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Details

Veröffentlichungs-Nr.

EP3255264

Aktenzeichen

EP17171639

Anmeldetag

18. Mai 2017

Veröffentlichung

25. Dezember 2019

Erteilung

25. Dezember 2019

Rechtsraum

EP

IPC

F02C6/08F02C9/18F04D27/02

Abstract

The present invention provides a multi-stage compressor for a gas turbine engine. The compressor has: a first outer casing, a second outer casing radially outward of the first outer casing, and a first bleed plenum one or more second bleed plenums located between the first and second outer casings and arranged to receive, in use, bleed flows of compressed air from respective stages of the compressor and to send the bleed flows to respective ports in the second outer casing. The first bleed plenum overlaps the, or each, second bleed plenum such that the, or each, second bleed plenum fluidly communicates with its port via a respective duct which, on extending between an off-take from the second bleed plenum to the port, passes through the first bleed plenum. The, or each, duct is configured to accommodate relative movement between the first and second outer casings.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete