HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING CONDITIONED COMPRESSOR AIR

A gas turbine engine (20) comprises a compressor (24) including a disk (184) and a blade (182). A turbine rotor (188) has a disk and a blade (186). Turbine conditioning air (199) is supplied to the turbine rotor (188). The turbine conditioning air (199) passes across the disk (184) of the compressor...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	FORCIER, MATTHEW P, HIESTER, PAUL J
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine (20) comprises a compressor (24) including a disk (184) and a blade (182). A turbine rotor (188) has a disk and a blade (186). Turbine conditioning air (199) is supplied to the turbine rotor (188). The turbine conditioning air (199) passes across the disk (184) of the compressor (24) to condition the disk (184). A method of operating a gas turbine engine (20) is also disclosed.