Gasturbinenmotor-Doppelbrennstoff-Brennkammer und Betriebsverfahren

Details

Veröffentlichungs-Nr.

EP4756292

Anmeldetag

3. Dezember 2025

Veröffentlichung

10. Juni 2026

Rechtsraum

EP

IPC

F23R3/34, F23R3/36, F23R3/38

Abstract

A combustor (26) for a gas turbine engine is provided that includes an annular combustor shell (34), a plurality of fuel nozzles (36), a rotary fuel slinger (38), and a plurality of first igniters (54). The annular combustor shell (34) includes front and rear annular liners (34A, 34B) that collectively form the combustor shell (34) and define a combustion chamber (40) that includes inner and outer radial combustion zones (40A, 40B). The fuel nozzles (36) are engaged with the front annular liner (34A) and the outer radial combustion zone (40B), and the fuel nozzles (36) are configured to inject a first fuel. The rotary fuel slinger (38) is engaged with the combustor shell (34) and configured to deliver a second fuel into the inner radial combustion zone (40A). The first fuel is a different type of fuel than the second fuel. The first igniters (54) are engaged with the outer radial combustion zone (40B) and are configured to ignite the first fuel.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete