Abstract: An aircraft engine includes a core gas path through which a core gas flow flows, an exhaust duct receiving the core gas flow, an air-cooled heat exchanger disposed in a heat exchanger duct having an air inlet providing cooling air to the air-cooled heat exchanger and an air outlet in fluid communication with the exhaust duct, and a cover disposed in the heat exchanger duct downstream of the air-cooled heat exchanger. The cover is movable between an open position, in which the cover allows the cooling air to flow through the air outlet into the exhaust duct, and a closed position, in which the cover substantially blocks the air outlet. The cover is operable to move from the open position to the closed position at a predetermined temperature of the cover.

Abstract: A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.

Abstract: The disclosure provides a powerplant for an aircraft comprising: at least two gas turbine engines, and at least one closed-cycle arrangement for recuperating heat from the at least two gas turbine engines and supplying power to at least one power-demanding system, wherein the closed-cycle arrangement comprises: a closed circuit channeling a working fluid subjected to a thermodynamic cycle; at least one pre-cooler configured to transfer heat from the working fluid to a heat sink; the heat sink in thermal communication with the pre-cooler, the heat sink being a fuel tank and/or an airframe surface; at least one pumping element configured to move the working fluid through the closed circuit; at least two primary heat exchangers, each one configured to transfer heat from a respective gas turbine engine to the working fluid; at least one expanding element configured to drive a gearbox and an output shaft by the expansion of the working fluid; wherein the output shaft driven by the expanding element is connected to

Abstract: A system includes a retention system configured to support a heat exchanger along a flow path within a duct. The retention system includes a first sleeve configured to extend between opposite first and second walls of the duct, a first cable extending through the first sleeve, and a first bumper coupled to the first sleeve. The first bumper is configured to contact the heat exchanger. The retention system includes a first tensioner coupled to the first cable, wherein the first tensioner is configured to provide a first tension in the first cable. The first tension is adjustable to detune the natural frequency of the heat exchanger away from any excitation load frequencies caused by an exhaust gas flow through the duct.

Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.

Abstract: A turbine engine includes a pressurized fluid source, a duct system comprising a plurality of ducts in fluid communication with the pressurized fluid source, and a duct failure detection system. The duct failure detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is in operable communication with two ducts of the plurality of ducts. Each of the plurality of ducts has at least two pressure sensors of the plurality of pressure sensors in operable communication therewith.

Abstract: A turbine housing has: a first inner member; a second inner member contacting with the first inner member; a turbine scroll flow path enclosed and defined by the first inner member and the second inner member; a first casting housing covering the first inner member at a side opposite to the second inner member; a second casting housing covering the second inner member at a side opposite to the first inner member; an aperture formed in one or both of the first casting housing and the second casting housing and including an opening that opens to an outside; a tube member arranged in the aperture and defining an inlet flow path connected to the turbine scroll flow path; and an inner opening defined by the first inner member and the second inner member and overlapping with one end of the tube member.

Abstract: A hydraulic continuous variable transmission is provided to connect a wind turbine and a generator. The hydraulic continuous variable transmission has a primary paddle wheel and a number of secondary paddle wheels for macro speed control. Also provided are pneumatic paddle wheels for micro speed control. A controller is included that measures AC electrical characterized output to load or line for speed control.

Abstract: An exhaust gas turbine (30) for expanding exhaust gas, comprising a turbine housing (33) having an inflow housing portion (35) for exhaust gas to be expanded and an outflow housing portion (36) for expanded exhaust gas, a turbine rotor (34) received by the turbine housing (33), the turbine rotor (34) being rotatable about an axis of rotation, a metering means (42) for a reducing agent or a precursor substance of a reducing agent, wherein the reducing agent or the precursor substance can be introduced into the expanded exhaust gas via the metering device (42), and with a swirl atomizer (43), rotating together with the turbine rotor (34), for the reducing agent or the precursor substance, the reducing agent or the precursor substance being atomizable in the expanded exhaust gas via the swirl atomizer (43), the swirl atomizer (43) engaging the turbine rotor (34) at a downstream, hub-side portion of the turbine rotor (34).

Abstract: A control device is applied to an internal combustion engine equipped with an electric heating catalyst system provided with an EHC. The control device executes a preheating process to warm up an exhaust gas reduction catalyst prior to a start of the internal combustion engine by supplying electric power to the EHC, when the control device determines that a temperature of the exhaust gas reduction catalyst is lower than an activation temperature. The control device executes a determination process for determining whether water is adhered to a catalyst carrier. The control device starts the internal combustion engine without executing the preheating process when the control device determines by the determination process that water is adhered to the catalyst carrier, even when the control device determines that the temperature of the exhaust gas reduction catalyst is lower than the activation temperature.

Abstract: A system for a vehicle has an oil supply, an engine oil pump comprising a plurality of ports and an engine coupled to the plurality of ports. A turbocharger is coupled to the engine. A turbocharger oil pump is coupled to the oil supply comprising a first port coupled to the turbocharger.

Abstract: A system and method of controlling a turbocharged engine system includes receiving a boost mode selection signal and controlling the turbocharged engine system in response to the boost mode selection signal.

Abstract: A seal system includes a ceramic component that has a non-core-gaspath surface region that defines a first surface roughness and a core gaspath surface region. A metallic component is situated adjacent the non-core-gaspath surface region. A coating system is disposed on the ceramic component. The coating system includes a silicon-containing layer on the non-core-gaspath surface region and a barrier layer that has a first section on the silicon-containing layer and a second section on the core-gaspath region and that is connected to the first section. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The first section is in contact with the metallic component and the second section serves as an environmental barrier on the core-gaspath region.

Abstract: A ram air turbine rotor comprises at least one intra-flow path shroud structure coupled between rotor blades, along a radial position between a support disc and an outer rim. The shroud structure includes shroud sectors each coupled between a respective pair of blades. The sectors each include a first edge adjacent to leading edges of the respective pair of blades, the first edge including a first curved segment, and a second edge adjacent to trailing edges of the respective pair of blades, the second edge including a second curved segment. The curved segments are each partially defined by a respective ellipse having a semi-major axis and a semi-minor axis. The semi-major axis is a portion of a spanwise distance between the respective pair of blades. The semi-minor axis is a portion of an axial distance between the leading edge of one blade and the trailing edge of an adjacent blade.

Abstract: A general mounting method for ducted fan propulsors is disclosed. This mounting method uses extremely slender stators that connect the duct ring to the propulsor which is mounted in the middle and drives the rotor, fan or propeller. The slender stators take the form of spokes and as such are so slender that the midspan stresses within the spokes are dominated by axial tension loads rather than the shear loads experienced by conventional stators. The spokes may have an aerodynamic shape and damping methods may be used to retard spoke vibrations and transmission of engine vibrations to the duct and force. The duct itself is also stiffened by the spoke arrangement, thereby reducing low frequency vibration modes.

Abstract: There is provided a load transfer interface in an aircraft engine for transferring a load from a bearing housing to an engine casing. The load transfer interface comprises a first component operatively coupled to and receiving the load from the bearing housing. The first component has a first annular body with a spigot extending axially from the first annular body. The interface comprises a second component operatively coupled to the first component and to the engine casing. The second component has a second annular body with a spigot-receiving cavity disposed therein. The spigot-receiving cavity is shaped and positioned to receive the spigot of the first component. The second component receives the load from the first component and transfers the load to the engine casing.

Abstract: A spray/gas mixer includes a main body having a circumferential wall defining an inlet opening at one end and an outlet opening at another end; a divider baffle within the main body; a swirl duct having a first end adjacent to the wall and a second end extending to the divider baffle; an injector orifice at the first end of the swirl duct; a swirl promoting means; and a restrictor. The swirl promoting means is arranged between the divider baffle and the restrictor. Gas passing through the swirl promoting means is swirled around the first longitudinal axis (A) before passing through the restrictor. The restrictor is disposed between the swirl promoting means and the second end, forcing gas reaching it from an upstream side away from a peripheral region of the interior towards a center axis of the main body.

Abstract: The present application provides an exhaust frame differential cooling system of a gas turbine engine to mitigate a temperature differential along a compressor and/or a turbine to minimize centerline eccentricity of a shaft. The exhaust frame differential cooling system may include a number of compressor temperature sensors positioned about the compressor and/or a number of turbine temperature sensors positioned about the turbine, an exhaust frame including an inner barrel with a bearing tunnel for the shaft, an outer barrel, and a number of struts extending from the inner barrel to the outer barrel, a blower, and a cooling air metering system that provides cooling air from the blower to the bearing tunnel and through the inner barrel, the struts, and the outer barrel in response to the temperature differential being determined along the compressor and/or the turbine.

Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.

Abstract: A gas turbine engine includes: a fan that is in front of a compressor and rotates in association with a rotating shaft; a casing including an inner shell and an outer shell and a bypass passage; bearings inside the inner shell; an oil mist generator that is outside the outer shell and generates oil mist by mixing oil with compressed air extracted through an extraction port of the compressor; an air pipe through which the compressed air extracted from the compressor is guided to the oil mist generator; and an oil mist pipe through which the oil mist generated by the oil mist generator is guided to the bearings. At least one of the air pipe and the oil mist pipe includes a heat exchanger that is in the bypass passage and is cooled by the air flowing through the bypass passage.