Gasturbinenbrennkammer und Betriebsverfahren

Details

Veröffentlichungs-Nr.

EP2479498

Aktenzeichen

EP12151967

Anmeldetag

20. Januar 2012

Veröffentlichung

5. Oktober 2016

Erteilung

5. Oktober 2016

Rechtsraum

EP

IPC

F23R3/06F23R3/34F23R3/50

Abstract

A combustor (30) for a gas turbine engine includes a radially inboard liner (36), a radially outboard liner (38), and a bulkhead (34) that cooperatively define an annular combustion chamber (32), a plurality of first fuel injectors (54) that are disposed in the bulkhead (34), and a plurality of second fuel injectors (62) that are disposed in at least one of the inboard liner (36) and the outboard liner (38) aftward of the bulkhead (34). A method is also provided for operating the combustor (30) wherein fuel distribution between a forward combustion zone (60) and a downstream combustion zone (64) is selectively varied in response to the power operating mode of the gas turbine engine with an objective to control NOx formation.

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete