Abstract: A system is provided for energy recovery. The system includes a heat recovery unit. The heat recovery unit is configured to receive at least one of heat or steam from a methanization reactor operating to convert carbon dioxide (CO2) and supplied hydrogen (H2) via methanization to produce methane (CH4), generate energy using at least one of the heat or the steam from the methanization reactor, and supply the generated energy to at least one of a carbon/carbon (C/C) preform production process, a separator, or another system.

Abstract: A system is provided for carbon dioxide (CO2) emission recovery. The system includes a methanization reactor. The methanization reactor is configured to receive CO2 separated from one or more off gases of a brake manufacturing process, convert the CO2 and supplied hydrogen (H2) via methanization to produce methane (CH4); and supply the produced CH4 to at least one of a carbon/carbon (C/C) preform production process or another system for heat generation.

Abstract: An aircraft system includes a thermal load, a controller, a tank for storing a cooling liquid, and a supply system for moving the cooling liquid outwardly of the tank and through a control valve to the thermal load. A controller is programmed to control the supply system. A conduit downstream of the thermal load is configured to communicate the cooling liquid to a fuel metering unit. The fuel metering unit also receives fuel from a high pressure pump. The fuel metering unit is configured to deliver a mixture of the cooling liquid and the fuel into a combustor on an associated aircraft engine. The controller programmed to determine a percentage solubility of the cooling fluid into the fuel at a detected temperature and pressure of the fuel reaching the fuel metering unit. The cooling fluid is combustible and soluble in the fuel. An aircraft and a method are also disclosed.

Abstract: An aircraft system includes a thermal load, a controller, a tank for storing a cooling liquid, and a supply system for moving the cooling liquid outwardly of the tank and through a control valve to the thermal load. A controller is programmed to control the supply system. A conduit downstream of the thermal load is configured to communicate the cooling liquid to a fuel metering unit. The fuel metering unit also receives fuel from a high pressure pump. The fuel metering unit is configured to deliver a mixture of the cooling liquid and the fuel into a combustor on an associated aircraft engine. The controller programmed to determine a percentage solubility of the cooling fluid into the fuel at a detected temperature and pressure of the fuel reaching the fuel metering unit. The cooling fluid is combustible and soluble in the fuel. An aircraft and a method are also disclosed.

Abstract: Disclosed is an electrochemical process to simultaneously produce a syngas suitable for the Fischer-Tropsch (F-T) process and oxygen. In an example embodiment, the process includes feeding steam and CO2 to an intermediate temperature (e.g., <700° C.) electrochemical reactor to produce separate CO-rich and O2-rich streams. An additional electrochemical reactor can be used to produce H2. The H2 is combined with CO from the first reactor to produce a syngas mixture ideal for a downstream F-T process. Alternatively, the electrochemical reactor can produce methane directly or a methanol stream for conversion to a hydrocarbon fuel.

Abstract: An exhaust moisture removal system for an electric generation system including: a sorbent wheel; an interchanger; a hydrogen evaporator including an exhaust portion; and an exhaust outflow stream passageway configured to convey an exhaust from a hydrogen fuel cell of the electric generation system through a first pass and then through a second pass, the second pass being located downstream of the first pass, wherein the first pass of the exhaust outflow stream passageway passes through the sorbent wheel, then through the interchanger, and then through the hydrogen evaporator, and wherein the second pass of the exhaust outflow stream passageway passes through the hydrogen evaporator, then through the interchanger, and then through the sorbent wheel.

Abstract: Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.

Abstract: An exhaust moisture removal system for an electric generation system including: a sorbent wheel; an interchanger; a hydrogen evaporator including an exhaust portion; and an exhaust outflow stream passageway configured to convey an exhaust from a hydrogen fuel cell of the electric generation system through a first pass and then through a second pass, the second pass being located downstream of the first pass, wherein the first pass of the exhaust outflow stream passageway passes through the sorbent wheel, then through the interchanger, and then through the hydrogen evaporator, and wherein the second pass of the exhaust outflow stream passageway passes through the hydrogen evaporator, then through the interchanger, and then through the sorbent wheel.

Abstract: A system includes a first sensor positioned to sense presence of a contrail in a first volume, wherein the first volume at least partially overlaps an expected volume of a contrail proximate an aircraft. A second sensor is positioned to sense a background reference in a second volume, where the second volume does not overlap the expected volume of a contrail proximate an aircraft. A controller is operatively connected to the first and second sensors. The controller includes machine readable instructions configured to cause the controller to utilize data input from both the first and second volumes to determine if a contrail is present from the aircraft. A system includes machine readable instructions configured to cause the controller to predict persistence of contrails on an intended route through the volume of airspace and to determine an improved route and/or propulsion operation to reduce contrail formation and persistence relative to the intended route.

Abstract: A method for providing inert gas to a protected space. The method includes: providing air having a pressure greater than or equal to 2 atmospheres absolute pressure to a chemical inert gas generator; producing an inert gas in the chemical inert gas generator; providing the inert gas to a condenser at an elevated pressure; reducing the water content of the inert gas in the condenser; and providing the dried inert gas to a protected space.

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 system and method for providing dried inert gas to a protected space is disclosed.

Abstract: A method of applying a trivalent chromium or chromium-free conversion coating to a metallic substrate including mixing a dye compound that interacts with electromagnetic radiation outside the human visual spectrum but not electromagnetic radiation that is within the human visual spectrum to produce an observable emission into the trivalent chromium or chromium-free conversion coating mixture to allow for inspection of the coating after applied with a correlating electromagnetic radiation source.

Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.

Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid 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 temperature of the catalytic reactor.

Abstract: A system and method for providing dried inert gas to a protected space is disclosed.

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: An environmental control system (ECS) for an aircraft includes a primary heat exchanger, a compressor including an inlet fluidically connected to the primary heat exchanger, a turbine operatively connected to the compressor, and a cryogenic fluid heat exchanger fluidically connected to the primary heat exchanger.

Abstract: An exhaust moisture removal system for an electric generation system including: a sorbent wheel; an interchanger; a hydrogen evaporator including an exhaust portion; and an exhaust outflow stream passageway configured to convey an exhaust from a hydrogen fuel cell of the electric generation system through a first pass and then through a second pass, the second pass being located downstream of the first pass, wherein the first pass of the exhaust outflow stream passageway passes through the sorbent wheel, then through the interchanger, and then through the hydrogen evaporator, and wherein the second pass of the exhaust outflow stream passageway passes through the hydrogen evaporator, then through the interchanger, and then through the sorbent wheel.