General Electric Company

Thomas Edward Brinson

Michael J Epstein

Kevin Richard Leamy

Benjamin Paul Breig

Javier Armando Parrilla

Matthew John Hurt

Andrew James Fleming

Paul Robert Gemin

George Eugene Wilmot, Jr

George Eugene Wilmot

Michael Jay Epstein

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.

Mechanically driven air vehicle thermal management device

Methods and devices for cooling systems () are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler () receiving bleed air from the jet engine compressor; a heat exchanger () downstream from the first precooler (); a cooling system compressor () downstream from the first precooler (), wherein the heat exchanger () and the cooling system compressor () are in separate flow paths from the first precooler (); a cooling system precooler () downstream from the cooling system compressor (); a VGT cooling system turbine () downstream from the cooling system precooler (); and a discharge conduit () downstream from the cooling system turbine () and the heat exchanger (). A bypass line () for bypassing the turbine can also be included.

Jet engine cold air cooling system

Methods and devices for cooling systems () are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler () receiving bleed air from the jet engine compressor; a heat exchanger () downstream from the first precooler (); a cooling system compressor () downstream from the first precooler (), wherein the heat exchanger () and the cooling system compressor () are in separate flow paths from the first precooler (); a cooling system precooler () downstream from the cooling system compressor (); a cooling system turbine () with variable guide vanes&#x2014;VGT&#x2014;and downstream from the cooling system precooler (); and a discharge conduit () downstream from the cooling system turbine () and the heat exchanger (). A bypass line () can also be included that bypasses the cooling system turbine ().

Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.

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Mason, OH, United States of America

Thomas Edward Brinson