Gasturbinentriebwerk mit Turbinenkomponenten aus Keramikmatrixverbundstoff

Details

Veröffentlichungs-Nr.

EP3608508

Aktenzeichen

EP19189306

Anmeldetag

31. Juli 2019

Veröffentlichung

25. Dezember 2024

Erteilung

25. Dezember 2024

Rechtsraum

EP

IPC

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

Abstract

A gas turbine engine (10) for an aircraft with an engine core (11) comprising 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 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 the second turbine comprises at least one ceramic matrix composite component and the mass of ceramic matrix composite in the second turbine is in the range of from 2% to 15% of the total mass of the second turbine.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete