The gas turbine includes a compressor to compress air introduced thereinto, a combustor to mix the compressed air with fuel for combustion, a main turbine having a plurality of turbine blades rotated by an energy produced by combustion gas in the combustor, a heat recovery boiler to produce steam by heat exchange with the combustion gas, and a fluid accelerator supplied with a first fluid compressed in the compressor to compress the first fluid and supply the compressed first fluid to the combustor, where the fluid accelerator includes a first inlet through which the first fluid is introduced, a second inlet through which a second fluid having a higher pressure than the first fluid is introduced, and an outlet through which the first and second fluids are mixed and discharged.

Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber. Liquid propellants supplied to the engine are utilized for regenerative cooling of the combustion chamber and preburner, where the liquid propellants are gasified in cooling manifolds before injection into the preburner and main combustion chamber.

A system is provided with an ejector having an outer wall extending circumferentially about a flow path, wherein the outer wall has a throat section along the flow path, and a diverging section downstream from the throat section along the flow path. The ejector includes a gas inlet configured to supply a gas into the flow path, and a water inlet configured to supply water into the flow path. The ejector is configured to produce steam in response to mixing of the water and the gas along the flow path. The system also includes a controller configured to control flows of the gas and the water to produce the steam for a steam purge of a liquid fuel circuit.

A jet valve to control flow of a fluid therethrough is disclosed. The jet valve includes a valve body, a juncture operatively coupled to the valve body, the juncture having a first fluid connection fluidly coupled to a header tank and a second connection fluidly coupled to a storage tank, a spool movably disposed within the valve body, the spool having an aperture extending longitudinally therethrough, a spring operatively coupled between the spool and the valve body, and a jet pump fluidly coupled to a fuel pump of the header tank via a bleed line, the jet pump disposed within the aperture, wherein operation of the fuel pump pressurizes the bleed line and moves the spool to a first position to (i) close a first fluid path between the header tank and the storage tank and (ii) provide a second fluid path between the header tank and the storage tank, the second fluid path through the aperture, and depressurization of the bleed line enables the spring to move the spool to a second position to close the second fluid path and open the first fluid path.

A pyrotechnic device comprising a main pyrotechnic charge, a firing device for firing the main pyrotechnic charge, a discharge passage for discharging the gas generated by firing the main pyrotechnic charge, and an injector device configured to inject a cooling fluid into said gas discharge passage, so as to deliver gas, specifically for driving turbines, at temperatures that are relatively low, and a method of cooling gas generated by firing the main pyrotechnic charge by injecting the cooling fluid.

Provided is a gas turbine engine including a main passage through which compressed air extracted from a compressor is guided to a bearing; and an oil supply device that supplies oil to the main passage. The oil supply device includes a pressure reducer in the main passage; an oil tank a divider that is movable and divides an internal space of the container into an oil chamber storing the oil and an air chamber; an extruder including a cylinder and a piston that divides an internal space of the cylinder into a first chamber and a second chamber; a switching mechanism that switches between a first state where the first chamber communicates with a low-pressure space whose pressure is lower than pressure in the air chamber and a second state where the first chamber communicates with a high-pressure space whose pressure is higher than pressure in the downstream passage.

A gas turbine engine defining an axial direction and a radial direction, and including a primary cooling circuit configured to receive a first flow of air; and a turbine rotor comprising a rotor blade, the rotor blade defining at least in part a forward wheelspace that is located forward of the rotor blade, the forward wheelspace configured to receive a second flow of air, the rotor blade further defining: a first cooling circuit internal to the rotor blade and in fluid communication with the primary cooling circuit for receiving the first flow of air from the primary cooling circuit; a second cooling circuit internal to the rotor blade and in fluid communication with the forward wheelspace for receiving a portion of the second flow of air from the forward wheelspace; and a means for drawing a portion of the second flow of air into the second cooling circuit.

A gas compressor comprising a rotating drum and a return assembly. The drum includes a compression channel assembly with compression channels between a common zone and a distal area. The compression channels may be formed by a plurality of V-shaped blocks. The return assembly draws liquid from an annular lake formed in the drum to a fluid outlet. A gas inlet in the return assembly mixes incoming gas with the liquid. An optional eductor connected to the gas inlet draws gas into the gas inlet. Fluid entering the common pressure zone is forced into the compression channels that compress the gas. Pressurized gas is separated from liquid in the fluid prior to leaving the compression channel. An inducer may be positioned between the fluid outlet of the return assembly and the opening of the centralized common pressure zone.

A jet engine uses an entrainment compressor within a housing to compress intake air. The compressed air is routed to a combustion chamber where it is ignited. A portion of the exhaust is directed outward for thrust and a portion is rerouted through an energy feedback system to one or more entrainment nozzles within the compressor housing. The exhaust acts as motive fluid to mix with the intake air. The motive fluid imparts energy to create the compressive capability of the jet engine. A startup system is configured to generate startup motive fluid selectively routed through some or all of the entrainment nozzles to initiate a stable idle flow of motive fluid. Some of the entrainment nozzles may include combustion chambers to further enhance the compressive capability of the jet engine.

A combination of a gas turbine engine and power electronics, includes an engine core and oil circuit to cool and lubricate bearings of the engine core, and a fuel circuit for supplying fuel to the combustor. The fuel circuit includes a low pressure pump for pressurising the fuel to a low pressure, and a high pressure pump to receive the low pressure fuel and increase the pressure to a high pressure for supply to a fuel metering system and the combustor. The engine includes a fuel-oil heat exchanger having a fuel side on the fuel circuit between an outlet of the low pressure pump and an inlet of the high pressure pump, and an oil side on the oil circuit to transfer heat from the oil circuit to the fuel circuit. The power electronics transfers heat to a cooling flow formed by a portion of the low pressure fuel.