Abstract: A turbine stationary blade is a turbine stationary blade that includes: a blade body; and a shroud formed in an end portion of the blade body in a blade height direction. The shroud includes: a bottom plate in contact with a combustion gas flow passage; a peripheral wall formed in the blade height direction and along a peripheral edge of the bottom plate; a recess forming a space surrounded by the peripheral wall and the bottom plate; a plurality of partition ribs connecting the blade body and the peripheral wall, dividing the recess into a plurality of spaces, and forming a plurality of cavities; and an impingement plate dividing the space into an outer cavity formed on an outer side in the blade height direction and an inner cavity formed on an inner side of the outer cavity, and having a plurality of through holes via which the outer cavity and the inner cavity communicate with each other.

Abstract: An aircraft propulsion system includes a series of condensers where water is condensed from the exhaust gas flow. Each of the series of condensers define a passage for exhaust gas flow such that water recovered from the exhaust gas flow drains at a downward angle in a direction of gravity through each of the series of condensers. A series of water separators separate the exhaust gas flow from water condensed in a corresponding one of the series of condensers and the water is transformed into a steam flow in an evaporator system for communication to the combustor.

Abstract: An assembly for an aircraft includes an aircraft housing, an auxiliary power unit (APU), an oil system, a door actuator, and a controller. The aircraft housing forms a compartment. The aircraft housing includes an intake door. The intake door is movable between a closed position, an open position, and intermediate positions between the closed position and the open position. The APU is disposed within the compartment. The APU includes an engine. The engine includes an air inlet and a rotational assembly. The oil pump is operatively connected to the rotational assembly. The door actuator is operatively connected to the intake door. The door actuator is operable to position the intake door in the closed position, the open position, and the intermediate positions to control an ambient air flow to the air inlet. The controller is operatively connected to the door actuator.

Abstract: A powerplant is provided for an aircraft. This aircraft powerplant includes a turbine engine core, a steam system and a bypass system. The turbine engine core includes a flowpath, a compressor section, a combustor section and a turbine section. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The steam system includes an evaporator disposed along the flowpath downstream of the turbine section. The steam system is configured to evaporate water into steam using the evaporator. The steam system is configured to introduce the steam into the flowpath upstream of the turbine section. The bypass system is configured to bleed fluid from the flowpath upstream of the turbine section to provide bleed fluid. The bypass system is configured to direct the bleed fluid into the flowpath downstream of the evaporator.

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Abstract: A fuel injector for a gas turbine engine combustor is provided that includes a swirler, a mounting stage, and a distributor. The swirler has a shaft, a collar, a throat section, and first and second axial ends. The throat section includes an inner radial surface that defines a central passage that extends between the swirler inner bore and the collar. The collar includes a plurality of apertures extending therethrough disposed radially outside of the central passage. The mounting stage is disposed in the inner bore, and has an annular flange, a central hub, and at least one strut. The distributor has a stem attached to a head. The stem has a distal end opposite the head portion engaged with the central hub. The head portion has an end surface and a side surface. The distributor is selectively positionable relative to the throat section.

Abstract: Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.

Abstract: An inlet system for an auxiliary power unit includes an inlet duct, and a frame coupled about the inlet duct. The frame defines an opening configured to be in fluid communication with the inlet duct. The inlet system includes a door having a first end opposite a second end. The door is coupled to the frame at the second end. The door is configured to move relative to the frame between a first position in which the door cooperates with the frame to inhibit airflow into the inlet duct and a second position in which the door is configured to enable the airflow into or out of the inlet duct. The door defines a ramp at the second end. A hook is spaced a distance apart from the ramp to define a gap configured to enable the airflow into or out of the inlet duct in the second position.

Abstract: A support assembly for supporting a main accessory gearbox of an aircraft turbine engine, the accessory gearbox including gears and supporting at least one item of equipment driven by the gears. The support assembly can include a structure for connecting and supporting the turbine engine to a pylon of the aircraft including: an intermediate axial portion for attachment to the pylon, having an upper end that defines a linking interface with the pylon, the intermediate axial portion bearing suspension rods, which are intended to be connected to the turbine engine; a front axial portion extending forward of the intermediate portion and having at least one suspension member configured to be connected to the turbine engine; and a rear axial portion extending rearwards of the intermediate portion and supporting the main accessory gearbox.

Abstract: A method for testing a hybrid power plant equipping a rotary-wing aircraft comprising at least one lift rotor, the hybrid power plant being configured to rotate the at least one lift rotor, the hybrid power plant comprising at least one heat engine configured to rotate the at least one lift rotor; and at least one electric motor supplied with electrical energy by at least one electrical power source, the at least one electric motor being configured to rotate the at least one lift rotor at least when at least one of the at least one heat engine fails.

Abstract: Examples described herein provide a method for restarting an engine of an aircraft during a flight of the aircraft. The method includes detecting a shutdown of the engine. The method further includes setting a flag to prevent a quick-relight situation. The method further includes performing an auto-relight procedure to attempt to restart the engine. The method further includes, responsive to determining that the auto-relight procedure failed to restart the engine, selectively performing at least one of a windmilling restart of the engine or a starter assist restart of the engine.

Abstract: A vertical type once-through heat recovery steam generator (HRSG) capable of improving operational stability during rapid startup and lifetime of a steam turbine while reducing environmental pollution caused by emissions, and a combined power generation system including the HRSG are provided. The HRSG includes a medium-pressure section including a medium-pressure side desuperheater installed at the rear of a medium-pressure superheater to lower the temperature of the steam supplied to a medium-pressure steam turbine, and a high-pressure section including a high-pressure side desuperheater installed at the rear of a high-pressure superheater to lower the temperature of the steam supplied to a high-pressure steam turbine.

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, an engine housing, an evaporator, a condenser and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The engine housing includes a cavity radially outboard of and axially overlapping the fan section and/or the bypass flowpath. The evaporator module is within the cavity. The condenser module is within the cavity. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a fuel injector assembly, and the fuel injector assembly includes an inner air swirler and a fuel swirler. The inner air swirler is configured to swirl inner air in a direction about an axis to provide inner swirled air. The fuel injector assembly is configured to inject the inner swirled air as an inner air flow along an inner air flow trajectory parallel with the axis. The fuel swirler is configured to swirl fuel in the direction about the axis to provide swirled fuel. The fuel injector assembly is configured to inject the swirled fuel as an annular fuel flow along a fuel flow trajectory parallel with the axis. The annular fuel flow is adjacent and circumscribes the inner air flow.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: An aircraft turbomachine includes a lubricating circuit notably including a reservoir of lubricating fluid, a pump drawing lubricating fluid from the reservoir to inject it toward several components of the turbomachine, and an intake pipe connecting the reservoir to an intake orifice of the pump, the turbomachine further including a pneumatic starting circuit including a starting tube through which there circulates a flow of compressed air intended to supply a pneumatic starter of the turbomachine, wherein it includes a pneumatic line extending from the starting tube as far as the reservoir so as to supply the reservoir with compressed air so as to cause the lubricating fluid to circulate through the intake pipe towards the pump.

Abstract: Dissimilarly shaped aircraft nozzles with tandem mixing devices, and associated systems and methods are disclosed. An ejector nozzle in a representative embodiment includes a nozzle duct having a nozzle flow axis, a first axial position and a second axial position. The nozzle duct has a first cross-sectional shape at the first axial position, and a second cross-sectional shape at the second axial position, with the second shape being geometrically non-similar to the first shape. The nozzle further includes a fan flow duct portion and a core flow duct portion, both upstream of the first axial position. An ejector duct is positioned in fluid communication with the nozzle duct, and has at least one portion with a cross-sectional shape geometrically similar to the second cross-sectional shape.

Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes an exhaust nozzle extending circumferentially about an axial centerline. The exhaust nozzle extends axially along the axial centerline to a trailing edge. The exhaust nozzle extends radially between an exterior inner surface and an exterior outer surface. The exhaust nozzle includes an inner skin, an outer skin and an internal cavity. The inner skin forms the exterior inner surface and includes a plurality of perforations. The internal cavity is disposed radially between the inner skin and the outer skin. The internal cavity is fluidly coupled with the perforations.

Abstract: Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen, which includes a plurality of mixing tubes through which air and fuel flow, and a multi-tube configured to insert the mixing tubes thereinto and support the same, wherein each of the mixing tubes has an inlet formed at a longitudinal end thereof for introduction of a first fluid, and a plurality of supply ports formed on a circumferential surface thereof for introduction of a second fluid, the mixing tube has a plurality of first supply ports formed on a first surface thereof, and a plurality of second supply ports formed on a second surface facing the first surface, and the first supply ports are staggered with the second supply ports.

Abstract: The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.