Vane carrier temperature control system in a gas turbine engine

A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: LAURELLO VINCENT P, THAM KOK-MUN
Format: Patent
Sprache:eng
Schlagworte:
Online-Zugang:Volltext bestellen
Tags: Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
Beschreibung
Zusammenfassung:A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine. The second cooling air source supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section. The air temperature control system controls a temperature of at least one of the first and second portions of vane carrier cooling air.