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Gas turbine cooling system

United States Patent

October 2, 2001
View the Complete Patent at the US Patent & Trademark Office
A gas turbine engine (10) having a closed-loop cooling circuit (39) for transferring heat from the hot turbine section (16) to the compressed air (24) produced by the compressor section (12). The closed-loop cooling system (39) includes a heat exchanger (40) disposed in the flow path of the compressed air (24) between the outlet of the compressor section (12) and the inlet of the combustor (14). A cooling fluid (50) may be driven by a pump (52) located outside of the engine casing (53) or a pump (54) mounted on the rotor shaft (17). The cooling circuit (39) may include an orifice (60) for causing the cooling fluid (50) to change from a liquid state to a gaseous state, thereby increasing the heat transfer capacity of the cooling circuit (39).
Bancalari; Eduardo E. (Orlando, FL)
Siemens Westinghouse Power Corporation (Orlando, FL)
09/ 429,101
October 28, 1999
REFERENCE TO GOVERNMENT CONTRACTS Development for this invention was supported in part by U.S. Department of Energy Contract No. DE-FC21-95MC32267. Accordingly, the United States Government may have certain rights in is invention.