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 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 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: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a temperature of the catalytic reactor.

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 an engine can include a fuel circuit and a primary fuel pump in fluid communication with the fuel circuit and configured to pump fuel to the engine as a function of engine speed. The primary fuel pump is configured to pump insufficient fuel flow to the engine during at least one engine speed or speed range. The system also includes a supplemental fuel pump in fluid communication with the fuel circuit configured to selectively pump fuel to the engine at least during the at least one engine speed or speed range to supplement fuel flow from the primary fuel pump to provide sufficient total fuel flow to the engine during all engine speeds.

Abstract: A system and method fare disclosed for inerting a protected space. Process water is delivered to an anode of an electrochemical cell where a portion of the process water is electrolyzed to form protons and oxygen. The protons are transferred across the separator to the cathode, and process water is directed through a process water fluid flow path including a first side of a membrane. Gas is transferred to a second side of the membrane to form a de-gassed process water on the first side of the membrane, and the de-gassed process water is recycled to the anode. Air is delivered to the cathode and oxygen is reduced at the cathode to generate oxygen-depleted air. The oxygen-depleted air is directed from the cathode of the electrochemical cell along an inerting gas flow path to the protected space.

Abstract: A system and method for inerting a protected space is disclosed. According to the method, process water is delivered to an anode of an electrochemical cell comprising the anode and a cathode separated by a separator comprising a proton transfer medium. A portion the process water is electrolyzed at the anode to form protons and oxygen, and the protons are transferred across the separator to the cathode. Process water is directed through a process water fluid flow path including a gas outlet, and a pressure differential is applied between the process water fluid flow path and a discharge side of the gas outlet to remove gas from the process water. Air is delivered to the cathode and oxygen is reduced at the cathode to generate oxygen-depleted air, which is directed from the cathode along an inerting gas flow path to the protected space.

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: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a space velocity through the catalytic reactor.

Abstract: Systems and methods for generating inerting gas on vehicles are described. The systems include a proton exchange membrane (PEM) inerting system, a pure water replenishment system configured to provide pure water to the PEM inerting system, wherein the pure water replenishment system is in fluid communication with the PEM inerting system to replenish water lost during operation of the PEM inerting system, and a control system configured to control operation of the pure water replenishment system to automatically replenish pure water to the PEM inerting system.

Abstract: Systems and methods for generating inerting gas on vehicles are described. The systems include a proton exchange membrane (PEM) inerting system, a pure water supply system configured to provide pure water to the PEM inerting system, wherein the pure water supply system is in fluid communication with the PEM inerting system to replenish water lost during operation of the PEM inerting system, and a recapture loop configured to direct at least one of moisture and water from an output of the PEM inerting system back into the PEM inerting system, wherein the recapture loop includes a water treatment system.

Abstract: Redundant electrochemical systems and methods for vehicles are described. The systems include a first electrochemical device located at a first position on the vehicle wherein the first electrochemical device is configured to generate at least one of inert gas, oxygen, and electrical power and a second electrochemical device located at a second position on the vehicle wherein the second electrochemical device is configured to generate at least one of inert gas, oxygen, and electrical power. The first electrochemical device is configured to operate in a first mode during normal operation of the vehicle and a second mode when the second electrochemical device fails, wherein in the second mode, the first electrochemical device provides the at least one of inert gas, oxygen, and electrical power for at least one vehicle critical system of the vehicle.

Abstract: A system is disclosed for aircraft life support and generating inert gas. The system includes an electrochemical cell with a cathode and an anode separated by a proton transfer medium. A cathode supply fluid flow path is between an air source and a cathode fluid flow path inlet, and an inerting gas flow path is in operative fluid communication with a cathode fluid flow path outlet and a protected space. An anode supply fluid flow path is between a water source and an anode fluid flow path inlet, and an oxygen gas flow path is in operative fluid communication with an anode fluid flow path outlet and an aircraft occupant breathing device. An electrical connection is between a power source and the electrochemical cell.

Abstract: A fuel system for a gas turbine engine includes a primary fuel pump providing fuel flow during engine operation and a primary electric motor coupled to the primary fuel pump for driving the primary fuel pump during engine operation. A secondary system provides fuel flow in the absence of fuel flow from the primary fuel pump.

Abstract: A fuel system for an engine can include a fuel circuit and a primary fuel pump in fluid communication with the fuel circuit and configured to pump fuel to the engine as a function of engine speed. The primary fuel pump is configured to pump insufficient fuel flow to the engine during at least one engine speed or speed range. The system also includes a supplemental fuel pump in fluid communication with the fuel circuit configured to selectively pump fuel to the engine at least during the at least one engine speed or speed range to supplement fuel flow from the primary fuel pump to provide sufficient total fuel flow to the engine during all engine speeds.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a space velocity through the catalytic reactor.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises an inlet temperature of a gas at an inlet of the catalytic reactor.