Umschaltbares Ablassventil für einen Gasturbinenmotor

Details

Veröffentlichungs-Nr.

EP3462008

Aktenzeichen

EP18198299

Anmeldetag

2. Oktober 2018

Veröffentlichung

25. November 2020

Erteilung

25. November 2020

Rechtsraum

EP

IPC

F02C9/18F04D27/02F01D17/10

Abstract

A gas turbine engine (20) includes a compressor section (24) having multiple stages, a combustor section (26) fluidly connected to the compressor section (24), a turbine section (28) fluidly connected to the combustor section (26), and a bleed structure (200) radially outward of the stages. The bleed structure (200) includes a body structure (214) having a first set of openings (216) radially outward of a first stage and a second set of openings (218) radially outward of a second stage. The bleed structure (200) further includes a circumferential sleeve (214) configured to cover the first set of openings (216) in a first position and configured to cover the second set of openings (218) in a second position. An actuator (230) is coupled to the circumferential sleeve (214) and is configured to articulate the circumferential sleeve (214) between the first and second positions.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete