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

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...

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Hauptverfasser:	KONITZER DOUGLAS GERARD, HAZEL BRIAN T, HURON ERIC SCOTT
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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 NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS 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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Zusammenfassung:	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).