Flugzeugmotorgondel

Details

Veröffentlichungs-Nr.

EP3112269

Aktenzeichen

EP16172656

Anmeldetag

2. Juni 2016

Veröffentlichung

9. Januar 2019

Erteilung

9. Januar 2019

Rechtsraum

EP

IPC

B64D33/02B64D29/00F02C7/045

Abstract

A gas turbine engine nacelle (40) comprising an intake liner (150). The liner (150) comprises a plurality of cells (52). Each cell (52) comprises an open radially inner end (54) in fluid communication with an interior side (42) of the nacelle (40), and an open radially outer end (56) in fluid communication with an exterior side (44) of the nacelle (40). Each open end (54, 56) of each cell (52) defines a respective cross sectional area. The intake liner (150) further comprises radially inner and outer facing sheets (58, 44) overlying a respective radially inner and outer open ends (54, 56) of the respective cell (52). Each facing sheet (58, 44) defines at least one aperture (60, 61) overlying at least one cell (52), an overlying portion of the respective aperture (60, 61) having a smaller cross sectional area than the respective open end of the respective cell.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete