Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.

Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

Abstract: In a thrust reverser for an aircraft propulsion unit, the thrust reverser includes an internal fixed structure, a mobile cowl and blocking flaps. The thrust reverser also includes a first actuation mechanism that is configured to move the mobile cowl between a closing position and an opening position so as to cause the blocking flaps to move respectively between a retracted position and a deployed position, thus causing the thrust reverser to pass respectively between a full-thrust configuration and a thrust-reversal configuration. The thrust reverser also includes a second actuation mechanism that is configured to move the blocking flaps between the retracted position and a partially deployed position when the mobile cowl is in the closing position, so as to cause the thrust reverser to pass respectively between the full-thrust configuration and a reduced-thrust configuration.

Abstract: A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.

Abstract: A propulsion assembly with a primary duct and a secondary duct, an outer fairing delimiting an outer compartment with an inlet opening, an inner fairing delimiting an inner compartment with an air exhaust aperture, a suction system having an inlet, an outlet and mobile elements that draw the air in via the inlet and deliver the air via the outlet, a drive that drives the mobile elements, a transfer pipe connected to the outlet, a distribution pipe disposed in the inner compartment, connected to the transfer pipe and having nozzles, a supply pipe that opens into the outer compartment and is connected to the inlet, and a regulator that regulates the flow rate of air in the suction system. The outside air is then driven by the suction system and passes through the two compartments in a forced manner.

Abstract: A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum and that define injection holes therethrough. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. The mixing conduits fluidly couple the high-pressure plenum to the main passage, and the fluid from the fluid plenum is delivered with the high-pressure fluid to the main passage, where the fluids mix before being discharged from an outlet of the main passage. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.

Abstract: A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

Abstract: The application relates to an assembly for controlling detonation wave mode of a rotating detonation combustion chamber, which includes an inner barrel, an outer plate and at least one sectoral direction-changing block. The outer plate is sleeved outside the inner barrel. An annular cavity is formed between the outer plate and the inner barrel. At least one groove is arranged on one side of the outer plate close to the inner barrel. The groove wall comprises an arc edge and a straight edge. The groove is connected with the annular cavity. The sectoral direction-changing blocks are arranged in the grooves in one-to-one correspondence. An arc edge of the sectoral direction-changing block is positioned far away from the inner barrel.

Abstract: A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.

Abstract: A pulse detonation combustion system includes: an inlet pipe; an intake cone disposed in the inlet pipe, having an end provided with a pneumatic valve, and including an atomizing air transfer tube, a fuel transfer tube, and a conical swirl nozzle connected to the atomizing air transfer tube and the fuel transfer tube; an atomizing air intake tube connected with the atomizing air transfer tube; a fuel supply tube connected with the fuel transfer tube; a pulse detonation combustion chamber located downstream of and communicated to the inlet pipe, and provided with a spark plug mounting seat for mounting a spark plug; a gas energy distribution adjustment device located downstream of and communicated to the pulse detonation combustion chamber; and a transition section located downstream of and communicated to the gas energy distribution adjustment device.

Abstract: A scramjet engine includes first and second flow path forming members and first and second fuel injection devices. A flow path formed between the first and second flow path forming members includes a turbulence forming region where compressed air is introduced and a combustion region located downstream thereof. The second flow path forming member is formed with a protrusion in the turbulence formation region. The first fuel injection device is configured to inject fuel into the compressed air via a first fuel nozzle. The second flow path forming member is formed with a cavity located in the combustion region. The second fuel injection device is configured to inject fuel into the compressed air via a second fuel nozzle. The cavity is provided with an inclined surface connected to a bottom surface. An inclination of the inclined surface is adjusted so that a shock wave is generated in the combustion region.

Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.

Abstract: A turbine exhaust unit supporting device that supports a turbine exhaust unit is provided. The turbine exhaust unit supporting device installed at a rear side of a turbine casing to support a turbine exhaust unit through which exhaust gas passing through a turbine is discharged, the supporting device includes a casing supporting block unit installed on an outer circumferential surface of the turbine casing, an exhaust unit supporting block unit spaced apart from the casing supporting block unit and installed on an outer circumferential surface of the turbine exhaust unit, and a rotary coupler including a first end rotatably coupled to the casing supporting block unit and a second end rotatably coupled to the exhaust unit supporting block unit.

Abstract: A gas turbine engine comprising a housing coupled to an upstream source of hot gas and superheated water droplets, the housing having a centerline, an annular bay section positioned radially away from the centerline and protruding in an upstream direction, a rotatable shaft positioned along the centerline, a fluid mover coupled to the rotating shaft and positioned to receive the hot gas and superheated water droplets from the upstream source and to move the hot gas and superheated water droplets radially toward the annular bay section of the housing, a separator plate that is fixedly coupled to the housing; and an extractive turbine assembly positioned downstream from the separator plate and the annular bay section. The superheated water droplets mix thoroughly with the hot gas inside the annular bay section causing the water droplets to covert to steam, and the steam flows to the extractive turbine, increasing an efficiency of turbine rotation.

Abstract: A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection (“EFI”) system that further includes one or more electrically controlled fuel injectors that can be selectively operated for start-up and control of such pulsejet engines. According to the system and method, the rate and/or pattern of fuel delivery to pulsejet engines can be varied not only by controlling the amount of time the fuel injectors are open versus closed to define a “duty cycle,” but also with the capability to selectively disable one or more fuel injectors in the programmed manner for start-up and control of such pulsejet engines.

Abstract: Rotating detonation engines are provided with various improvements pertaining to performance and reliability. Improvements pertain to, for example, a fluidic valve/premixing chamber, injection/swirl, flow control and turning, ignition, and cooling. A rotating detonation engine can include a cylindrical inner shell within an outer housing, a cylindrical outer shell positioned between the inner shell and the outer housing, an annular gap between the outer shell and the outer housing functioning as a detonation chamber.

Abstract: The present invention discloses an isolation section suppressing shock wave forward transmission structure for a wave rotor combustor and a wave rotor combustor, and belongs to the new concept field of unsteady combustion. The isolation section suppressing shock wave forward transmission structure for a wave rotor combustor includes a wave rotor and a gas inlet port, and the wave rotor is provided with several wave rotor channels. When the wave rotor rotates, the several wave rotor channels communicate with the isolation section sleeve sequentially through the fan-shaped hole. The present invention suppresses reflected shock waves by changing a flow blockage ratio and a shape of the pneumatic valve to consume back transmission pressure, which is beneficial to a fuel intake process, so that steady working of the wave rotor combustor in a state of deviating from a design point can be implemented.

Abstract: A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection (“EFI”) system that further includes one or more electrically controlled fuel injectors that can be selectively operated for start-up and control of such pulsejet engines. According to the system and method, the rate and/or pattern of fuel delivery to pulsejet engines can be varied not only by controlling the amount of time the fuel injectors are open versus closed to define a “duty cycle,” but also with the capability to selectively disable one or more fuel injectors in the programmed manner for start-up and control of such pulsejet engines.

Abstract: A pulse combustor system for operating pulse combustors in anti-phase. The pulse combustor system includes two pulse combustors connected at their combustion chambers by a connecting tube. Each of the pulse combustors has a fundamental oscillation mode and one or more additional oscillation modes when operated in isolation. The connecting tube has a length corresponding to ¼ of the fundamental oscillation mode wavelength.