Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

Abstract: A fuel injector for a multipoint injection system can include a body defining an air cavity for allowing air to flow therethrough and an interior cavity. A fuel is tube disposed at least partially within the interior cavity of the body. The fuel tube can include a first end configured to connect to a fuel injector connector of a fuel manifold, and a second end configured to connect to a fuel distributor of the fuel injector, wherein the fuel injector is configured to be disposed at least partially in a combustor dome. The fuel tube is configured to move in an axial direction to allow flexibility between the fuel manifold and the combustor dome.

Abstract: High-pressure fan duct bleed air is used to pressurize a cavity between the fan duct inner wall and the inner wall thermal insulation blankets. The cavity is pressurized to prevent hot air from the nacelle core compartment from flowing under the insulation blankets and degrading the fan duct inner wall. Pressure regulating valves (PRV) allow better control of the cavity pressure during different phases of the flight profile and under different levels of insulation blanket seal degradation by passively controlling exit area from the cavity based on an established pressure limit. Moreover, the pressurization system can be implemented as a passive cooling system by increasing the mass flow rate into the cavity and then the core compartment to a level suitable for core compartment cooling.

Abstract: A gas turbine engine includes a liner positioned within a compressor section or a turbine section of the gas turbine engine and at least partially defining a core air flowpath through the gas turbine engine. The gas turbine engine also includes a casing at least partially enclosing the liner. Additionally, the gas turbine engine includes a pressure sensor assembly having a body, an extension member, and a pressure sensor. The pressure sensor is positioned at least partially within the body and the body is positioned at least partially on an outer side of the casing, the extension member extending from the body through a casing opening in the casing and towards a liner opening in the liner. The extension member defines a continuous sense cavity exposing the pressure sensor to the core air flowpath.

Abstract: The present disclosure is directed to a system for mitigating rotor bow at a turbine engine. The system includes a casing circumferentially surrounding a rotor assembly in which a heat pipe is attached to the casing and extended circumferentially around the rotor assembly.

Abstract: A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.

Abstract: A thermal management system for an aircraft engine. The thermal management system extracts interstage engine bleed air from the engine's compressor and performs three stage cooling of the interstage engine bleed air using two heat exchangers and a vapor cycle system evaporator. The cooled air is then further cooled by expansion through a set of turbines and subsequently used as a heat sink for heat loads on the aircraft.

Abstract: A gas turbine engine has a nacelle providing an external skin of the engine, a casing structure radially inwards of the external skin and providing an outer surface of an air flow duct of the engine, and plural engine components located in the bay formed between the casing structure and the nacelle. The components are part of either a first set of components or a second set of components. The components of the first set are all the components from the bay which are potential ignition sources, and the components of the second set are all the remaining components from the bay. The engine further has a container located in the bay, the container being fireproof capable of withstanding the application of heat by a standard flame for 15 minutes and the container containing the components of the first set.

Abstract: The present disclosure is directed to a rotor thrust balanced turbine engine that may increase engine performance and efficiency while managing thrust mismatch or imbalance in a low pressure (LP) spool between a fan assembly and a turbine rotor assembly. The gas turbine engine defines a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a turbine rotor assembly and a turbine frame. The turbine rotor assembly defines a first flowpath radius and a second flowpath radius each extended from the axial centerline. The first flowpath radius is disposed at the upstream end of the turbine rotor assembly, and wherein the second flowpath radius is disposed at the downstream end of the turbine rotor assembly.

Abstract: In a gas turbine system which includes a compressor for sucking and compressing air and an air supplying means for supplying the compressed air from the compressor to a combustor and a turbine and which drives a power generator through rotation of the turbine, a control apparatus includes a sensing unit and a compressed air control unit. The sensing unit measures a turbine inlet temperature indicating a temperature of combustion gas introduced into the turbine and measures an exhaust gas temperature indicating a temperature of exhaust gas discharged from the turbine. The compressed air control unit control the air supplying means to adjust the amount of compressed air supplied to the turbine, based on the measured turbine inlet temperature and the measured exhaust gas temperature. The control apparatus allows the combustor to completely combust fuel even in a low load state, thereby reducing the amount of harmful exhaust gas discharged to the atmosphere.

Abstract: A combustor arrangement, the combustor arrangement being annular and being arranged about an axis, the axis defining an axial direction, having an annular housing to house a plurality of burners and an annular combustion chamber, the burners arranged circumferentially about the axis inside the annular housing, wherein an annular space is defined between the housing, the burners and the annular combustion chamber, the annular space arranged to guide a compressed fluid. A plurality of stiffening plates, each arranged within the annular housing, wherein two adjacent ones of the burners are separated by one of the stiffening plates. A combustor separating wall arrangement separates the annular space from the annular combustion chamber provides openings for the burners. The stiffening plates are arranged angled and connected to the combustor separating wall arrangement and two boundary walls of the housing, and further plates extend into the annular space.

Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

Abstract: An injector includes: an upstream support plate into which a fuel gas is to be introduced and which has a shape of a tapered cylinder with a diameter which enlarges; a downstream support plate that defines a plenum at an inner side along with the upstream support plate; and premixing tubes, each of which is supported by the upstream support plate and the downstream support plate and is configured to introduce air. The premixing tubes are disposed in circular rows at equal intervals in a circumferential direction, and portions of the premixing tubes which are located in the plenum include fuel introducing holes.

Abstract: A combustor liner assembly is provided including an inlet wall, an inner wall, an outer wall, and a plurality of fasteners. The inlet wall has an opening into a combustion chamber. The inner wall is coupled to the inlet wall at a first end of the combustor liner. The inner wall defines a radially inner end of the combustion chamber. The outer wall includes a plurality of segments. The plurality of segments define a radially outer end of the combustion chamber. A first portion of the plurality of fasteners couples each of the plurality of segments to another of the plurality of segments. A second portion of the plurality of fasteners couples at least one of the plurality of segments to the inlet wall at the first end of the combustor liner.

Abstract: A thrust reverser assembly may comprise a sleeve including an inner sleeve portion and an outer sleeve portion. A plurality of guide rails may be coupled to a radially outward surface of the inner sleeve portion. A plurality of blocker doors may be slidably coupled to the plurality of guide rails. The plurality of blocker doors may be located between the inner sleeve portion and the outer sleeve portion.

Abstract: A gas turbine engine combustor has a dome and a shell extending axially from the dome. The dome and the shell cooperates to define a combustion chamber. A dome heat shield is mounted to the dome inside the combustion chamber. A front heat shield is mounted to the shell inside the combustion chamber. The dome heat shield and the front heat shield have axially overlapping portions cooperating to define a flow guiding channel. The flow guiding channel has a length (L) and a height (h). The length (L) is at least equal to the height (h).

Abstract: Provided is a structure for bleeding gas from a chamber for receiving compressed gas from a compressor of a gas turbine engine and supplying the compressed gas to a combustor. The structure includes: a turbine casing covering an outer circumference of a turbine; an engine housing forming, between the engine housing and the turbine casing, a bleeding space that communicates with the chamber; a bleeding duct through which compressed gas in the bleeding space is guided to the outside of the engine housing; and an annular partitioning member arranged on an upstream side, relative to the bleeding duct in the bleeding space so as to separate the bleeding space from the chamber, and having a plurality of communication holes through which an upstream side and a downstream side relative to the partitioning member communicate with each other.

Abstract: A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (Ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (NTL) of a free turbine of the turbine engine.

Abstract: A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot having an inlet positioned axially between the stator vane row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; an annular array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot.

Abstract: One example aspect of the present disclosure is directed to a method for operating a gas turbine engine. One example aspect of the present disclosure is directed to a method for operating a gas turbine engine, the gas turbine engine including at least a high pressure spool and a low pressure spool. The method includes causing, by one or more control devices, electrical power to be drawn from the high pressure spool and the low pressure spool into a power distribution system. The method includes determining, by the one or more control devices, a power adjustment event associated with the high pressure spool. The method includes initiating, by the one or more control devices, a power assist operation to redirect electrical power to the high pressure spool based at least in part on the power adjustment event.