Abstract: A fuel spray nozzle includes a fuel circuit having in series a gallery, circumferentially spaced passages arranged in a row around the nozzle, and an annular spin chamber. Each passage has an inlet for receiving a respective portion of the fuel from the gallery and a metering orifice for discharging its portion of the fuel. The passages are configured such that, when the flow of liquid fuel to the inlet port is shut off, a respective differential static pressure develops across stagnant liquid fuel remaining between the inlet and the metering orifice of each passage, and the passages are further configured such that one or more selected passages develop a different differential static pressure to the remaining passages causing a flow of purging air to enter the gallery from the combustor through the selected passages and exit through the remaining passages, thereby purging the gallery and the passages of fuel.

Abstract: A combustor for a rotating detonation engine includes a radially outer wall extending along an axis (A); a radially inner wall extending along the axis (A), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a1) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a2) to the inlet, wherein the second passage axis is arranged at an angle (?) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.

Abstract: A main injector can include multiple sub-element mixers. A first sub-element mixer includes a first main air nozzle circumscribing a first main fuel nozzle. A second sub-element mixer includes a second main air nozzle circumscribing a second main fuel nozzle. An annular combustor can include a circumferential array of main injectors disposed proximate a pilot injector. Each main injector of the array of main injectors can be oriented with first sub-element mixers proximate to the pilot injector and second sub-element mixers spaced axially downstream relative to first sub-element mixers in a staged configuration.

Abstract: A heat engine system comprises a compressor, a heat source, and a turbine, each having an inlet and an outlet, and which collectively define part of a working fluid flow circuit. The system further comprises a housing operable to be sealed to define a reservoir in which the compressor, heat source, and turbine are located. The working fluid flow circuit further comprises a compressor-to-heat-source duct which extends between the compressor outlet and the heat source inlet, a heat-source-to-turbine duct which extends between the heat source outlet and the turbine inlet, and a turbine-to-compressor duct which extends between the turbine outlet and the compressor inlet. A bleed valve is provided in flow communication with the compressor outlet, operable to bleed working fluid into the reservoir. An intake valve is provided in flow communication with the compressor inlet operable to allow passage of working fluid from the reservoir to the compressor inlet.

Abstract: A method of blending at least two fuels includes providing at least two fuels to a helical static mixer via a fuel supply system, the fuel supply system including a fuel supply circuit for each fuel of the at least two fuels, mixing, via a plurality of helical structures of the helical static mixer, the at least two fuels to form a fuel mixture, determining, via one or more sensors, a measured interchangeability index of the fuel mixture, comparing the measured interchangeability index to a predetermined interchangeability index, adjusting, via the fuel supply system, one or more parameters of at least one of the at least two fuels based on the comparison between the measured interchangeability index and the predetermined interchangeability index, and providing the fuel mixture to a combustion system.

Abstract: A fuel injector includes a first fuel path, a second fuel path, and an air path. The first fuel path is independent from the second fuel path. The ratio of a first outlet area of the first fuel path, a second outlet area of the second fuel path, and a third outlet area of the air path is constant. A fuel system includes a first fuel source, a second fuel source, an air source, and the injection. The first fuel source is fluidly connected to the first fuel path. The second fuel source is fluidly connected to the second fuel path. The air source is fluidly connected to the air path.

Abstract: A cooling structure for a radial turbine is equipped with a partition wall arranged between a compressor and the radial turbine, and a through hole formed in the partition wall supplying a part of air compressed by the compressor to the rear surface of the radial turbine as cooling air. The through hole is inclined in a rotational direction of the radial turbine in the range of 40° to 80° with respect to a rotation axis of the radial turbine.

Abstract: A fuel nozzle and a method of operating the fuel nozzle, can include a group of chambers located in the fuel nozzle, wherein the chambers can include an inner mixing chamber and an outer mixing chamber. The inner mixing chamber and the outer mixing chamber each can accept air and fuel separately and combine the air and the fuel to form a mixture of the air and the fuel. A first hole pattern and a second hole pattern can be configured in the fuel nozzle, wherein the fuel enters the inner mixing chamber through the first hole pattern and enters the outer mixing chamber through the second hole pattern. Furthermore, an angled discharge can be included with the inner mixing chamber, wherein the angled discharge slows an exit velocity of the mixture of the air and the fuel prior to exiting the fuel nozzle through a discharge end of the fuel nozzle.

Abstract: A fuel system a main manifold with an inlet and a plurality of main manifold branches. Each valve in a plurality of valves is connected in fluid communication with a respective one of the main manifold branches in the plurality of main manifold branches to receive flow from the main manifold. Each secondary manifold in a plurality of secondary manifolds connects a single one of the valves in the plurality of valves to a pair of secondary manifold branches. Each nozzle in a plurality of fuel nozzles includes a first inlet connected in fluid communication to one of the valves through one of the secondary manifold branches, and a second inlet connected in fluid communication to a different one of the valves through a different one of the secondary manifold branches so each of the fuel nozzles has a redundant connection to the main manifold through two of the valves.

Abstract: A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal.

Abstract: A multi-stage micro-decomposition swirl burner with an ammonia-doped fuel, and a low NOx control method are provided. A natural gas central pipe, a primary air pipe and a burner housing are nested from inside to outside in sequence to form a primary air duct and an over-fire air channel which are isolated from each other. Natural gas is ejected from the natural gas central pipe, and swirl vanes are arranged in the primary air duct, such that the primary air can be mixed with the central natural gas in a swirl state, and then a diffusion flame is formed under the action of an ignition device. Therefore, a pilot flame with sustainable combustion is formed at the center of an injection end of the burner.

Abstract: The present disclosure relates to a gas turbine plant which decomposes ammonia into a decomposition gas including hydrogen and supplies the decomposition gas as fuel to a combustor of the gas turbine. The gas turbine plant supplies sufficient heat to the ammonia in order to thermally decompose the ammonia effectively and separates the residual ammonia present in the decomposition gas and supplies the decomposition gas to a combustor of the gas turbine.

Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.

Abstract: This performance evaluation device comprises: an acquisition unit which acquires a sampling value of a gas turbine output and a sampling value of a steam turbine output, measured at each time during the operation of a combined cycle power generation plant that generates power using the gas turbine and the steam turbine; and an output calculation unit which obtains a plant output that is a total output of the sampling value of the gas turbine output measured at a first time and the sampling value of the steam turbine that is the steam turbine output corresponding to the gas turbine output at the first time and is measured at a second time after a predetermined delay from the first time.

Abstract: The present disclosure provides a central staged combustion chamber with self-excited sweeping oscillating fuel injection nozzles, including an outer housing with a cavity inside, a main stage coaxially disposed with the outer housing, and a pilot stage coaxially disposed with the outer housing. An annular fuel passage is used for connecting a plurality of self-excited sweeping oscillating fuel injection nozzles, and the self-excited sweeping oscillating fuel injection nozzles are suitable for injecting oscillating liquid fuel into a primary swirling passage. The fuel is output in a fan shape through each of the self-excited sweeping oscillating fuel injection nozzles and is dispersed by an incoming flow through the swirling passage, so that the atomization performance and spatial distribution uniformity of the fuel can be greatly improved.

Abstract: A combustion device includes: an ammonia tank; a combustor connected to the ammonia tank; an air supply source; and an ammonia autothermal cracking device having inlets connected to the ammonia tank and the air supply source and an outlet connected to the combustor.

Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall having a liquid swirler inner wall end portion angled radially outward from the nozzle axis, a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially outward from the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween.

Abstract: A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. The fuel inlet portion is configured to receive a flow of a fuel, with an inlet to the fuel stem portion being fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion being fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion comprises an outer air swirler and an inner air swirler, with the inner air swirler being positioned concentrically within the outer air swirler. The outer air swirler comprises a plurality of first vanes that are arranged in an annular array within an outer air swirler body and is configured to impose a first rotational flow component on an air flow entering the outer air swirler.

Abstract: A system includes a gas turbine having a turbine stage disposed in a combustion gas path, wherein the turbine stage includes turbine vanes disposed upstream from turbine blades. The system includes an isothermal expansion system coupled to the turbine stage. The isothermal expansion system includes multi-fluid injectors configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion, wherein at least one of the multi-fluid injectors is coupled to each of the turbine vanes. Each of the multi-fluid injectors includes a fuel port configured to inject a fuel, an oxidant port configured to inject an oxidant, and a barrier fluid port configured to inject a barrier fluid between the fuel and the oxidant, wherein the barrier fluid is configured to delay mixing between the fuel and the oxidant.

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.