Methods and systems for cooling gas turbine engine igniter tubes

A combustor for a gas turbine engine includes a plurality of igniter tubes (64) that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner (40) that includes a plurality of openings (66) sized to receive...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	STAKER, JOHN ROBERT, KUTTER, ELLA CHRISTINE, FARMER, GILBERT, VISE, STEVEN CLAYTON, HARRIS, TARIQ KAY, AL-ROUB, MARWAN
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A combustor for a gas turbine engine includes a plurality of igniter tubes (64) that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner (40) that includes a plurality of openings (66) sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device (120) that extends radially outward from the igniter tube. During operation, airflow (190) contacting the air impingement device is channeled radially inward (192) by a scoop portion (122) for impingement cooling of the igniter tubes and the combustor outer liner.