Brennkammer mit Segmentierter Wand

Details

Veröffentlichungs-Nr.

EP3236155

Aktenzeichen

EP17162512

Anmeldetag

23. März 2017

Veröffentlichung

6. Mai 2020

Erteilung

6. Mai 2020

Rechtsraum

EP

IPC

F23R3/00F23R3/50F23R3/60

Abstract

A gas turbine engine combustion chamber (15) comprises upstream and downstream ring structures (43, 54, 56) and a plurality of circumferentially arranged combustion chamber segments (58, 60). Each segment (58, 60) extends the full length of the combustion chamber (15) and each segment (58, 60) is secured to the upstream ring structure (43) and is mounted on the downstream ring structure (54, 56). A frame structure (75) at the downstream end of each segment (58, 60) has a plurality of circumferentially spaced radially extending holes (86). The downstream end of each segment (58, 60) has an axially upstream extending groove (88) and the downstream ring structure (54, 56) has an annular axially upstream extending hook (90) which locates in the groove (88) of each segment (58, 60). A portion of the downstream ring structure (54, 56) abuts the frame structure (75) of each segment (58, 60). The downstream ring structure (54, 56) has a plurality of holes (94) extending radially through the portion (92) abutting the frame structure (75) and segment (58, 60) is removably secured to the downstream ring structure (54, 56) by a plurality of fasteners (96) locating in the holes (86, 94) in the segments (58,60) and the downstream ring structure (54,56).

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete