Abstract: A gas turbine engine includes a first spool associated with a primary combustor, a second spool associated with a secondary combustor, and a third spool, each spool including a compressor and a turbine mounted to a shaft. A transmission and accessory gearing are enclosed within a housing of an accessory gearbox. The transmission rotationally couples the third spool to the second spool and accessory gearing. A method of operating the gas turbine engine includes supplying a first fuel flow rate to the primary combustor and supplying a second fuel flow rate to the secondary combustor within an intermediate speed range of the gas turbine engine.

Abstract: A propulsion system is provided for an aircraft. This aircraft propulsion system includes an engine housing, an open propulsor rotor, an engine core and a thrust diversion system. The open propulsor rotor is outside of the engine housing. The engine core is within the engine housing and motively coupled to the open propulsor rotor. The thrust diversion system is configured with the engine housing. The thrust diversion system includes a door configured to move radially from a stowed position to a deployed position.

Abstract: An apparatus generates energetic particles and generates a plasma of a vaporized solid material and gaseous precursors for the application of coatings to surfaces of a substrate by way of condensation of plasma and for electric propulsion applications.

Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The combustor further includes a liner panel mounted to one of the inner shell and the outer shell aft of the bulkhead. The liner panel includes a first section including a first plurality of effusion holes. A first portion of the first plurality of effusion holes extends in a substantially circumferential direction. A second portion of the first plurality of effusion holes, disposed forward of the first portion, transitions from the substantially circumferential direction toward a substantially forward direction. A third portion of the first plurality of effusion holes, disposed aft of the first portion, transitions from the substantially circumferential direction to a substantially aft direction.

Abstract: A fuel leak detection system for hydrogen fuel system including a monitored component. The fuel leak detection system including a sensor and controller communicatively coupled to the sensor. The sensor is positioned to monitor at least a portion of the monitored component. The sensor is configured (i) to sense a parameter corresponding to a hydrogen fuel leak of the monitored component and (ii) to generate an output. The controller is configured (i) to receive the output of the sensor, (ii) to determine, based on the output of the sensor, if a leak has occurred in the monitored component, and (iii) to generate an output indicating a fuel system leak when the controller determines that the leak has occurred in the monitored component. The monitored component may be a component of one of a fuel tank, a power generator, and a fuel delivery assembly.

Abstract: An air turbine starter having a housing defining an interior with a primary inlet and a primary outlet to define a primary air flow path from the primary inlet to the primary outlet. A nozzle is located within the interior and has circumferentially spaced vanes. A shroud is also located within the interior and circumscribes at least a portion of the vanes. A retention mechanism constrains the axial movement of nozzle.

Abstract: Disclosed is a fuel system for a gas turbine engine. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and a source of compressed air flow to drive the driving turbine. The source of compressed air may be the engine core, a dedicated fuel system compressor or the compressor of a cabin blower system.

Abstract: A Fiber-fed Pulsed Plasma Thruster (FPPT) has an anode, a coaxial insulator, and a fiber propellant feed system. At least two cathodes insulated from each other are configured about the coaxial insulator to define an interior profile shaped into a nozzle region. At least one igniter fitted through each cathode. Wherein when the igniters are triggered, the igniters expel electrons toward the anode to ignite a primary high energy discharge between the anode and the cathodes thereby creating a plasma that vaporizes the fiber propellant. The dissociated fiber propellant combines with the primary high energy discharge to create a partially or fully ionized plasma, that is electromagnetically and electrothermally accelerated to produce predominantly {right arrow over (j)}×{right arrow over (B)}{right arrow over (j)}×{right arrow over (B)} thrust.

Abstract: Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.

Abstract: Electrical power systems for distributing electrical power in arrangements including one or more gas turbine engines; one such system includes: one or more rotary electric machines coupled to a gas turbine engine spool; a set of converter circuits connected to the rotary electric machines converting between alternating current (ac) and direct current (dc), wherein the rotary electric machines and the converter circuits output a number R?2 of dc power channels, each channel having an index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein N>R and each dc load channel has an index n=(1, . . . , N). For each respective N load channels, a current limiting device (CLD) limits the current flowing from power channels to a load connectable to the electrical power system via the respective load channel.

Abstract: An engine system is provided that includes a gas turbine engine and an actuation system. The gas turbine engine includes a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The actuation system includes a fluid reservoir, a flow regulator and a flow circuit. The flow regulator is configured as or otherwise includes a barrier between the fluid reservoir and the flow circuit. The flow regulator is configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact. The flow regulator is configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks. The flow circuit is configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks.

Abstract: A turbofan engine includes a fan, a core turbine engine having an exhaust section, and a hydrogen-exhaust gas heat exchanger in flow communication with the exhaust section and hydrogen flowing along a hydrogen supply line. The hydrogen-exhaust gas heat exchanger defines a load capacity factor determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates characteristics of hydrogen, ambient air, and exhaust gas at takeoff, as well as a fan diameter of the fan and an overall pressure ratio of the turbofan engine. The load capacity factor is between 2.92 and 24 for the fan diameter being between 0.5 and 5 meters and the heat transfer surface area density being between 500 m2/m3 and 13,000 m2/m3.

Abstract: A gas turbine engine including a catalytic reactor and a combustor. The catalytic reactor is configured (i) to receive hydrogen fuel, (ii) to receive air containing oxygen, (iii) to catalytically react at least a portion of the oxygen in the air with at least a portion of the hydrogen in the hydrogen fuel to produce water, and (iv) to output diluent comprising the catalytically produced water. The combustor includes (a) a combustion chamber and (b) at least one nozzle that is fluidly coupled to the catalytic reactor to receive the diluent output by the catalytic reactor and configured to inject the diluent into the combustion chamber.

Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and outer annular passages has an upstream end, a downstream end and an annular wall extending therebetween. The annular wall defines a mixing plane at a trailing edge thereof at the downstream end at which the core and bypass gas flows are mixed. The annular wall has a radially inner surface and a radially outer surface. A plurality of protrusions are disposed on and extend laterally along and radially from at the radially inner surface and/or the radially outer surface. The plurality of protrusions are arranged one alongside another on the radially inner surface and/or the radially outer surface.

Abstract: An aircraft turbine engine assembly, including a lubricating oil circuit and a fuel supply device, the assembly also including a passive bypass valve enabling the oil to bypass an exchanger, the valve including a valve body and a piston arranged to move in a sliding space defining a first actuating chamber supplied with oil from the oil circuit, as well as a second actuating chamber supplied with fuel from the device, the valve being configured so that when the differential pressure between the oil pressure in the first actuating chamber and the fuel pressure in the second actuating chamber drops below a predetermined value of differential pressure, the piston moves from a normal operating position to an exchanger bypass position.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure and an electric machine. The rotating structure is configured to rotate about a rotational axis. The stationary structure circumscribes the rotating structure. The electric machine includes a rotor and a stator. The rotor circumscribes the rotating structure and is coupled to the rotating structure through a spline connection. The stator is connected to the stationary structure.

Abstract: An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam injector. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustor wall and a combustion chamber. The combustor wall is disposed between the combustion chamber and the air plenum. The combustor wall includes a quench aperture that extends through the combustor wall from the air plenum to the combustion chamber. The steam injector projects partially into or through the quench aperture.

Abstract: Electric engine to provide thrust to fly an aircraft. Engine includes housing, air inlet, shaft, bladed rotor having a plurality of magnets secured on shaft, stator having plurality of coils positioned so as to interact with plurality of magnets and an exhaust nozzle. Powering coils causes interaction with magnets that results in bladed rotor rotating and pressurizing and accelerating air received via air inlet and expelling via exhaust nozzle to provide thrust. Engine may include generator having stator with coils secured to shaft via bearings and plurality of rotors with magnets secured to shaft to rotate with shaft. Magnets rotating past coils results in electric generation. Second hollow shaft may be mounted to shaft with bearings and generator may be located with hollow shaft. Second bladed rotor may be connected to, and rotate, second shaft. Engine may include ducts external to bladed rotor and fan to route air therein.

Abstract: The invention relates to a method for controlling a turbomachine comprising a gas generator, the turbomachine comprising an electric machine forming a device for injecting torque into/removing torque from one of the low pressure/high pressure rotation shafts of said gas generator. Said method comprises a step of implementing a fuel control loop in order to determine a fuel flow setpoint into the combustion chamber, and comprising, in the event that at least one operability limit is reached, determining a corrected fuel flow setpoint, said corrected fuel flow setpoint exhibiting a difference in relation to the setpoint. Said method also comprises a step of implementing a torque control loop in order to determine a torque setpoint for the electric machine, and comprising determining a torque correction quantity as a function of said difference, said torque setpoint being determined as a function of said torque correction quantity.

Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.