Brennkammerabschnitt für eine Turbomaschine

Details

Veröffentlichungs-Nr.

EP4772796

Anmeldetag

6. November 2025

Veröffentlichung

8. Juli 2026

Rechtsraum

EP

IPC

F23R3/14, F23R3/28

Abstract

A combustion section (100, 200) for a turbine engine (10) includes a combustor (102, 202) having a combustion chamber (108, 208) and a fuel nozzle (104, 204, 304, 404, 504) for delivering an air-fuel mixture into the combustion chamber (108, 208). The fuel nozzle comprises a body (112, 212, 312, 412, 512) defining a centerline (114, 214, 314, 414, 514) and a central channel (116, 216, 316, 416, 516) extending between an inlet (118, 218) and an outlet (120, 220) that opens to the combustion chamber (108, 208). The central channel (116, 216, 316, 416, 516) includes a compressed air flow passage (122, 222) and a mixer (124, 224) for combining fuel and air. A vane (142, 242, 342, 442, 542) extends from the body (112, 212, 312, 412, 512) and includes an outer wall (144, 244) extending radially between a root (146, 246, 346, 446, 546) and a tip (148, 248, 348, 448, 548) in a spanwise direction (Sd), and axially between a leading edge (150, 250) and a trailing edge (152, 252) in a chordwise direction (Cd). The outer wall (144, 244) includes a plurality of lobes (156, 256, 356, 456, 556) defining a waveform (174, 274, 374, 474, 574) that increases in amplitude (178, 278) in the chordwise direction (Cd) to promote enhanced mixing and uniform combustion.

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete