Methods and apparatus for testing gas turbine engines

Details Methods and apparatus for testing gas turbine engines Methods and apparatus for testing gas turbine engines

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/12 (2006.01) F01D 25/12 (2006.01) G01M 15/14 (2006.01)

Patent

CA 2590798

A cooling system (100) for a gas turbine engine (10) control system (99) is provided. The cooling system (100) includes an inlet portion (117) coupled in fluid communication with a source of cooling fluid, the inlet portion configured to channel cooling fluid from the cooling fluid source to the control system to facilitate cooling the control system, and an outlet portion (119) configured to channel cooling fluid from the control system to one of the cooling fluid source and a reservoir, and a differential pressure sensor (152) in flow communication with the inlet portion and the outlet portion, the differential pressure sensor configured to sense whether a pressure difference exists within the inlet and outlet portions.

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