Methods and apparatus for operating turbine engines using rotor temperature sensors

A gas turbine engine including a temperature sensor assembly that continuously monitors an operating temperature within a multi-stage rotor assembly of the turbine engine is described. A plurality of cavities are defined within the multi-stage rotor assembly. The temperature sensor assembly includes...

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Bibliographische Detailangaben
Hauptverfasser:	MONIZ THOMAS, DAMLIS NICHOLAS, SMITH, JR. JACK WILLARD, SCHLEUE JOSEPH HENRY, BOND DONALD RAY
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS 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 SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MEASURING MEASURING QUANTITY OF HEAT MEASURING TEMPERATURE MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PHYSICS STEAM ENGINES TESTING THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine including a temperature sensor assembly that continuously monitors an operating temperature within a multi-stage rotor assembly of the turbine engine is described. A plurality of cavities are defined within the multi-stage rotor assembly. The temperature sensor assembly includes a plurality of temperature sensor assemblies that monitor the temperature within each of the rotor assembly cavities. Each temperature sensor assembly includes a plurality of support guide tubes attached to the engine and extending from an outer casing of the engine to each cavity. A temperature sensor is inserted through the guide tubes and positioned within each cavity.