Brennkammerabschnitt für eine Turbomaschine

Details

Veröffentlichungs-Nr.

EP4782749

Anmeldetag

16. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

IPC

F23R3/14, F23R3/28, F23R3/36

Abstract

A combustion section (14) for a turbine engine (10), the combustion section (14) comprising a wall (46) at least partially forming a combustion chamber (50) and a fuel nozzle (48, 100, 200, 300, 400) extending through a respective portion of the wall (46), the fuel nozzle having a fuel nozzle body (102, 302, 402) defining a central channel (108, 208, 308, 408) and a fuel nozzle centerline (104, 304, 404), the central channel (108, 208, 308, 408) opening to the combustion chamber (50) at a fuel nozzle outlet (74), a swirler (110, 210, 310, 410) provided along the fuel nozzle body (102, 302, 402) and extending into the central channel (108, 208, 308, 408), the swirler (110, 210, 310, 410) having a helical vane (112, 212, 312, 412) wrapped circumferentially about the fuel nozzle centerline (104, 304, 404).

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete