General Electric Company

Matthew John Hurt

Donald Michael Corsmeier

Michael J Epstein

Ramon Martinez

Kevin Richard Leamy

Gregg Hunt Wilson

George Eugene Wilmot, Jr

Paul Charles Johnson

Benjamin Paul Breig

Javier Armando Parrilla

Thomas Edward Brinson

Andrew James Fleming

George Eugene Wilmot

Keith Alan Joerger

Michael Jay Epstein

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.

Growing community of inventors

Liberty Township, OH, United States of America

Matthew John Hurt