Gas turbine engine cooling system
Patent 5392614 Issued on February 28, 1995. Estimated Expiration Date: 
January 21, 2013. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
January 21, 2013. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 2970437 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 InventorAssigneeApplicationNo. 006417 filed on 01/21/1993US Classes:62/402, Motor-type expander60/806, And cooling62/87Converting energy of expansion to mechanical movementExaminersPrimary: Capossela, Ronald C.Attorney, Agent or FirmForeign Patent References
International ClassF25D 009/00AbstractA 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. | |
