferentially around the central axis. The splined balance weight is located radially between the first component and the second component.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 5/10 - Antivibration means

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  ?

• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F02C 9/22 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes by adjusting turbine vanes
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers

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

Abstract

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

IPC Classes  ?

• B64D 33/10 - Radiator arrangement
• B64D 37/34 - Conditioning fuel, e.g. heating
• F02C 7/12 - Cooling of plants
• F02C 7/224 - Heating fuel before feeding to the burner
• F02K 7/10 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

Abstract

A cooling apparatus includes a first fluid flowpath and a second fluid flowpath. The first fluid flowpath includes a subcooler having a first side in fluid communication with the first fluid flowpath; a flow control valve; a primary evaporator assembly including at least one evaporator configured to be disposed in thermal communication with a heat load; and a pressure regulator operable to control a saturation pressure within the at least one evaporator. The second fluid flowpath is in fluid communication with a second side of the subcooler.

IPC Classes  ?

• F25B 40/00 - Subcoolers, desuperheaters or superheaters
• F25B 6/00 - Compression machines, plants or systems, with several condenser circuits
• F25B 40/02 - Subcoolers
• F25B 41/20 - Disposition of valves, e.g. of on-off valves or flow control valves

Abstract

A turbine engine may include a compressor section of the turbine engine. The turbine engine may include a combustion section of the turbine engine. The combustion section may be downstream of the compressor section. The turbine engine may include a turbine section of the turbine engine. The turbine section may be downstream of the combustion section. The turbine engine may include a sensor for speed detection. The sensor may be disposed at an upstream segment of the turbine section. The sensor may include a cooling jacket. The cooling jacket may encase at least a portion of the sensor. A cooling fluid may be in fluid communication with the cooling jacket and an outer surface of the sensor. The cooling jacket may be shaped to direct cooling fluid around the sensor.

IPC Classes  ?

• F02C 7/12 - Cooling of plants
• F01D 17/02 - Arrangement of sensing elements
• F01D 25/12 - Cooling

Abstract

A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

IPC Classes  ?

• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

An example system includes a power electronics system; a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft; and an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system, wherein the power electronics system is configured to deliver alternating current (AC) electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from an AC electrical bus of the aircraft.

IPC Classes  ?

• H02P 9/08 - Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
• F02C 7/268 - Starting drives for the rotor

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 27/10 - 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
• B64D 27/02 - Aircraft characterised by the type or position of power plants

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
• B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
• F02K 1/56 - Reversing jet main flow

Abstract

A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

IPC Classes  ?

• F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
• F01D 25/12 - Cooling
• F02C 3/08 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
• 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

Abstract

A compressor assembly for a gas turbine engine includes an outer band, a plurality of variable pitch vanes, and an inner band. The plurality of variable pitch vanes extend radially between the outer band and the inner band. The inner band extends circumferentially partway about an axis and includes a first ring segment and a second ring segment that cooperate to receive the plurality of variable pitch vanes.

IPC Classes  ?

• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/02 - Selection of particular materials
• F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids

Abstract

A gas turbine engine system includes a gas turbine engine, an accessory gearbox, and a flywheel powered barring engine system. The gas turbine engine includes a rotor and a turbine. The accessory gearbox is connected with the rotor. The flywheel powered barring engine system is connected with the accessory gearbox and configured to rotate the rotor after shut down of the gas turbine engine.

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 6/14 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads

Abstract

A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening and a third opening that extend completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening via at least the third opening. The first and second opening are configured to receive a plug or a probe.

IPC Classes  ?

• F01D 25/12 - Cooling
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for

Abstract

A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

IPC Classes  ?

• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

A power-generation system for a nuclear reactor includes a power unit, a heat exchanger, and a temperature control system. The power unit produces compressed air that is heated by the nuclear reactor via the heat exchanger. The temperature control system includes a heat transfer fluid and a heat exchanger fluidly connected with the compressed air to transfer heat between the compressed air and heat transfer fluid to control the power level of the power unit.

IPC Classes  ?

• G21C 15/12 - Arrangement or disposition of passages in which heat is transferred to the coolant, e.g. for coolant circulation through the supports of the fuel elements from pressure vesselArrangement or disposition of passages in which heat is transferred to the coolant, e.g. for coolant circulation through the supports of the fuel elements from containment vessel
• G21C 15/253 - Promoting flow of the coolant for gases, e.g. blowers
• G21C 15/243 - Promoting flow of the coolant for liquids

Abstract

A gas turbine engine comprises an engine core and an electric fan array. The engine core includes a compressor, a combustor, and a turbine. The compressor compresses and delivers air to the combustor. The combustor mixes fuel with the compressed air received from the compressor and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor are directed into the turbine to cause the turbine to rotate about an axis and drive the compressor. The electric fan array may include at least two non-concentric fans having parallel shafts.

IPC Classes  ?

• F04D 29/66 - Combating cavitation, whirls, noise, vibration, or the likeBalancing
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
• F04D 25/06 - Units comprising pumps and their driving means the pump being electrically driven
• F04D 27/00 - Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
• F02C 9/16 - Control of working fluid flow