Gelappte Gasentladungsverkleidung für ein Bläsertriebwerk

Details

Veröffentlichungs-Nr.

EP3441593

Aktenzeichen

EP18188087

Anmeldetag

8. August 2018

Veröffentlichung

13. Juli 2022

Erteilung

13. Juli 2022

Rechtsraum

EP

IPC

F02C7/14

Abstract

A gas turbine engine (10) has an engine core (24) including a primary flowpath (38). A first bypass duct (120) is positioned radially outward of the engine core (24). A gas discharge (52) protrudes radially into the first bypass duct (120). The gas discharge (52) includes a fairing (112) defining a lobed outlet (114). The lobed outlet (114) includes a plurality of axially aligned peaks (116) and axially aligned valleys (118). Each of the axially aligned valleys (118) is configured to prevent a fluid passing through the valley (118) from traveling radially inward immediately downstream of the fairing (112) creating regions of relatively cool, mixed, and hot airflows.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete