Kompressorschaufelelement

Details

Veröffentlichungs-Nr.

EP3404212

Aktenzeichen

EP18167527

Anmeldetag

16. April 2018

Veröffentlichung

4. März 2020

Erteilung

4. März 2020

Rechtsraum

EP

IPC

F01D5/14

Abstract

An aerofoil member for a compressor of a gas turbine engine is provided. In use the aerofoil member extends between radially inner and radially outer endwalls which define a gas annulus of the compressor. The aerofoil member has a leading edge, a trailing edge, a pressure surface and a suction surface such that successive cross-sections through the aerofoil member transverse to the radial direction provide respective aerofoil sections. The external shape of the aerofoil member is defined by the stacking of the aerofoil sections on a stacking axis which passes through a reference point common to each aerofoil section. The aerofoil member has lean produced by the projection of the stacking axis onto a plane normal to the engine axis intersecting a first one of the endwalls at an angle of from 5° to 25° to the circumferential direction direction such that the pressure surface faces the first endwall. With increasing distance along the stacking axis from the first endwall, the stacking axis experiences a turning point such that the pressure surface has a convex shape adjacent the first endwall.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete