Abstract

A fluid storage tank can be configured to store a cooling fluid in a liquid state and a gas state. A first heat exchanger can be configured to release heat into the fluid storage tank. A second heat exchanger can be disposed fluidly downstream of the fluid storage tank and configured to exchange heat between the cooling fluid and a heat load. A pressure control device can be disposed fluidly downstream of the second heat exchanger. The first heat exchanger can be fluidly downstream of the second heat exchanger such that cooling fluid, after being heated in the second heat exchanger, passes through the first heat exchanger and thereby heats upstream cooling fluid resident in the fluid storage tank.

IPC Classes  ?

• F17C 7/04 - Discharging liquefied gases with change of state, e.g. vaporisation

Abstract

A cooling apparatus includes: a first fluid flowpath including the following elements, in downstream flow sequence: a separator vessel; a subcooler having a first side in fluid communication with the first fluid flowpath and a second side configured to be disposed in thermal communication with a cold sink; a flow control valve; a primary evaporator assembly including at least one primary evaporator configured to be disposed in thermal communication with a primary heat load; and a pressure regulator operable to maintain a refrigerant saturation pressure within the primary evaporator at a predetermined set point.

IPC Classes  ?

• F25B 40/02 - Subcoolers
• F25B 41/00 - Fluid-circulation arrangements

Abstract

A system may include a prime mover configured to provide mechanical energy to the system by spinning a shaft. The system further includes a synchronous AC generator mechanically coupled to the shaft, and an exciter mechanically coupled to the shaft and configured to output a field current for exciting the synchronous AC generator. The system also includes a number of synchronous electric motors electrically coupled to the AC generator and configured to drive one or more mechanical loads. A controller of the system is configured to establish and maintain a magnetic coupling between the synchronous AC generator and the synchronous electric motors by controlling a level of the field current during a ramped increase in rotation of the synchronous AC generator from zero rotational speed. The motors accelerate synchronously with the generator due to the magnetic coupling as the rotational speed of the generator increases.

IPC Classes  ?

• H02P 9/00 - Arrangements for controlling electric generators for the purpose of obtaining a desired output
• H02P 9/08 - Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
• H02P 9/30 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
• H02P 5/74 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors controlling two or more AC dynamo-electric motors
• H02P 6/20 - Arrangements for starting
• H02P 1/54 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting two or more dynamo-electric motors
• H02P 1/56 - Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting two or more dynamo-electric motors simultaneously
• H02J 3/40 - Synchronising a generator for connection to a network or to another generator

Abstract

An apparatus includes a composite gas turbine engine multi-airfoil blade (10) that includes first and second circumferentially spaced adjacent composite airfoils (12) coupled together via a common composite attachment (18). The common attachment (18) does not employ a fastener. The composite multi-airfoil blade(10) may have a unitary construction having a ceramic matrix composition.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

The present disclosure relates to a hot section gas turbine engine component assembly and a method for forming such.

IPC Classes  ?

• B22F 3/15 - Hot isostatic pressing
• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• B22F 7/08 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
• C22C 1/04 - Making non-ferrous alloys by powder metallurgy
• C22C 14/00 - Alloys based on titanium
• B22F 3/24 - After-treatment of workpieces or articles

Abstract

A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion (22) and a second surface coupled to the second end of the blade portion (22), the first and second surfaces arranged to extend divergently away from one another, and a plurality of compliant layers (36) arranged to engage a turbine wheel of the gas turbine engine to space the first and second surfaces from mating surfaces of the turbine wheel to dissipate locakized stresses on the engagement portion by absorbing and distributing the forces along the length of the engament portion to prevent fracturing of the engagement portion.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

A gas turbine engine comprising a combustion system configured for continuous detonation combustion process, the process employing a rotating continuous detonation wave (70).

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F23R 7/00 - Intermittent or explosive combustion chambers
• 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

Abstract

An exemplary gas turbine engine may include a compressor, a turbine, and a combustor disposed between the compressor and the turbine. The combustor generally may have an inner casing. The exemplary gas turbine may further include a pre-swirl nozzle configured to receive a cooling stream. The cooling stream may be supplied from a cooled cooling air stream. The pre-swirl nozzle may further be configured to direct at least a portion of the cooling stream to the turbine. The pre-swirl nozzle may be flexibly mounted to the inner casing of the combustor.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/08 - Heating, heat-insulating, or cooling means
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F23R 3/60 - Support structuresAttaching or mounting means

Abstract

A retention pin assembly (50) may include a stud (72) having a head (76), a shaft (74), and a deformable end (78). The shaft (74) may include a stepped surface having a greater diameter than the deformable end (78). The assembly may include a support member (66) having an opening for receiving the deformable end (78). The support member (66) may include a pocket (80). The stepped surface of the shaft (74) may position the stud (72) in relation to the support member (66). The deformable end (78) of the stud (72) may be operable to be melted to form a mechanical retainer within the pocket (80) without forming a metallurgical joint between the stud (72) and the pocket (80). A leaf seal assembly comprising such a retention pin, and a corresponding method of forming a joint.

IPC Classes  ?

• B21J 15/08 - Riveting by applying heat to the end parts of the rivets to enable heads to be formed
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F02C 7/28 - Arrangement of seals

Abstract

A turbine shroud (46) for a gas turbine engine (10) includes a metallic support ring (48) and a ceramic blade track (50). The support ring is an annular component including an outer carrier (54) and an inner carrier (56) made up of a plurality of inner carrier segments (57). The blade track is formed from a plurality of blade track segments (51) including dovetail posts (61, 62). The dovetail posts are inserted through apertures (91, 92) in the support ring and are coupled to the support ring by segment retainers (52) coupled to the dovetail posts providing a retention system for the ceramic blade track.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator

Abstract

One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.

IPC Classes  ?

• F01D 25/08 - CoolingHeatingHeat insulation
• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

An improved retention pin assembly (50) and method of forming a pin assembly (50) that uses a melt in a pocket (80) without a metallurgical joint having been formed. The assembly (50) can be generated by a method of forming a joint which includes providing a metal shaft (74) and a member (66) that is operable to receive the shaft (74). A pocket (80) is formed within the member (66) which operates to receive a melt pool. Next the shaft (74) is inserted into apertures (70) in the member (66). A welding or melting operation is then performed to create a melted portion that occupies the pocket (80). A joint is created using a retention pin (72).

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• B21J 15/08 - Riveting by applying heat to the end parts of the rivets to enable heads to be formed
• F02C 7/28 - Arrangement of seals

Abstract

A system (10) for removing oxygen from a fuel is provided including a pressurized gas lumen (22) and a liquid transport lumen (16) having a fuel separation device (32). The liquid transport lumen (16) is positioned partially within the pressurized gas lumen (22) and includes a plurality of openings (20) formed along its length within said pressurized gas lumen (22). A shearing feature (28) is formed within the liquid transport lumen (16) and is positioned downstream of the openings (20) and upstream of the fuel separation device (32). The gas enters the liquid transport lumens (16) through the openings (22)to form a plurality of bubbles removing oxygen from the fuel. The shearing feature collapses the bubbles into larger bubbles prior to flow into the fuel separation device (32).

IPC Classes  ?

• B01D 19/00 - Degasification of liquids

Abstract

A combustor assembly for a gas turbine engine (10) includes a hanger (62) and a combustor liner (52) fixed to the hanger such as, for example, by an annular weld joint (72). The combustor liner has an inner surface (56) extending along an axis (16) and is operable to define either a radial outer boundary or a radial inner boundary of the combustion chamber. The combustor assembly also includes a heat shield (76) at least partially overlapping and confronting the inner surface of the combustor liner along the axis, with the heat shield releasably engaged with the hanger.

IPC Classes  ?

• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
• F23R 3/60 - Support structuresAttaching or mounting means

Abstract

A composite component includes a bonded portion and a component mount. The component mount is coupled to the bonded portion to move relative to the bonded portion. The bonded portion includes a fiber portion and a ceramic portion.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts

Abstract

A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.

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 combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.

IPC Classes  ?

• F23R 3/06 - Arrangement of apertures along the flame tube
• F23R 3/04 - Air inlet arrangements

Abstract

A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed. The method includes fabricating an airfoil preform that has a slotted forward end and a continuous trailing end. The slotted forward end of the airfoil preform is coupled to an airfoil core insert. A ceramic matrix composite covering is applied to cover the slots of the airfoil perform. The continuous trailing end of the airfoil preform is removed to expose the slots. A gas turbine engine airfoil is also disclosed.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like

Abstract

A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

An exemplary nozzle having a variable internal exhaust area for a gas turbine engine can have a plurality of flap trains extending around a periphery of the gas turbine engine. Each flap train can include a convergent flap pivotally attached to an engine body and a divergent flap pivotally attached to the engine body downstream of the convergent flap. The nozzle can further have a fluid circuit in communication with the convergent and divergent flaps and configured to pivot the convergent and divergent flaps between a radially inward position and a radially outward position.

IPC Classes  ?

• F02K 1/12 - Varying effective area of jet pipe or nozzle by means of pivoted flaps
• F02K 1/15 - Control or regulation

Abstract

A cooling system for an aircraft includes a first cooling circuit (702) having a first evaporator (706) and a second evaporator (708), and a second cooling circuit (704) having a third evaporator (712) and a fourth evaporator (714). One of the first and second cooling circuits (702,704) includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• F25B 9/06 - Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using expanders

Abstract

A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes. One aspect is the ability to provide variable cooling that can be controlled by various devices. The variable cooling features can be used with devices such as cooled turbine components like vanes and/or blades. Devices can be used to reconfigure the performance and/or operability of a gas turbine engine.

IPC Classes  ?

• F02C 9/48 - Control of fuel supply conjointly with another control of the plant
• B64D 31/04 - Initiating means actuated personally

Abstract

A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.

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 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages

Abstract

A flight vehicle (10) includes a fuselage (12) and a gas turbine engine (14). The gas turbine engine is coupled to the fuselage to provide thrust when air surrounding the flight vehicle is admitted to the gas turbine engine and combusted with fuel. The flight vehicle further includes a generator (16) coupled to the gas turbine engine to provide power to equipment included in the vehicle.

IPC Classes  ?

• B64D 27/20 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

Abstract

Embodiments may include an actuation system for an exhaust nozzle of a gas turbine engine. The actuation system may comprise a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions. Each of the plurality of divergent flaps may extend from a respective one of the plurality of convergent flaps. The system may further include a first sync ring rotatably carried by an engine body and configured to synchronously move the divergent flaps between the first and second divergent positions and a second sync ring rotatably carried by the engine body and configured to synchronously move the convergent flaps between the first and second convergent positions. A method may translate rotation of the sync ring to movement of a vehicle surface between radially outward and inward positions.

IPC Classes  ?

• F02K 1/12 - Varying effective area of jet pipe or nozzle by means of pivoted flaps
• F02K 1/15 - Control or regulation

Abstract

An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.

IPC Classes  ?

• F02K 1/12 - Varying effective area of jet pipe or nozzle by means of pivoted flaps
• F02K 1/82 - Jet pipe walls, e.g. liners
• 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
• F02K 3/077 - 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 the plant being of the multiple flow type, i.e. having three or more flows

Abstract

A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
• B64C 27/68 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
• B64C 27/24 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
• F01D 7/02 - Rotors with blades adjustable in operationControl thereof having adjustment responsive to speed
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes
• F02K 1/18 - Control or regulation automatic

Abstract

The present disclosure includes a turbine vane assembly formed by a plurality of vane segments (21), the assembly comprising a vane (22) made from ceramic matrix composite material having an outer wall (30) extending between a leading edge (22a) and a trailing edge (22b) and between a first end (22c) and an opposing second end (22d). An endwall (25, 26) made at least partially from a ceramic matrix composite material configured to engage the first end of the vane, and a retaining region (41) including corresponding bi-cast grooves (33, 38, 40, 51) formed adjacent the first end of the vane and a receiving aperture (34, 37) formed in the endwall, wherein a bond is formed in the retaining region to join the vane and endwall together.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating

Abstract

One embodiment of an engine may include an enclosure surrounding an engine having an engine centerline, and the enclosure defining a passage for a cold-side airflow. The engine may also include one or more contiguous heat exchangers having a cold side inlet surface receiving a cold-side airflow. The heat exchanger may be disposed within the passage, such that a surface normal relative to the cold side inlet surface is offset by at least 30 degrees from the engine centerline.

IPC Classes  ?

• F01D 25/12 - Cooling
• 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 7/12 - Cooling of plants
• 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 sealing assembly includes a support, an engine component, and a seal. The engine component is mounted relative to the support to define a gap between the engine component and the support. The seal is arranged between the support and the engine component to block gasses from passing through the gap. The seal is adapted to compress and expand to fill the gap during expansion and contraction of the adjacent components that occurs during operation of a gas turbine engine including the sealing assembly. The seal includes a mount ring, a ceramic tadpole gasket and retainer ring.

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F02C 7/28 - Arrangement of seals

Abstract

A method of operating a gas turbine engine may include operating a starter motor to rotate a spool of the gas turbine engine; determining a torque of the starter motor during rotation of the spool; and controlling the rotation of the spool based on the torque.

IPC Classes  ?

• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F01D 19/00 - Starting of machines or enginesRegulating, controlling, or safety means in connection therewith
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A gas turbine engine includes a centrifugal compressor having an improved impeller structure. The impeller structure includes a near axial discharge configuration thus reducing the overall size of the envelop surrounding the compressor assembly. The impeller structure may have axial exit vanes.

IPC Classes  ?

• F04D 17/02 - Radial-flow pumps specially adapted for elastic fluids, e.g. centrifugal pumpsHelico-centrifugal pumps specially adapted for elastic fluids having non-centrifugal stages, e.g. centripetal
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F04D 29/28 - Rotors specially adapted for elastic fluids for centrifugal or helico-centrifugal pumps
• F04D 29/30 - Vanes
• 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

Abstract

A system for controlling operation of an aircraft engine includes a master controller, a control node coupled to a component of the aircraft engine and to the master controller, wherein the control node includes a computing device for performing diagnosis of the component. The computing device is configured to assess performance of the component during operation of the aircraft, determine whether the component is performing within specification, and if not performing within specification, indicate that the component is out of specification.

IPC Classes  ?

• G05B 19/406 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by monitoring or safety
• G05B 23/02 - Electric testing or monitoring

Abstract

A real-time gas turbine management system includes a controller system coupled to a gas turbine engine. The controller system is configured to control demand on a first and second component of a gas turbine engine. The controller system is configured to identify a set point reference of the first component, identify a set point reference of the second component, and identify a data set indicative of a level of deterioration of the gas turbine engine. The controller system is also configured to change the set point reference of the first component to extend a lifespan of the gas turbine engine and/or change the set point reference of the second component to extend the lifespan of the gas turbine engine.

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring

Abstract

An aircraft 1 is provided with a gas turbine engine 20 having a plurality of shafts. A first output shaft 32 provides power to an electrical machine 40 and a propeller 50, while a second output shaft 33 provides power to a refrigerant compressor 70. The refrigeration system may be integrated to the propeller, like a ducted fan, or on the outer skin of the aircraft.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B64D 27/02 - Aircraft characterised by the type or position of power plants
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

A gas turbine engine variable porosity combustor liner (42) has a laminated alloy structure. The laminated alloy structure has combustion chamber (44) facing holes (110) on one side and cooling plenum (72) facing holes (112) on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages (114) sandwiched between metal alloy sheets (100, 102) of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

IPC Classes  ?

• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
• F23R 3/06 - Arrangement of apertures along the flame tube

Abstract

A real-time engine management system having a controller system configured to control demand on a first component of an engine. The controller system is also configured to access a first set of prognostic data about the first component, where the first set of prognostic data includes a remaining lifespan approximation of the first component operating at a present operating condition. The controller system is also configured to identify a temporal length of an engine procedure operating at the present operating condition, alter a current limit constant associated with the first component to increase the remaining lifespan approximation of the first component beyond the temporal length, and implement the current limit constant associated with the first component so that the first component does not fault during the engine procedure.

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring

Abstract

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

IPC Classes  ?

• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct.

IPC Classes  ?

• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
• F02C 7/14 - Cooling of plants of fluids in the plant

Abstract

One embodiment of the present disclosure is a unique active seal system. Another embodiment is another unique active seal system. Another embodiment is a unique method for operating a turbomachine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for active seal systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• 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

In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface. A corresponding method of manufacturing is also provided.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
• F01D 25/08 - CoolingHeatingHeat insulation

Abstract

A cooling system comprising: a component (128) having an inner wall (130) and an outer wall (132) spaced apart from one another; a plurality of pedestals (138) extending between the inner and outer walls; a plurality of inner trip strips (134) projecting from the inner wall towards the outer wall at a predetermined height; a plurality of outer trip strips (136) projecting from the outer wall towards the inner wall at a predetermined height, wherein one of either an inner trip strip or an outer trip strip extends between adjacent pedestals; at least one inlet through aperture (118) formed in the inner wall of the component operable for transporting a cooling fluid into a space between the inner and outer walls of the component; and a plurality of outlet through apertures (116) formed in the outer wall of the component operable for transporting the cooling fluid out of the space between the inner and the outer walls of the component; wherein at least one of the inlet through apertures and outlet through apertures is located in one of an inner well and an outer well, respectively, wherein the inner well is bounded on all sides by a plurality of inner trip strips, and wherein the outer well is bounded on all sides by a plurality of outer trip strips.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 25/12 - Cooling

Abstract

A cooling system includes a heat exchanger (210) through which a refrigerant flows, and which rejects heat to a fluid, an evaporator (208), a first circuit having an expansion device (214), a second circuit having an expansion machine (202) coupled to a compressor (204), and a set of valves (218) arranged to direct the refrigerant through the first circuit, the second circuit, or both the first and second circuits based on ambient conditions.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• F25B 9/06 - Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using expanders

Abstract

One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and electrical systems.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F02C 9/00 - Controlling gas-turbine plantsControlling fuel supply in air-breathing jet-propulsion plants
• H02J 9/06 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over

Abstract

A control for a turbine engine using electrical machines monitors engine health and allocates power extraction between the electrical machines.

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
• G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
• G05B 13/04 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
• G05B 23/02 - Electric testing or monitoring

Abstract

A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post (42), an insert (44), and a braze layer (46) coupling the insert to the ceramic post. The ceramic post (42) includes a body (52) adapted to be coupled to a turbine engine component and a head coupled to the body. The insert (44) is arranged in a space formed in the head (54) and the braze layer extends from the ceramic post to the insert to bond the insert to the ceramic post.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/30 - Fixing blades to rotorsBlade roots

Abstract

An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.

IPC Classes  ?

• 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
• 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

One embodiment of the present disclosure is a unique system. Another embodiment is a unique fastener system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, fastener systems and other systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02K 1/04 - Mounting of an exhaust cone in the jet pipe
• F02C 7/20 - Mounting or supporting of plantAccommodating heat expansion or creep
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting

Abstract

A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

IPC Classes  ?

• F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.

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
• F02C 7/12 - Cooling of plants

Abstract

An aircraft, comprising: a wing; a fuselage coupled to the wing; an engine (34) coupled to at least one of the fuselage and the wing; an electrical load (20) associated with the aircraft during flight operations; a generator (32) coupled to the engine and configured to generate electrical power for the electrical load; a conductor (38) electrically disposed between the electrical load and the generator; a conduit (46) configured to house the conductor; and a dielectric gas (44) disposed in the conduit; wherein the conduit (46) is configured to envelop the conductor (38) in the dielectric gas (44).

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes
• H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc

Abstract

Gas turbine engine (10) having a cold section comprising a fan (12) and/or a compressor (16), a combustor (20) and a turbine (22), the fan, compressor and turbine having blades (34) surrounded by a shroud (36), and an electrical machine (24) for generating electrical power, the electrical machine having a stator (60) positioned adjacent to or within the shroud and a rotor (62) having rotor tips positioned proximate to the stator and in a different axial location than the blades.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• 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 7/18 - Composite ram-jet/rocket engines

Abstract

An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 5/32 - Locking, e.g. by final locking-blades or keys

Abstract

A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate. An anti-rotation peg has a radially oriented tab for engaging the split ring so as to control the rotation of the ring. The system may be used to balance the operating condition of a turbo machine.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 5/30 - Fixing blades to rotorsBlade roots
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

An aircraft may have a heat generating component and an engine, at least one of which generates a heat load, and a thermal management system to cool the heat load. The engine may have a duct and an engine fan configured to draw an inlet air stream into an inlet portion of the duct, where at least a portion of the inlet air stream may be used as an engine air stream. The thermal management system may include a cooling circuit configured to circulate a fluid through the heat load such that at least a portion of it may be transferred to the fluid, a heat exchanger configured to enable heat transfer between the fluid and a cooling air stream, and a pumping device. The pumping device may be configured to draw the cooling air stream through the heat exchanger and into a portion of the engine air stream.

IPC Classes  ?

• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
• F02C 7/14 - Cooling of plants of fluids in the plant

Abstract

A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components. The assembly is finally rigidised.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor. Cooling is more efficient in part due to the dual wall construction and in part due to reduced parasitic leakage, and the design is less sensitive to attachment features which operate at lower temperatures.

IPC Classes  ?

• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
• F23R 3/60 - Support structuresAttaching or mounting means

Abstract

One embodiment of the present disclosure is a unique gas turbine engine having a bearing system, or a damper system, or a sealing system, and a corresponding method of operating the engine. Another embodiment is a unique rotor machine. Desired clearances are maintained in the engine and rotor and by the method. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for rotor machines, such as but not limited to, gas turbine engines.

IPC Classes  ?

• F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
• F02C 7/06 - Arrangement of bearingsLubricating
• F16C 25/06 - Ball or roller bearings
• F01D 5/10 - Antivibration means
• F01D 25/04 - Antivibration arrangements
• F04D 29/66 - Combating cavitation, whirls, noise, vibration, or the likeBalancing
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F01D 11/24 - Actively adjusting tip-clearance by selectively cooling or heating stator or rotor components
• F02C 7/28 - Arrangement of seals
• F16C 37/00 - Cooling of bearings
• F04D 29/059 - Roller bearings
• F16C 19/52 - Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F04D 29/10 - Shaft sealings

Abstract

A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller. The radial diffuser assembly includes a first arcuate wall and a second wall, and a near axial diffuser coupled to the radial diffuser assembly and positioned to receive the compressed air from the radial diffuser assembly. The gas turbine includes a gas seal coupled between the second wall and a wall of the near axial diffuser, the gas seal configured to prevent the compressed air from passing through the seal while allowing relative motion between the radial diffuser assembly and the near axial diffuser.

IPC Classes  ?

• F04D 29/08 - Sealings
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F04D 29/44 - Fluid-guiding means, e.g. diffusers

Abstract

A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

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 27/00 - Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• 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
• F16J 15/32 - Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
• F04D 27/02 - Surge control

Abstract

A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.

IPC Classes  ?

• F04D 29/44 - Fluid-guiding means, e.g. diffusers
• 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
• F04D 29/62 - MountingAssemblingDisassembling of radial or helico-centrifugal pumps

Abstract

A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.

IPC Classes  ?

• F01D 5/08 - Heating, heat-insulating, or cooling means
• F04D 29/053 - Shafts
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F04D 29/58 - CoolingHeatingDiminishing heat transfer

Abstract

A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments (64,66) which are coupled to a rotatable ring, or rings (68,70), are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments (64,66) can be rotated through the ring, or rings (68,70), between a first position associated with the first vane (60) and a second position associated with a second vane (62) to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments (64,66) can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

A gas turbine engine (50) is disclosed which includes a bypass passage (58) that in some embodiments is capable of being configured to act as a resonance space. The resonance space can be used to attenuate or accentuate a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. In one form the resonance space can attenuate a noise forward of the bypass duct. In another form the resonance space can. attenuate a noise aft of the bypass duct.

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
• 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 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 gas turbine engine component includes an insulating coating that is adhered to a surface of the component that permits the components to operate at higher temperatures with reduced thermal stress. The coating can be selectively applied to one or more portions of a part feature where, in some embodiments, the part feature may include a portion that does not include the coating. The part feature can include recognized features of a component such as an interior surface of a hollow component, a back side of a blade track, a cooling hole passage, etc.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud.

IPC Classes  ?

• 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 shroud for a gas turbine engine includes an annular metallic carrier(48), a ceramic blade track (50), and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection (54) is formed between the annular metallic carrier and the ceramic blade track to locate the ceramic blade track relative to the annular metallic carrier. The cross- key connection includes a plurality of keys (56) and a plurality of corresponding keyways (58).

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• 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 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines with heat exchange systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02C 7/224 - Heating fuel before feeding to the burner

Abstract

One embodiment of the present invention is a unique dome panel for a gas turbine engine combustor. Another embodiment is a unique gas turbine combustor. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and combustion systems and components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• 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

One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor. The thermoelectric device can be used in some forms to harvest power derived from a waste heat. The tip clearance control system can include a sensor used to determine a clearance between a tip and a wall of the turbomachinery component.

IPC Classes  ?

• F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing

Abstract

A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor. The thermoelectric device can be used in some forms to harvest power derived from a waste heat. The tip clearance control system can include a sensor used to determine a clearance between a tip and a wall of the turbomachinery component.

IPC Classes  ?

• F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing

Abstract

One embodiment of the present invention is a unique platform. Another embodiment is a unique engine system. Another embodiment is a unique wiring harness system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for one or more of various types of platforms, such as aircraft, ground vehicles, water-borne vessels and stationary platforms; engine systems; and wiring harness systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• B60R 16/023 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for transmission of signals between vehicle parts or subsystems

Abstract

An electric machine is disclosed integrated to rotate with a shaft of a gas turbine engine. In one form the electric machine is integrated with a fan of the gas turbine engine. A rotor of the electric machine can be disposed at the end of the fan blades and the stator integrated into a flow path forming surface of the gas turbine engine. In one form the windings of the electric machine can change configuration permitting some windings to be placed in parallel with one or more other windings, and then connected together in series with remaining windings, if any. The voltage of the electric machine can change as a result of a change in configuration of the windings.

IPC Classes  ?

• H02K 1/32 - Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
• H02K 47/00 - Dynamo-electric converters
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02K 16/00 - Machines with more than one rotor or stator
• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use

Abstract

One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• B60H 1/00 - Heating, cooling or ventilating devices

Abstract

A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source. The port cover extends circumferentially around the gas turbine engine and can include a portion that is anchored and an opposite portion coupled to an actuator. Movement of the actuator causes the port cover to open and close the port. Biasing members can be used to urge the port cover into one of an open and closed position against the movement of the actuator.

IPC Classes  ?

• F02C 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages
• F02C 7/268 - Starting drives for the rotor
• F02C 7/28 - Arrangement of seals
• 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
• F02C 9/52 - Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid

Abstract

An apparatus including an internal combustion engine receiving air from an air particle separator is disclosed. The air particle separator has an air intake capable of receiving air and a particulate matter conveyed by the air, the particle separator being capable of filtering the particulate matter from the air to produce a clean flow and a dirty flow. The clean flow is provided to the inlet of the internal combustion engine. The bladed component rotates about an axis and has an annular construction disposed radially outward of the plurality of members configured to receive a circumferential force to cause the bladed component to rotate about the axis.

IPC Classes  ?

• B01D 45/00 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces

Abstract

A blade track assembly is disclosed having a variety of features. The assembly can have annular or segmented components, or a combination of the two. In one form the assembly includes blade tracks having a forward and aft edge that can be received in an opening of respective hangers. The hangers can include anti- movement features to discourage movement of a blade track. A rib can extend between hangers and in one form can be used as part of a seal assembly. Clips can be used to secure the blade track in openings of the respective hangers, as well as to discourage movement of the blade track.

IPC Classes  ?

• F04D 27/02 - Surge control
• 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 25/08 - CoolingHeatingHeat insulation
• F01D 5/14 - Form or construction

Abstract

Embodiments of the present invention include unique gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. In one form, gas turbine engine 10 is an aircraft propulsion power plant. In other embodiments, gas turbine engine 10 may be a land-based or marine engine.

IPC Classes  ?

• F02K 3/00 - Plants including a gas turbine driving a compressor or a ducted fan

Abstract

One embodiment of the present invention is a unique turbine blade for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbine blades for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
• B63H 1/26 - Blades

Abstract

One embodiment of the present invention is a unique gas turbine engine system. Another embodiment is a unique exhaust nozzle system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine systems and exhaust nozzle systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F01B 25/00 - Regulating, controlling or safety means
• 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
• F02C 7/24 - Heat or noise insulation

Abstract

A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.

IPC Classes  ?

• F02C 7/12 - Cooling of plants

Abstract

A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a. third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.

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

Abstract

One embodiment of the present invention is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for employing continuous detonation combustion processes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect

Abstract

An aircraft having a cooling system is disclosed. The cooling system can he used to cool a heat emitting component In one form the cooling system is a refrigerant system and includes a relatively high temperature device such as, but not limited to, a condenser. The relatively high temperature component is placed In thermal communication with a passing air flow. In one embodiment the aircraft includes a pod in which at least a portion of the cooling system is disposed. For example, a condenser of a vapor cycle refrigerant system can be located in the pod and in thermal communication with the air flow. The cooling system can also include a device capable of delivering a cooling fluid into the air flow and/or to the relatively high temperature component. The cooling fluid can he evaporated to provided additional cooling.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant

Abstract

A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

IPC Classes  ?

• F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use

Abstract

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique reheat system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and reheat systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02C 3/16 - 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 the combustion chambers being formed at least partly in the turbine rotor

Abstract

One embodiment of the present invention is a unique gas turbine engine combustion finer. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices,, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion liners. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02C 1/00 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid

Abstract

One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

IPC Classes  ?

• C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
• C23C 18/00 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating
• C23C 26/02 - Coating not provided for in groups applying molten material to the substrate

Abstract

One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

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

One embodiment of the present invention is a unique flight vehicle. Another embodiment is a unique propulsion system. Another embodiment is a unique thrust vectoring system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for flight vehicles, propulsion systems and thrust vectoring systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02K 1/40 - Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet

Abstract

One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers

Abstract

One embodiment of the present invention is a unique variable camber vane system for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and variable camber vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

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

Abstract

One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

IPC Classes  ?

• B32B 3/06 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers togetherLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
• B32B 5/14 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by a layer differing constitutionally or physically in different parts, e.g. denser near its faces

Abstract

A system includes a turbine engine with a fueling system including a valve fluidly coupled to a fuel supply on an upstream side and fluidly coupled to fueling passages on a downstream side. The valve maintains the fuel supply at a pressure greater than an ambient pressure. The system includes nozzle exits corresponding to the fueling passages, and the fueling passages flow fuel from the valve to each of the nozzle exits monotonically downward. The valve is a check valve or a controlled valve. The valve maintains the fuel supply at a pressure such that fuel in the fuel supply is a continuous fluid phase. The fuel leaves the nozzle exits to the combustion chamber of the turbine engine.

IPC Classes  ?

• F02C 7/22 - Fuel supply systems

Abstract

One embodiment of the present invention is a unique engine Another embodiment of the present invention is a unique combustion system, Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02C 3/02 - Gas-turbine plants characterised by the use of combustion products as the working fluid using exhaust-gas pressure in a pressure exchanger to compress combustion-air

Abstract

A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button.

IPC Classes  ?

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

Abstract

One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for pulse detonation combustion systems, gas turbine engines, and other machines and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

IPC Classes  ?

• F02C 5/00 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion