THERMALLY ACTUATED ASSEMBLY FOR A GAS TURBINE SYSTEM AND METHOD OF CONTROLLING A COOLING AIRFLOW PATH

A thermally actuated assembly (10) for a gas turbine assembly for a gas turbine system includes a heat transfer component (20) having a first portion (22) and a second portion (24), wherein the first portion (22) is disposed within a first cavity (14) having a first temperature and the second portio...

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Bibliographische Detailangaben
Hauptverfasser:	Liotta, Gary Charles, Miranda, Carlos Miguel
Format:	Patent
Sprache:	eng ; fre ; ger
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 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A thermally actuated assembly (10) for a gas turbine assembly for a gas turbine system includes a heat transfer component (20) having a first portion (22) and a second portion (24), wherein the first portion (22) is disposed within a first cavity (14) having a first temperature and the second portion (24) is disposed in a second cavity (16) having a second temperature, wherein the heat transfer component (20) extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element (26) disposed within the second cavity (16) and in operable communication with the heat transfer component (20). Further included is a flow manipulating device (30,32) disposed within the second cavity (16) and configured to displace in response to a temperature change in the first cavity (14).