Abstract: An adjustable injector system for adjusting a radial distribution of a mixed fuel includes an adjustable injector configured to receive first and second non-carbon fuels and configured to adjust the radial distribution of the mixed fuel with a movable part, wherein the mixed fuel is obtained from mixing the first non-carbon fuel with the second non-carbon fuel; a sensor configured to determine an instability of a flame generated by the mixed fuel; and a controller electrically connected to the adjustable injector and the sensor, and configured to change a configuration of the adjustable injector, based on an input signal from the sensor, to control the radial distribution of the mixed fuel.

Abstract: A method of assembling a mobile electric power generation system includes using a generator trailer having an electric generator, a gas turbine trailer having a gas turbine, an exhaust trailer configured to exhaust air, and an air filter and ventilation trailer having an anti-icing system. The generator trailer and the gas turbine trailer is positioned at a work site such that the generator trailer and the gas turbine trailer are in an end-to-end configuration. The gas turbine trailer is operably coupled to the generator trailer.

Abstract: A gas turbine facility includes: a fuel pipe connected to a fuel supply facility; a fuel supply pipe connected to a combustor of a gas turbine; a fuel treating pipe connected to a fuel treating apparatus that treats a fuel; and a three-way valve having an inlet port connected to the fuel pipe, a first outlet port connected to the fuel supply pipe, and a second outlet port connected to the fuel treating pipe.

Abstract: A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.

Abstract: A gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath. The gas turbine engine also includes a turbine rear frame extending through the core air flowpath at a location downstream of the turbine section and defining a leading edge within the core air flowpath. The gas turbine engine also includes a waste heat recovery system operable to separate, at or upstream of the leading edge of the turbine rear frame, a core airflow exiting the turbine section into a primary exhaust airflow and a waste heat recovery airflow. The waste heat recovery system comprises a heat source exchanger positioned to receive the waste heat recovery airflow.

Abstract: An ignition and combustion assist system and method comprising a plasma igniter and electronic driver unit for use with gas turbine engines operating under low air densities, reduced voltage conditions and overall pressure ratios of 3:1 to 7:1. The plasma igniter has an inner chamber housing a centrally positioned and electrically isolated electrode attached to an electrical lead, driver unit, and AC or DC power supply. The electrode features a corner positioned near an outlet end of the igniter, where a plasma arc ignites a fuel-air mixture creating a flame extending into a primary burn region of a combustor of the gas turbine. The driver unit is in two embodiments and configured with low-cost microsecond voltage wave time periods or energy-efficient nano-second pulses. The method uses the plasma igniter and the electronic driver units described herein separately with other components or together.

Abstract: A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.

Abstract: A method for operating a glow plug includes controlling a temperature of the glow plug by switching between applying a voltage VH and applying a voltage VN<VH to the glow plug. Applying the voltage VH and applying the voltage VN causes a glow plug current to oscillate about a glow plug current threshold. The glow plug current threshold is associated with one of the voltage VH and the voltage VN. The method includes monitoring the glow plug current at the one of the voltage VH and the voltage VN.

Abstract: A cooling system includes a conduit extending from an upstream end to a downstream end and retains a gas. A heat exchanger is fluidly coupled with and disposed within a surface of the conduit. A portion of the gas is directed into the heat exchanger via one or more passages extending between the conduit and the heat exchanger, and a portion of the gas is directed out of the heat exchanger via the one or more passages. The heat exchanger directs cooling fluid in one or more directions within the heat exchanger along one or more passageways of plural passageways. The heat exchanger directs the portion of the gas in one or more directions within the heat exchanger along one or more other passageways of the plural passageways. The heat exchanger cools the gas by exchanging heat from the gas to the cooling fluid within the heat exchanger.

Abstract: A seal interposed between a turbojet engine and a movable part of a nacelle includes a tubular body delimiting an inner cavity interposed between at least one fixing part and a platform. The platform includes a first lateral edge, a second lateral edge and a planar surface extending from the first lateral edge to the second lateral edge. The seal includes a protuberance arranged on the platform. The protuberance is centered on the platform or extends from the first lateral edge to the second lateral edge.

Abstract: A heat exchanger includes an inlet plenum chamber, an outlet plenum chamber fluidly coupled to the inlet plenum chamber, and a plurality of intermediate plenum chambers disposed downstream from the inlet plenum chamber and upstream from the outlet plenum chamber. The plurality of intermediate plenum chambers includes a first intermediate plenum chamber, at least one tube bundle, and a first bypass valve fluidly coupled to the first intermediate plenum chamber. The first bypass valve is configured to control fluid flow rate from the first intermediate plenum chamber to the outlet plenum chamber.

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a lower door and an upper door defining, in thrust reversal configuration, a deflection opening, through which a portion of the fluid not serving to produce the thrust reversal of the aircraft can exit the reverser downstream. The downstream edge of the lower door is offset towards the rear with respect to the downstream edge of the upper door so as to orient the fluid flow passing through the deflection opening vertically upwards. When the propulsion assembly is mounted at the rear portion of the fuselage of the aircraft, this makes it possible in particular to improve the supply of the control surface of the aircraft in the landing phase, in particular in crosswind conditions.

Abstract: An air supply device, a gas turbine system and a using method thereof are disclosed. In the air supply device, an air intake compartment includes a connection end; a combustion air intake filter is located in the air intake compartment and connected with the combustion air intake filter; a combustion air intake interface is located on a tail plate and is connected with the combustion air silencer; and a sound insulation turnover mechanism includes a sound insulation flap and a turnover mechanism, the air intake compartment includes a first bottom plate and the tail plate that is located at the connection end, the sound insulation flap is located at the connection end, and the turnover mechanism is connected with the sound insulation flap, and is configured to drive the sound insulation flap to rotate relative to the tail plate.

Abstract: Aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.

Abstract: In some embodiments, apparatuses are provided herein useful to sealing a gap, such as a gap between a gas turbine engine nozzle flap and sidewall. An apparatus for sealing such a gap may be a plunger seal that includes a plunger, a retaining element, a guide pin, and a biasing element. The plunger includes a sealing edge and an actuating edge having at least one recess and an opening formed therein. The biasing element and a portion of the guide pin are nested in the recess. The retaining element anchor the plunger to the retaining element. The retaining element also anchors the plunger seal to the housing When installed in a gap, the housing engages the flap and the plunger engages the sidewall. The biasing element is under compression and urges the guide pin into the actuating edge to urge the plunger toward the sidewall and seal the gap.

Abstract: A compressor wheel is provided for the output shaft. Air bleed ports are formed in a shroud case that surrounds the compressor wheel. A plurality of air bleed passages are formed in the engine housing that surrounds the shroud case. An annular chamber is formed between the air bleed ports and the air bleed passages, for storing compressed air that is extracted from the air bleed ports.

Abstract: A heat exchanger for a hydrogen fuel delivery system includes a tube bank including an inner-tube where a first portion of the inner-tube extends through an inlet region of the tube bank, a second portion of the inner-tube extends through a mid-region of the tube bank, and a third portion of the inner-tube extends through an outlet region of the tube bank. A thermal buffer at least partially surrounds the inner-tube. A first portion of the thermal buffer extends along the first portion of the inner-tube, a second portion of the thermal buffer extends along the second portion of the inner-tube, and a third portion of the thermal buffer extends along the third portion of the inner-tube. A plurality of fins is disposed along the inner-tube and extends radially outwardly from an outer surface of the thermal buffer.

Abstract: Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

Abstract: A heat exchanger, has: a heat exchanger core having an inlet, an outlet, at least one first conduit connecting the inlet to the outlet, and at least one second conduit in heat exchange relationship with the at least one first conduit; a bypass conduit connecting the inlet to the outlet while bypassing the at least one first conduit; and a valve in communication with the bypass conduit and having: a valve member movable between a closed position in which fluid communication through the valve and via the bypass conduit is blocked and an open position in which fluid communication through the bypass conduit and through the valve is permitted, the valve member defining an auxiliary passage, and a thermal fuse overlapping the auxiliary passage and blocking fluid communication through the valve member via the auxiliary passage, the thermal fuse having a melting temperature above a predetermined temperature of the fluid.

Abstract: An engine assembly defining an axial direction (A) and including a gearbox, an engine core including at least one rotor, and a flexible coupling shaft having a first end and a second end along the axial direction (A). The first end of the flexible coupling shaft is connected to the engine core and the second end of the flexible coupling shaft is connected to the gearbox. A damper system is positioned at the second end of the flexible coupling shaft. The damper system is configured to reduce vibrations to the flexible coupling shaft during operation of the engine assembly.