Brennkammerabschnitt für eine Turbomaschine

Details

Veröffentlichungs-Nr.

EP4711675

Anmeldetag

14. August 2025

Veröffentlichung

18. März 2026

Rechtsraum

EP

IPC

F23R3/28, F02C7/22

Abstract

A combustion section (102, 202, 302) for a turbine engine (100, 200, 300) comprises a circumferential casing (104) defining an interior (108), and a combustor (106, 206, 306) arranged within the interior (108). The combustor includes an annular liner (116, 216, 316) that defines a combustion chamber (124). Multiple fuel nozzles (130) open into the combustion chamber (124). A fuel supply system (142, 242, 342) is provided within the interior (108) and includes a fuel manifold (148, 248, 348) and multiple fuel line branches (146, 246, 346). Each fuel line branch (146, 246, 346) extends between a respective portion of the fuel manifold (148, 248, 348) and a corresponding portion of the combustor (106, 206, 306) or a respective one of the fuel nozzles (130), thereby supplying fuel to the combustion chamber (124).

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA