GAS TURBINE ENGINE COMPRESSOR COMPONENT COMPRISING THERMAL BARRIER, THERMAL BARRIER SYSTEM, AND METHOD OF USING THE SAME

摘要

PROBLEM TO BE SOLVED: To provide a means for protecting materials from an environment of a high temperature and the high stress of a compressor of a gas turbine engine.

SOLUTION: A thermal barrier 20 operable to maintain the temperature of the shaft below about 700°C (1,300°F) is arranged at least at a first surface 13 of a shaft 14 located at a hot flow path side 16 of gas turbine engine compressor disks 10, 12 even if the hot flow path side 16 reaches a service operating temperature of from about 700°C (1,300°F) to about 788°C (1,450°F).

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