TURBINE CLEARANCE CONTROL SYSTEM AND METHOD FOR IMPROVED VARIABLE CYCLE GAS TURBINE ENGINE FUEL BURN

A method of assembling a gas turbine engine (20) includes setting a build clearance at assembly in response to a running tip clearance (108) defined with a cooled cooling air. Another method of operating a gas turbine engine (20) includes supplying a cooled cooling air to a high pressure turbine (32...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	LEDWITH, WALTER A. JR, HALL, THEODORE W, MILLER, ANDREW S, ROBAK, CHRISTOPHER W, PIMENTA, DAVID C, HANLON, CHRISTOPHER J, GRIFFIN, DAVID RICHARD, CARR, SCOTT A, WHITE, PETER A, FARRIS, JOHN R
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 JET-PROPULSION 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 method of assembling a gas turbine engine (20) includes setting a build clearance at assembly in response to a running tip clearance (108) defined with a cooled cooling air. Another method of operating a gas turbine engine (20) includes supplying a cooled cooling air to a high pressure turbine (32) in response to an engine rotor speed. A corresponding gas turbine engine (20) comprising a turbine clearance control, wherein a part of the core flow (60) is bled to be cooled in a heat exchanger (70) and then directed to the high pressure turbine section (32), wherein the heat exchanger cooling flow is a first by pass flow (58) coming from a second fan stage section and then directed to a second by pass flow (56) coming from a first stage fan section.