Cooling air cooler for a gas turbofan engine
Method and apparatus for compressing gas
Heat and liquid recovery using open cycle heat pump system
Auxiliary refrigerated air system employing mixture of air bled from turbine engine compressor and air recirculated within auxiliary system
Auxiliary refrigerated air system employing input air from turbine engine compressor after bypassing and conditioning within auxiliary system Patent #: 5056335
ApplicationNo. 006417 filed on 01/21/1993
US Classes:62/402, Motor-type expander60/806, And cooling62/87Converting energy of expansion to mechanical movement
ExaminersPrimary: Capossela, Ronald C.
Attorney, Agent or Firm
Foreign Patent References
International ClassF25D 009/00
AbstractA gas turbine engine cooling system. Hotter engine compressor air is cooled by a heat exchanger using a colder engine fluid (such as fuel or lower pressure (colder) engine compressor air. The cooled air passes through the compressor section of an auxiliary turbocompressor and is used to cool the engine high pressure turbine. Some of the cooled air (or uncooled discharge air from the engine high pressure compressor) is used to drive the turbine section of the turbocompressor. The spent air exiting the turbine section of the turbocompressor is used to help cool the engine low pressure turbine.