Gasturbinentriebwerk mit Turbinenkomponenten aus Keramikmatrixverbundstoff

Details

Veröffentlichungs-Nr.

EP3608509

Aktenzeichen

EP19189307

Anmeldetag

31. Juli 2019

Veröffentlichung

17. April 2024

Erteilung

17. April 2024

Rechtsraum

EP

IPC

F01D5/28F01D15/12F01D25/12F02C3/107F02K3/06

Abstract

A gas turbine engine (10) for an aircraft comprising an engine core (11) with a turbine (17, 19), a combustor (16), and a compressor (14, 15), the turbine comprising a first turbine (19) and a second turbine (17) and the compressor comprising a first compressor (14) and a second compressor (15), a first core shaft (26) connecting the first turbine to the first compressor, a second core shaft (27) connecting the second turbine to the second compressor, the second turbine, second compressor, and second core shaft being arranged to rotate at a higher rotational speed than the first core shaft, the gas turbine engine further comprising a bypass duct radially outside the engine core, a fan (23) comprising a plurality of fan blades and a gearbox (30) that receives an input from the first core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the first core shaft, wherein part of the flow (C) that enters the engine core bypasses the combustor and is used as turbine cooling flow to cool the turbine, the fan diameter is in the range of from 225cm to 400cm, and at cruise conditions, the cooling to bypass flow efficiency ratio is no greater than 0.02.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete