Drallkörper für Verbrenner eines Gasturbinenmotors

Details

Veröffentlichungs-Nr.

EP3431876

Aktenzeichen

EP18185063

Anmeldetag

23. Juli 2018

Veröffentlichung

20. Oktober 2021

Erteilung

20. Oktober 2021

Rechtsraum

EP

IPC

F23R3/14F23R3/28

Abstract

A combustor (50) for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber (62), and a fuel injector (70) extending at least partially into the combustion chamber, and configured to deliver a flow of fuel (76) and a flow of combustion air (78) into the combustion chamber for combustion. The fuel injector includes a swirler (74) with a swirler exit (94) having a circumferential width (96) along a circumferential axis greater than a radial width (98) along a radial axis. A swirler for a gas turbine engine includes a swirler entrance (92) and a swirler exit (94). The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete