Waste heat management systems are described. The waste heat management systems include a turbine engine having a compressor section, a combustor section, a turbine section, and a nozzle. The compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle. The waste heat management systems also include an auxiliary power unit (APU) system and a waste heat recovery system operably connected to the APU system. The APU system is integrated into a working fluid flow path of the waste heat recovery system.

Power generation systems are described. The systems include a shaft, a compressor operably coupled to a first end of the shaft, a turbine operably coupled to a second end of the shaft, a generator operably coupled to the shaft between the compressor and the turbine, and a working fluid arranged in a closed-loop flow path that flows through each of the compressor and the turbine to drive rotation of the shaft. The shaft includes an internal fluid conduit configured to receive a portion of the working fluid at one of the first end and the second end and convey the portion of the working fluid through the generator to the other of the first end and the second end, wherein the portion of the working fluid is rejoined with a primary flow path of the working fluid.

A heat exchanger which may be used in an engine, such as a vehicle engine for an aircraft or orbital launch vehicle. is provided. The heat exchanger may be configured as generally drum-shaped with a multitude of spiral sections, each containing numerous small diameter tubes. The spiral sections may spiral inside one another. The heat exchanger may include a support structure with a plurality of mutually axially spaced hoop supports, and may incorporate an intermediate header. The heat exchanger may incorporate recycling of methanol or other antifreeze used to prevent blocking of the heat exchanger due to frost or ice formation.

A heat exchanger which may be used in an engine, such as a vehicle engine for an aircraft or orbital launch vehicle. is provided. The heat exchanger may be configured as generally drum-shaped with a multitude of spiral sections, each containing numerous small diameter tubes. The spiral sections may spiral inside one another. The heat exchanger may include a support structure with a plurality of mutually axially spaced hoop supports, and may incorporate an intermediate header. The heat exchanger may incorporate recycling of methanol or other antifreeze used to prevent blocking of the heat exchanger due to frost or ice formation.

Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.

Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.

A system is provided. The system includes an inlet providing a first medium; an inlet providing a second medium; a compressing device including a compressor and a turbine; and at least one heat exchanger located downstream of the compressor. The compressing device is in communication with the inlet providing the first medium. The turbine is downstream of the compressor. An outlet of the at least one heat exchanger is in fluid communication with an inlet of the compressor and an inlet of the turbine.

A system is provided. The system includes an inlet providing a first medium; an inlet providing a second medium; a compressing device including a compressor and a turbine; and at least one heat exchanger located downstream of the compressor. The compressing device is in communication with the inlet providing the first medium. The turbine is downstream of the compressor. An outlet of the at least one heat exchanger is in fluid communication with an inlet of the compressor and an inlet of the turbine.

The present invention provides a direct-fired supercritical carbon dioxide power generation system and a power generation method thereof, the system comprising: a combustor for burning hydrocarbon fuel and oxygen; a turbine driven by combustion gas discharged from the combustor; a heat exchanger for cooling combustion gas discharged after driving the turbine, by heat exchange with combustion gas recycled and supplied to the combustor; and an air separation unit for separating air to produce oxygen, wherein a portion of the combustion gas discharged after driving the turbine is branched before being introduced to the heat exchanger and is supplied to the air separation unit.

The present invention provides a direct-fired supercritical carbon dioxide power generation system and a power generation method thereof, the system comprising: a combustor for burning hydrocarbon fuel and oxygen; a turbine driven by combustion gas discharged from the combustor; a heat exchanger for cooling combustion gas discharged after driving the turbine, by heat exchange with combustion gas recycled and supplied to the combustor; and an air separation unit for separating air to produce oxygen, wherein a portion of the combustion gas discharged after driving the turbine is branched before being introduced to the heat exchanger and is supplied to the air separation unit.