Abstract: In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.

Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: A system including a turbine engine configured to generate rotor power and produce an engine air flow. The system is configured to provide rotor power to one of more shaft-driven lift fans to generate a first thrust on an aircraft body and provide a gas flow to one or more gas-driven lift fans to generate a second thrust on the aircraft body. The gas flow may be at least a portion of the engine air flow produced by the turbine engine. The turbine engine may be configured to exhaust another portion of the engine air flow through a jet nozzle to generate an engine thrust. In examples, the system includes at least a second turbine engine. The one of more shaft-driven lift fans and/or one of more gas-driven lift fans be powered by the turbine engine, the second turbine engine, or both the turbine engine and the second turbine engine.

Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.

Abstract: A combined cycle power plant includes a gas turbine engine that includes a compressor having a compressor inlet, a compressor outlet, and an interstage inlet defined therebetween. The turbine also includes a turbine outlet configured to discharge a first exhaust gas stream therefrom. A heat recovery steam generator is configured to receive the first exhaust gas stream, extract heat from the first exhaust gas stream, and discharge a second exhaust gas stream therefrom. Either a recirculation compressor pressurizes a first portion of the second exhaust gas stream for recirculation towards the compressor interstage inlet, or an admission compressor pressurizes an air stream directed towards the compressor interstage inlet. A first cooler cools the stream directed to the compressor, thereby defining a cooled stream, wherein the first cooler provides the cooled stream to the interstage inlet of the compressor.

Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Abstract: A system for controlling idle speed and power draw includes a determination unit configured to determine a current available power value, a determination unit configured to determine a current power consumption value, a determination unit configured to determine a future power requirement variation value, a computation unit configured to calculate a future estimated total power requirement value, a computation unit configured to calculate a future estimated available power value, an optimization unit configured to determine an optimization result by comparing the estimated total power requirement value with a power value associated with an optimization criterion and a controller configured to send an order to adapt an idle speed of the engine, an order to adapt the estimated total power requirement or no order as a function of the optimization result.

Abstract: A circuit (10) for draining at least one combustible fluid for a cavity of a turbine includes a drain (12) in fluidic communication with the at least one cavity, and a first isolation valve (14) and a second isolation valve (16) defining between them an isolation cavity (C) of a portion of the drain. A discharge line (18) is in fluidic communication with the isolation cavity (C) to allow the discharge of air out of the isolation cavity (C). A supply line (22) supplies pressurized fluid to the isolation cavity (C), and a supply valve (24) is arranged in the supply line (22) for regulating the supply of the isolation cavity (C) with pressurized fluid. A discharge valve (20) is arranged in the discharge line (18) for regulating the discharge of the gases out of the isolation cavity (C), and a device (26) is provided for determining a failure of the drainage circuit (10).

Abstract: A computing system for an unducted rotor engine with a variable pitch vane assembly in aerodynamic relationship with an unducted rotor assembly, including a sensor-based controller configured to execute a first set of operations and a model-based controller configured to execute a second set of operations. The first set of operations includes obtaining a first signal corresponding to a commanded low spool speed; obtaining a second signal indicative of a pitch angle corresponding to thrust output from the unducted rotor assembly and variable pitch vane assembly; generating a pitch feedback signal corresponding to a commanded adjustment to the pitch angle based at least on one or both of a variable blade pitch angle or a variable vane pitch angle. The second set of operations include obtaining a desired thrust output via a throttle input; determining, at least via a power management block, a commanded thrust output signal; receiving the commanded thrust output signal; and generating an output signal.

Abstract: A fuel pump system can include a motor and a pump connected to the motor. The pump can be configured to receive an inlet flow from an inlet line, to pressurize the inlet flow, and to output a pressurized flow to an output line for an engine. The system can include a bypass line disposed between the outlet line and the inlet line, and a bypass valve disposed on the bypass line and configured to allow pressurized flow to flow to the inlet line in an open state, and to prevent pressurized flow from flowing to the inlet line in a closed state. The bypass valve can be configured to allow pressurized flow to flow to the inlet line to circulate flow and to maintain a constant pressure on the output line.

Abstract: A combustor nozzle, a combustor, and a gas turbine including the same are proposed. The combustor nozzle includes a nozzle module. The nozzle module includes a fuel supply pipe supplying fuel from the front side to the rear side, a fuel plenum having an internal fuel flow path through which the fuel flows and communicating with the fuel supply pipe, an air inlet formed in front of the fuel plenum, a plurality of tubes disposed through a rear side of the fuel plenum, wherein a front end of each tube communicates with the air inlet, and a fuel port communicating with the fuel flow path is formed on a lateral side of each tube, and a swirler provided with a plurality of swirling guides disposed obliquely in axial and circumferential directions on an inner circumferential surface of each of the plurality of tubes to swirl fluid, with a central portion thereof opened when viewed from the axial direction of the tube.

Abstract: A fuel flow system for a gas turbine engine includes a fuel inlet to admit a flow of fuel into the fuel flow system and a fuel outlet to direct the flow of fuel to the gas turbine engine from the fuel flow system. One or more pumps are positioned along a fuel flow path connecting the fuel inlet to the fuel outlet. A metering valve is in flow communication with the one or more pumps to meter the flow of fuel. A minimum pressure shut-off valve is fluidly connected to the one or more pumps, and a shutoff apparatus configured to permit selective energizing to stop the flow of fuel from the fuel outlet without operation of the metering valve.

Abstract: An Ericsson cycle turbine engine. The Ericsson cycle turbine may comprise: a centrifugal gas compressor, shaft, at least one heat exchanger, and a reaction turbine. The centrifugal gas compressor may function as a spinning wheel trompe and may be fed with a gas-liquid mixture. The centrifugal gas compressor may separate a gas from the gas-liquid mixture after compression of that gas via centrifugal acceleration. The shaft may couple to the downstream end of the centrifugal gas compressor and may have an annular space to permit the compressed gas to travel therein. The heat exchanger may introduce heat to the compressed gas, such that isobaric expansion is approached. The reaction turbine may couple to the downstream end of the shaft and may rotate the shaft when releasing the compressed gas. The liquid may be mercury, oil, or a water-glycol mixture. The gas may be helium, air, argon, or ammonia.

Abstract: A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

Abstract: Methods and fluid supply systems are provided for supplying fluids while adjusting a pump discharge pressure to compensate for downstream pressure changes. The fluid supply system comprises a variable displacement piston (VDP) pump configured to supply a fluid at a pump discharge pressure, fuel metering units (FMUs) downstream of the VDP pump, each of the FMUs configured to receive the fluid from the VDP pump at the pump discharge pressure and supply the fluid at metered flow discharge pressures, and a pump compensator valve fluidically coupled with the FMUs to receive the fluid therefrom at the metered flow discharge pressures and configured to continuously, either fluidically or mechanically, adjust the pump discharge pressure of the VDP pump between a higher of a minimum pump discharge pressure and a floating ceiling pump discharge pressure, the floating ceiling pump discharge pressure based on a highest of the metered flow discharge pressures.

Abstract: A combustor liner has an outer liner and an inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer liner and the inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber and form a throat between them. A bridge member extends across the converging-diverging sections to form a damper cavity therebetween. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member on a downstream portion of the converging-diverging section, so that an acoustic damper is defined by the converting-diverging section, the bridge, and the damper inlet feed. The acoustic damper dampens acoustic characteristics of the combustor.

Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.

Abstract: A reheat assembly for a gas turbine engine includes; a jetpipe casing defining a reheat core section configured to duct a core flow of air and a reheat bypass section configured to duct a bypass flow of air. The reheat bypass section is disposed radially outward of the reheat core section, and the reheat core section and the reheat bypass section are at least partially separated by a support duct. An integrated flameholder is mounted to the jetpipe casing, and a fuel pipe is configured to convey fuel to the integrated flameholder. The integrated flameholder includes a flameholder body extending radially inward from the jetpipe casing through the reheat bypass section and into the reheat core section to promote a wake-stabilised region downstream of the body; and an integrated atomiser configured to atomise fuel provided to the integrated flameholder and to discharge the atomised fuel into the wake stabilised region.

Abstract: A valve having a first segment between a first outer wall and a first inner wall and has a first outer port near the first outer wall and a side port between the first inner and outer walls; a second segment between a second outer wall and a second inner wall and has a second outer port near the second outer wall; a center segment between the first and second inner walls, and a center port; and a piston within the valve, having: a first piston head in the first segment that slides to block and unblock the side port; a second piston head in the second segment that slides between the second inner and outer walls, the second piston head having a surface area that is the same as the first piston head; and a shaft connecting the first and second piston heads.

Abstract: A fuel delivery system for a gas turbine engine comprises a cryogenic fuel tank, a first fuel line for connection to the cryogenic fuel tank, a fuel pump connected to receive fuel via the first fuel line, a plurality of fuel lines connecting the fuel pump to a combustor of the gas turbine engine, a controller configured to operate the fuel delivery system, a purge gas tank connected to the first fuel line and configured to store a purge gas for purging the plurality of fuel lines and a fuel gas tank connected to the first fuel line and configured to store a fuel gas for flushing purge gas from the plurality of fuel lines.