BUFFER SYSTEM THAT COMMUNICATES BUFFER SUPPLY AIR TO A PORTION OF A GAS TURBINE ENGINE

A gas turbine engine (20) includes a buffer system (60; 160; 260) that communicates a buffer supply air (62; 162; 262A, 262B) to a portion of the gas turbine engine (20). The buffer system (60; 160; 260) includes a first bleed air supply (64; 164; 264A, 264B) having a first pressure, a second bleed...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	MUNSELL, Peter M, STRIPINIS, Philip. S
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 POSITIVE-DISPLACEMENT ENGINEPLANTS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NOT OTHERWISE PROVIDED FOR STEAM ENGINES USE OF WASTE HEAT OF COMBUSTION ENGINES WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine (20) includes a buffer system (60; 160; 260) that communicates a buffer supply air (62; 162; 262A, 262B) to a portion of the gas turbine engine (20). The buffer system (60; 160; 260) includes a first bleed air supply (64; 164; 264A, 264B) having a first pressure, a second bleed air supply (66; 166; 266A, 266B) having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply (64; 164; 264A, 264B) and the second bleed air supply (66; 166; 266A, 266B) to communicate the buffer supply air (62; 162; 262A, 262B) to the portion of the gas turbine engine (20).