Gas turbine engine compressor components comprising thermal...

Details Gas turbine engine compressor components comprising thermal... Gas turbine engine compressor components comprising thermal...

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/24 (2006.01) F02C 3/04 (2006.01)

Patent

CA 2739210

Gas turbine engine compressor disk (10, 12) having a hot flowpath side (16); a shaft (14) having a first surface (13) positioned in the hot flowpath side (16); and a thermal barrier (20) applied to at least the first surface (13) of the shaft (14) wherein the thermal barrier is operable to maintain the temperature of the shaft below about 700°C (1300°F) when the hot flowpath side experiences a service operating temperature of from about 700°C (1300°F) to about 788°C (1450°F).

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