F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 7/14 (2006.01) F01D 25/12 (2006.01) F02C 9/18 (2006.01)
Patent
CA 2716237
A gas turbine engine cooling system (6) includes a heat exchanger (56) in fluid communication with a source of cooling air (57), a first cooling circuit (62) including a first heat exchanger circuit (100) in the heat exchanger (56) and a first bypass circuit (110) with a first bypass valve (114) for selectively bypassing at least a portion of first airflow (118) around the first heat exchanger circuit (100). A second cooling circuit (102) may be used having a second heat exchanger circuit (104) in the heat exchanger (56) and a shutoff control valve (112) operably disposed in the second cooling circuit (102) upstream of the second heat exchanger circuit (104) and the heat exchanger (56). A circuit inlet (58) of the first cooling circuit (62) may be used to bleed a portion of compressor discharge bleed air (79) for the first airflow (118) to cool turbine blades (40) mounted on a rotor disk (42) using an annular flow inducer (84) downstream of the first bypass valve (114) and the heat exchanger (56).
Company General Electric
Craig Wilson And Company
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