Brennstoffdüse für ein Flugzeugtriebwerk

Details

Veröffentlichungs-Nr.

EP4524471

Aktenzeichen

EP24200374

Anmeldetag

13. September 2024

Veröffentlichung

19. März 2025

Rechtsraum

EP

IPC

F23R3/28F23D11/38

Abstract

A fuel nozzle (70) for a gas turbine engine (20) includes a first fuel nozzle body (72) and a second fuel nozzle body (74). The first fuel nozzle body (72) and the second fuel nozzle body (74) form a fuel passage (78). The fuel passage (78) includes a fuel accumulation chamber (80), an upstream fuel passage (112), a downstream fuel passage (114), and a plurality of tangential feed holes (116). The upstream fuel passage (112) extends along an upstream fuel passage centerline (118) to a terminal end (120) of the upstream fuel passage (112). The terminal end (120) is spaced from the accumulation chamber (80). The downstream fuel passage (114) extends from a passage inlet (126) along a downstream fuel passage centerline (124). The passage inlet (126) is disposed at the accumulation chamber (80). The plurality of tangential feed holes (116) are formed by the first fuel nozzle body (72). Each tangential feed hole (116) of the plurality of tangential feed holes (116) extends between and to a hole inlet (128) and a hole outlet (130). The hole inlet (128) is disposed at the upstream fuel passage (112) upstream of the terminal end (120). The hole outlet (130) is disposed at the accumulation chamber (80).

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada

Fachgebiete