Triebwerksgondel für ein Hecktriebwerk eines Luftfahrzeugs

Details

Veröffentlichungs-Nr.

EP3351475

Aktenzeichen

EP18151056

Anmeldetag

10. Januar 2018

Veröffentlichung

13. Dezember 2023

Erteilung

13. Dezember 2023

Rechtsraum

EP

IPC

B64D27/20B64C7/02B64D33/02B64D27/14

Abstract

An aircraft (10) is provided including a fuselage (12) extending between a forward end (16) and an aft end (18). An aft engine is mounted to the fuselage (12) at the aft end of the fuselage (18). The aft engine includes a nacelle (306) having a forward section. An airflow duct (344) is also provided extending at least partially through the nacelle (306) and including an opening on the forward section of the nacelle (330). The opening is configured for providing an airflow to, or receiving an airflow from, the forward section of the nacelle (306) to increase an amount of, e.g., boundary layer airflow received within the aft engine during operation of the aircraft (10), to guide the flow of boundary layer airflow into the engine more smoothly, or to reduce a distortion on the engine.

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete