A last chance screen for a fuel system includes a mesh that includes a first plurality of members extending in a first direction and a second plurality of members extending in a second direction and intersecting the first members. Openings are formed in the mesh between the first plurality of members and the second plurality of members. The first plurality of members and the second plurality of members have an airfoil shaped cross-section.

A last chance screen for a fuel system includes a mesh that includes a first plurality of members extending in a first direction and a second plurality of members extending in a second direction and intersecting the first members. Openings are formed in the mesh between the first plurality of members and the second plurality of members. The first plurality of members and the second plurality of members have an airfoil shaped cross-section.

A method of producing compressed air for use onboard an aircraft includes receiving compressor discharge air into an air channel of a fuel injector. The method also includes cooling the compressor discharge air within the air channel by heat exchange with fuel flowing in the fuel injector, and issuing cooled air from the internal air channel out of an engine case as a source of compressed air.

A method of producing compressed air for use onboard an aircraft includes receiving compressor discharge air into an air channel of a fuel injector. The method also includes cooling the compressor discharge air within the air channel by heat exchange with fuel flowing in the fuel injector, and issuing cooled air from the internal air channel out of an engine case as a source of compressed air.

A turbine engine system includes at least one hydrogen fuel tank, a core flow path heat exchanger in a core flow path; and engine systems located in the core flow path. The engine system including at least a compressor section, a combustor section having a burner, and a turbine section. The core flow path heat exchanger is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank through a hydrogen fuel supply line, passing through the core flow path heat exchanger and then supplied into the burner for combustion.

A turbine engine system includes at least one hydrogen fuel tank, a core flow path heat exchanger in a core flow path; and engine systems located in the core flow path. The engine system including at least a compressor section, a combustor section having a burner, and a turbine section. The core flow path heat exchanger is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank through a hydrogen fuel supply line, passing through the core flow path heat exchanger and then supplied into the burner for combustion.

An installation for supplying a cryogenic fuel to a combustion chamber of a turbine engine of an aircraft including a tank, a mixing chamber, and one or more heat exchangers. The tank stores cryogenic fuel in a and connects to a combustion chamber for supplying the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The one or more heat exchangers are provided between the cryogenic fuel and air of an air-conditioning circuit of the aircraft, mounted in a line connecting the tank for cryogenic fuel to the mixing chamber and in a line to be connected to the air-conditioning circuit of the aircraft, the heat exchange taking place therein so as to cool the air of the air-conditioning circuit of the aircraft and to increase the temperature of the cryogenic fuel coming from the tank.

An installation for supplying a cryogenic fuel to a combustion chamber of a turbine engine of an aircraft including a tank, a mixing chamber, and one or more heat exchangers. The tank stores cryogenic fuel in a and connects to a combustion chamber for supplying the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The one or more heat exchangers are provided between the cryogenic fuel and air of an air-conditioning circuit of the aircraft, mounted in a line connecting the tank for cryogenic fuel to the mixing chamber and in a line to be connected to the air-conditioning circuit of the aircraft, the heat exchange taking place therein so as to cool the air of the air-conditioning circuit of the aircraft and to increase the temperature of the cryogenic fuel coming from the tank.

A cryogenic fuel supply system includes a storage tank, a mixing chamber, an auxiliary heating device, a heat exchanger, and flow distribution devices, and a controller. The storage tank stores cryogenic fuel in a liquid state. The mixing chamber receives various flows of cryogenic fuel in a supercritical or gaseous state, the mixing chamber being connected to a combustion chamber to supply the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The auxiliary heating device heats the cryogenic fuel. The heat exchanger assembly includes a cryogenic fuel/oil heat exchanger and a heat exchanger between the cryogenic fuel and the air circulating in a primary duct of the turbine engine. A flow distribution device is upstream of the auxiliary heating device, and one or more flow distribution devices are disposed upstream of the heat exchanger assembly. The controller controls opening and closing of the flow distribution devices.

A cryogenic fuel supply system includes a storage tank, a mixing chamber, an auxiliary heating device, a heat exchanger, and flow distribution devices, and a controller. The storage tank stores cryogenic fuel in a liquid state. The mixing chamber receives various flows of cryogenic fuel in a supercritical or gaseous state, the mixing chamber being connected to a combustion chamber to supply the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The auxiliary heating device heats the cryogenic fuel. The heat exchanger assembly includes a cryogenic fuel/oil heat exchanger and a heat exchanger between the cryogenic fuel and the air circulating in a primary duct of the turbine engine. A flow distribution device is upstream of the auxiliary heating device, and one or more flow distribution devices are disposed upstream of the heat exchanger assembly. The controller controls opening and closing of the flow distribution devices.