Gas turbine engine compressor components comprising thermal barriers and method of using the same

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...

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Bibliographische Detailangaben
Hauptverfasser:	HURON, ERIC SCOTT, KONITZER, DOUGLAS GERARD, HAZEL, BRIAN THOMAS
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES ORMATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHERTHAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	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).