GAS TURBINE COMBUSTOR WITH IMPROVED QUENCH HOLES ARRANGEMENT

A gas turbine engine has a combustor module including an annular combustor (26) having a liner assembly that defines an annular combustion chamber (30) and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes (116) and a circumferential row of a p...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	Snyder, Timothy S, Kim, Won-Wook
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 gas turbine engine has a combustor module including an annular combustor (26) having a liner assembly that defines an annular combustion chamber (30) and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes (116) and a circumferential row of a plurality of smaller quench air admission holes (120) disposed downstream with respect to the flow of combustion gas products. The plurality of quench air admission holes (120) are arranged with respect to the plurality of relatively large dilution air admission holes (116) disposed upstream thereof such that there is associated with each dilution air admission hole (116) a first quench air admission hole (120) and a second quench air admission hole (120), the first quench air admission hole (120) being offset laterally in a first lateral direction and the second quench air admission hole (120) being offset laterally in a second lateral direction opposite to the first direction.