Gas turbine engine with insulated cooling circuit

A gas turbine engine 110 is provided comprising a compressor 112 with an insulated cooling circuit 310. The compressor 112 comprises a compressor casing 118 having a compression chamber 119 and at least one stator 128 and at least one rotor 126 disposed in the compression chamber 119, the at least o...

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Bibliographische Detailangaben
Hauptverfasser:	WALKER, Roger, PARKER, William, VEDHAGIRI, Sivaraman, DAVIDSON, Dwight, LIU, Yang, CARUSO, Philip
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 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 MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine 110 is provided comprising a compressor 112 with an insulated cooling circuit 310. The compressor 112 comprises a compressor casing 118 having a compression chamber 119 and at least one stator 128 and at least one rotor 126 disposed in the compression chamber 119, the at least one stator 128 comprising a stator body 210 having a plurality of tubes 320 for transporting cooling air 322 through passages 312 in the stator body 210 into the compression chamber 119. The plurality of tubes 320 are surrounded by an air gap 328 for insulating the tubes from the stator body 210.