A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

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.

A method of making a fluid injector for a gas turbine engine includes depositing material onto a piece of tube stock. The method includes machining the deposited material into a fluid injector component. Depositing can include laser cladding the material onto the piece of tube stock. The method can include placing or flowing braze into a braze joint location between the deposited material and another fluid injector component and forming the braze into a braze joint in the braze joint location.

Embodiments are directed toward a monopropellant continuous detonation engine. In some embodiments, the continuous detonation engine includes an engine body, a monopropellant feed assembly, and a detonation initiator. The engine body defines a detonation wave channel. The monopropellant feed assembly delivers monopropellant from a monopropellant storage tank into the detonation wave channel. The detonation initiator initiates continuous detonation of the monopropellant in the detonation wave channel, preferably without a catalyst to promote decomposition of the monopropellant. Accordingly, specific impulse is increased compared to constant-pressure reaction thrusters that catalytically decompose the monopropellant with deflagration combustion.

Embodiments are directed toward a monopropellant continuous detonation engine. In some embodiments, the continuous detonation engine includes an engine body, a monopropellant feed assembly, and a detonation initiator. The engine body defines a detonation wave channel. The monopropellant feed assembly delivers monopropellant from a monopropellant storage tank into the detonation wave channel. The detonation initiator initiates continuous detonation of the monopropellant in the detonation wave channel, preferably without a catalyst to promote decomposition of the monopropellant. Accordingly, specific impulse is increased compared to constant-pressure reaction thrusters that catalytically decompose the monopropellant with deflagration combustion.

A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.

A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.