GAS TURBINE ENGINE COMPRESSOR COMPONENTS COMPRISING THERMAL BARRIERS, THERMAL BARRIER SYSTEMS, AND METHODS OF USING THE SAME

Gas turbine engine compressor disks having a hot flowpath side; a shaft having a first surface positioned in the hot flowpath side; and a thermal barrier applied to at least the first surface of the shaft where the thermal barrier is operable to maintain the temperature of the shaft below about 700°...

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Bibliographische Detailangaben
Hauptverfasser: KONITZER DOUGLAS GERARD, HAZEL BRIAN THOMAS, HURON ERIC SCOTT
Format: Patent
Sprache:eng
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Zusammenfassung:Gas turbine engine compressor disks having a hot flowpath side; a shaft having a first surface positioned in the hot flowpath side; and a thermal barrier applied to at least the first surface of the shaft where 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.).