Abstract: A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as a residual flow. The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow. A combustor is configured to receive and combust the hydrogen flow from the separation device to generate a gas flow. A compressor section is configured to supply compressed air to the combustor. A turbine section is in flow communication with the gas flow produced by the combustor and is mechanically coupled to drive the compressor section.

Abstract: A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as a residual flow. The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow. A combustor is configured to receive and combust the hydrogen flow from the separation device to generate a gas flow. A compressor section is configured to supply compressed air to the combustor. A turbine section is in flow communication with the gas flow produced by the combustor and is mechanically coupled to drive the compressor section.

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

Abstract: A fuel system for a gas turbine engine includes a main fuel pump generating a main fuel flow into a main fuel passage and a secondary pump generating a secondary fuel flow into a secondary flow passage. A first control valve is disposed in a passage between the main fuel passage and the secondary flow passage. The first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow.

Abstract: A gas turbine engine includes a cracking device that is configured to decompose a portion of an ammonia flow into a flow of component parts of the ammonia flow, a thermal transfer device that is configured to heat the ammonia flow to a temperature above 500° C. (932° F.), a combustor that is configured to receive and combust the flow of component parts of the ammonia flow to generate a high energy gas flow, a compressor section that is configured to supply compressed air to the combustor, and a turbine section in flow communication with the high energy gas flow produced by the combustor and mechanically coupled to drive the compressor section.

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

Abstract: A process for designing an internal turbine engine component including operating a test rig incorporating a physical morphing component having a first geometry and generating a data set of empirically determined component performance parameters corresponding to the first geometry. Providing the data set of empirically determined component performance parameters to a computational optimization system and automatically. Determining a geometry optimization of the morphing component. Altering the geometry of the morphing component to match the geometry optimization. Reiterating operating the test rig and providing the data set of empirically determined component performance parameters.

Abstract: An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.

Abstract: A fuel system for a gas turbine engine includes a main fuel pump generating a main fuel flow into a main fuel passage and a secondary pump generating a secondary fuel flow into a secondary flow passage. A first control valve is disposed in a passage between the main fuel passage and the secondary flow passage. The first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow.

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

Abstract: A process for designing an internal turbine engine component including operating a test rig incorporating a physical morphing component having a first geometry and generating a data set of empirically determined component performance parameters corresponding to the first geometry. Providing the data set of empirically determined component performance parameters to a computational optimization system and automatically. Determining a geometry optimization of the morphing component. Altering the geometry of the morphing component to match the geometry optimization. Reiterating operating the test rig and providing the data set of empirically determined component performance parameters.

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

Abstract: A turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes, a liquid hydrogen fuel storage tank that is configured to maintain the liquid hydrogen fuel at a pressure greater than an external pressure and less than 20 bar, an electric machine that is in thermal communication with a liquid hydrogen fuel flow from the liquid hydrogen fuel storage tank, the liquid hydrogen fuel flow is configured to maintain at least a component of the electric machine at an operating temperature below an ambient temperature, and a fuel system that is configured to receive gas hydrogen fuel flow and communicate the gas hydrogen fuel flow to a power generation device.

Abstract: A process for designing an internal turbine engine component including operating a test rig incorporating a physical morphing component having a first geometry and generating a data set of empirically determined component performance parameters corresponding to the first geometry. Providing the data set of empirically determined component performance parameters to a computational optimization system and automatically. Determining a geometry optimization of the morphing component. Altering the geometry of the morphing component to match the geometry optimization. Reiterating operating the test rig and providing the data set of empirically determined component performance parameters.

Abstract: A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as a residual flow. The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow. A combustor is configured to receive and combust the hydrogen flow from the separation device to generate a gas flow. A compressor section is configured to supply compressed air to the combustor. A turbine section is in flow communication with the gas flow produced by the combustor and is mechanically coupled to drive the compressor section.

Abstract: A gas turbine engine includes a cracking device that is configured to decompose a portion of an ammonia flow into a flow of component parts of the ammonia flow, a thermal transfer device that is configured to heat the ammonia flow to a temperature above 500° C. (932° F.), a combustor that is configured to receive and combust the flow of component parts of the ammonia flow to generate a high energy gas flow, a compressor section that is configured to supply compressed air to the combustor, and a turbine section in flow communication with the high energy gas flow produced by the combustor and mechanically coupled to drive the compressor section.

Abstract: A turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes, a liquid hydrogen fuel storage tank that is configured to maintain the liquid hydrogen fuel at a pressure greater than an external pressure and less than 20 bar, an electric machine that is in thermal communication with a liquid hydrogen fuel flow from the liquid hydrogen fuel storage tank, the liquid hydrogen fuel flow is configured to maintain at least a component of the electric machine at an operating temperature below an ambient temperature, and a fuel system that is configured to receive gas hydrogen fuel flow and communicate the gas hydrogen fuel flow to a power generation device.

Abstract: An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.

Abstract: A process for designing an internal turbine engine component including operating a test rig incorporating a physical morphing component having a first geometry and generating a data set of empirically determined component performance parameters corresponding to the first geometry. Providing the data set of empirically determined component performance parameters to a computational optimization system and automatically. Determining a geometry optimization of the morphing component. Altering the geometry of the morphing component to match the geometry optimization. Reiterating operating the test rig and providing the data set of empirically determined component performance parameters.

Abstract: A fuel system for a gas turbine engine includes a main fuel pump generating a main fuel flow into a main fuel passage and a secondary pump generating a secondary fuel flow into a secondary flow passage. A first control valve is disposed in a passage between the main fuel passage and the secondary flow passage. The first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow.