Abstract: An aircraft propulsion system includes a compressor section where an inlet airflow is compressed, a combustor section where the compressed inlet airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path, a turbine section through which the exhaust gas flow expands to generate a mechanical power output, the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow, and a condenser where water is extracted from the second exhaust gas flow, and a first heat exchanger where at least a portion of the extracted water is utilized for cooling a core flow along the core flow path.

Abstract: A fuel system includes a main fuel pump sub-system (MFP) with an inlet for receiving a supply of fuel from an inlet line. The MFP has a main outlet line configured to supply fuel to a main fuel throttle valve assembly (MFTV), and a cross-over outlet line. An augmentor fuel pump sub-system (ABFP) has an inlet connected in fluid communication with the cross-over outlet line, and an outlet connected in fluid communication with a main augmentor supply line. A actuation fuel pump sub-system (AFP) has an inlet connected in fluid communication with a branch of the main outlet line, an outlet line with a first outlet line branch configured to connect to supply fuel to the MFTV, and a second outlet line branch configured to connect to supply fuel to an actuation system.

Abstract: A temperature measurement system for a gas turbine engine, the gas turbine engine including, in axial flow sequence, a compressor section, a combustor section having plural fuel spray nozzles, and a turbine section. The temperature measurement system includes one or more optical thermometers, each optical thermometer configured to measure the temperature of a component washed by the working gas of the engine, the or each component being in the combustor section or the turbine section at a first position along the axis of the engine.

Abstract: An aircraft engine comprises a rotating component and a reduction gearbox connected thereto. A rotating shaft extending along an axis is coupled to the gearbox. A thrust bearing disposed in a bearing housing extends around the shaft and supports the shaft. The bearing housing defines a piston chamber. A piston therein axially secured to the shaft and in sealing engagement with the bearing housing divides the chamber into two cavities. The piston has opposite first and second axial faces exposed to respective cavities. The first face faces axially away from the thrust bearing. A compressed air source is in fluid communication with the first cavity with air at a first pressure exerting a first force against the first axial face. The second cavity is at a second pressure exerting a second force against the second axial face. The first force is greater than the second.

Abstract: A delay time calculation method includes: a step of calculating a plurality of segment movement delay times respectively indicating times required for the fuel gas to pass through a plurality of segments; a step of calculating a total movement delay time which is a time required for the fuel gas to move through the fuel line from the measurement point to the supply target device, by adding up the plurality of segment movement delay times; and a step of acquiring the delay time based on the total movement delay time. The step of calculating the plurality of segment movement delay times includes acquiring the segment movement delay time based on a correlation between the segment movement delay time acquired in advance and a fuel flow rate supplied to the supply target device, for each of the plurality of segments.

Abstract: The invention relates to a blade comprising a shield (14) attached to the upstream end of the body of the blade, the shield (14) comprising an upstream end forming a leading edge of the blade, the shield (14) further comprising a nose (141) upstream from which the leading edge is located, an pressure-face fin and an suction-face fin laterally attached on the blade, the fins extending from the nose, the blade comprising a defrosting air passage duct (15) arranged inside the nose and extending radially inside the nose, the duct (15) having an inner end (151) emerging opposite the root (125) and a radially external end emerging from the nose between the leading edge and its junction at the pressure-face fin.

Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.

Abstract: A turbine engine including an engine core, an engine drive shaft, an accessory gear box (AGB), an air turbine starter (ATS) and a bleed air circuit. The engine core has a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The engine drive shaft operably couples the fan section, the compressor section and the turbine section. The AGB and the ATS are operably coupled to the engine drive shaft.

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.

Abstract: The object is to provide a powder fuel feed apparatus, a gasifier unit, and an integrated gasification combined cycle and a control method of a powder fuel feed apparatus that can suppress deformation of a sintered metal filter with simple and inexpensive configuration. An embodiment includes: a distributor pipe (89) in which a mixed gas containing moisture and a gas in which pulverized coal and nitrogen transported with the pulverized coal are mixed is transported; and a diluting nitrogen system (90) that, when a flow velocity of the mixed gas is less than a predetermined threshold, additionally supplies a diluting nitrogen to a mixing chamber (97) connected to the distributor pipe (89) and forming a part of the distributor pipe (89), and the diluting nitrogen system (90) continuously supplies a predetermined flow rate of the diluting nitrogen to the mixing chamber (97).

Abstract: A system is provided for an aircraft. This system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant includes a turbo-compounded intermittent internal combustion engine and a dual rotor electric machine. The turbo-compounded intermittent internal combustion engine includes a turbine rotor operatively coupled to the propulsor rotor through the dual rotor electric machine. The dual rotor electric machine includes a first rotor, a second rotor, a first stator and a second stator. The first stator and the second stator are arranged radially between and axially aligned with the first rotor and the second rotor.

Abstract: A gas turbine engine includes a propulsor having blades extending from a propulsor hub. A compressor section includes a first compressor and a second compressor. A speed reduction device includes an epicyclic gear system. The epicyclic gear system includes a sun gear, a plurality of intermediate gears, a carrier supporting the intermediate gears and the propulsor hub, and a ring gear. A turbine section includes a first turbine and a second turbine. The second turbine drives the propulsor through the epicyclic gear system. The epicyclic gear system is straddled by forward and aft bearings that engage the carrier.

Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.

Abstract: A vane assembly for a gas turbine engine which is a single unitary component that includes an aerofoil. A leading edge passageway is disposed proximal to a leading edge of the aerofoil and configured to receive a flow of a fluid therein. The vane assembly further includes a connecting passageway fluidly communicating the leading edge passageway with a trailing edge distribution passageway that is spaced apart from the leading edge, the leading edge passageway and a trailing edge of the aerofoil. The vane assembly further includes a plurality of trailing edge passageways disposed proximal to a pressure surface of the aerofoil and extending from the trailing edge distribution passageway towards the trailing edge along a chordwise direction. Each trailing edge passageway is configured to discharge the fluid through a corresponding passageway outlet disposed on the pressure surface and in fluid communication with a corresponding trailing edge passageway.

Abstract: A stator vane assembly includes a platform that defines an opening. The stator vane assembly further includes an airfoil segment that includes an airfoil and a boss. The airfoil includes a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. The boss extends from at least one of the base or the tip of the airfoil. The boss is disposed in the opening of the platform. The stator vane assembly further includes a mechanical retention device that couples the platform to the boss of the airfoil segment.

Abstract: A heat management system includes a fuel tank storing a fuel; a first heat exchanger thermally coupled to the fuel tank; a hydraulic pump for circulating a hydraulic fluid; a hydraulic circuit including first and second hydraulic lines fluidly coupled to the first heat exchanger and the hydraulic pump, such that the first heat exchanger brings the hydraulic fluid and the fuel into a heat exchange relationship; an oil circuit; and a second heat exchanger thermally coupled to the oil circuit and at least one of the first and second hydraulic lines, such that the second heat exchanger brings the hydraulic fluid and the oil into a heat exchange relationship, thereby allowing heat transfer between the fuel and the oil via the hydraulic fluid.

Abstract: An engine system includes a gas turbine engine with a first compressor, a first combustor, and first turbine. The engine system also includes a secondary power unit with a second compressor, a second combustor, a second turbine, a third compressor coupled to the second compressor, and an electric motor-generator, where the secondary power unit is coupled to the gas turbine engine and includes a heat exchanger. A controller is operable to determine an operating mode of the engine system, select an input energy source and an output type of the secondary power unit based on the operating mode, control the secondary power unit based on the input energy source and the output type as selected, detect a change in the operating mode of the engine system, and modify the input energy source and/or the output type of the secondary power unit based on the change in the operating mode.

Abstract: A combustor includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which an air hole passing through the upstream side end face and the downstream side end face is formed in the tube plate; and a fuel injector that injects fuel into air passing through the air hole. The air hole has: a bent channel that curves toward a direction orthogonal to the combustor axis toward the downstream side; and an inclined channel that is connected to the downstream side of the bent channel so as to be continuous therewith, and that extends inclining with respect to the combustor axis and opens to the downstream side end face. A fuel injection position at which the fuel injector injects fuel is located on the downstream side of the upstream end of the bent channel.

Abstract: An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.

Abstract: A scoop for an aircraft turbine engine, this scoop including a body which is movable between at least two positions, including a first position in which it is configured to capture part of a first air stream flowing in a first direction, wherein the body is movable into a second position in which it is configured to capture part of a second air stream flowing in a second direction which is opposite to the first direction, and wherein the body is mounted to move freely between the at least two positions so as to automatically adopt the first position when the first air stream flows, and to automatically adopt the second position when the second air stream flows.