A system is provided. The system includes a first inlet providing a medium from a source; a compressing device in communication with the first inlet; and at least one heat exchanger. The compressing device includes a compressor that receives the medium and a turbine downstream of the compressor. The system is powered by mechanical power from the medium and by electrical power through a motor. The motor input power is less than or equal to 0.5 kilowatt per pounds per minute of the medium compressed.

A system is provided. The system includes a first inlet providing a medium from a source; a compressing device in communication with the first inlet; and at least one heat exchanger. The compressing device includes a compressor that receives the medium and a turbine downstream of the compressor. The system is powered by mechanical power from the medium and by electrical power through a motor. The motor input power is less than or equal to 0.5 kilowatt per pounds per minute of the medium compressed.

The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide systems and ways for improving gas turbine engine reliability through an electric motor backup system for cooling features of the turbine section.

A twin-vaned nozzle ring for a turbine nozzle of a turbocharger nozzle ring is made by assembling the nozzle ring from three separately formed parts. A center part includes a first ring of circumferentially spaced first vanes and a second ring of circumferentially spaced second vanes, the first and second rings being axially spaced and integrally joined to each other. The first vanes are circumferentially offset from the second vanes, and exits from the first vane passages are radially aligned with and circumferentially interleaved with exits from the second vane passages. First and second side walls are provided as separate parts. Finally, the first side wall is joined to a distal or outer face of the first ring, and the second side wall is joined to a distal face of the second ring to complete the assembly.

A twin-vaned nozzle ring for a turbine nozzle of a turbocharger nozzle ring is made by assembling the nozzle ring from three separately formed parts. A center part includes a first ring of circumferentially spaced first vanes and a second ring of circumferentially spaced second vanes, the first and second rings being axially spaced and integrally joined to each other. The first vanes are circumferentially offset from the second vanes, and exits from the first vane passages are radially aligned with and circumferentially interleaved with exits from the second vane passages. First and second side walls are provided as separate parts. Finally, the first side wall is joined to a distal or outer face of the first ring, and the second side wall is joined to a distal face of the second ring to complete the assembly.

The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

The turbomachine comprises a casing arrangement and a shaft supported for rotation therein. The shaft is rotatingly supported by a first and second bearing unit. First and second compressor sections are provided in the casing arrangement. The first compressor section comprises a first compressor impeller mounted on the shaft for rotation therewith, and the second compressor section comprises a second compressor impeller mounted on the shaft for rotation therewith. The turbomachine further comprises a first turboexpander and a second turboexpander mounted on the shaft for rotation therewith in the casing arrangement.

The turbomachine comprises a casing arrangement and a shaft supported for rotation therein. The shaft is rotatingly supported by a first and second bearing unit. First and second compressor sections are provided in the casing arrangement. The first compressor section comprises a first compressor impeller mounted on the shaft for rotation therewith, and the second compressor section comprises a second compressor impeller mounted on the shaft for rotation therewith. The turbomachine further comprises a first turboexpander and a second turboexpander mounted on the shaft for rotation therewith in the casing arrangement.

A combined cycle heat engine (10). The engine (10) comprises a first gas turbine engine (11) comprising a first air compressor system (14), a first combustion system (16) and a first turbine system (18) and a second gas turbine engine (32) comprising a second air compression system (36), a second turbine system (40), and a heat exchanger (38) configured to transfer heat from an exhaust (24) of the first turbine system (18) to compressed air from the second air compressor (36). The second gas turbine engine (32) comprises a second combustion system (20) downstream of the heat exchanger (38) and upstream of the second turbine system (40).