公开(公告)号：US20180335044A1

公开(公告)日：2018-11-22

申请号：US15978556

申请日：2018-05-14

申请人： ROLLS-ROYCE plc

发明人： James V. TAYLOR ,  Robert J. MILLER

IPC分类号： F04D29/32 ,  F01D5/14

摘要： An aerofoil member that extends between radially inner and radially outer endwalls which define a gas annulus of the compressor. 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.

公开(公告)号：US20180298912A1

公开(公告)日：2018-10-18

申请号：US15634244

申请日：2017-06-27

申请人： ROLLS-ROYCE plc

发明人： Christopher R. HALL ,  Anastasios KOVANIS ,  Anthony M. DICKENS ,  James V. TAYLOR

IPC分类号： F04D29/32 ,  F04D29/54 ,  F04D29/38

摘要： This disclosure concerns aerofoils for an axial flow compressor. The compressor has an array of aerofoils angularly spaced about its axis of rotation. The aerofoils have leading and trailing edges extending in a direction spanning a flow region defined between a radially inner rotor component and a radially outer casing. Each aerofoil has opposing pressure and suction surfaces extending between the leading and trailing edges and terminating at a free end of the aerofoil. Each aerofoil leans towards the pressure surface by an angle of between 10° and 80° in the vicinity of the aerofoil tip. The aggressive negative lean towards the tip may help reduce over-tip leakage flow in use.

公开(公告)号：US20170292528A1

公开(公告)日：2017-10-12

申请号：US15459878

申请日：2017-03-15

申请人： ROLLS-ROYCE plc

发明人： William J. BROWN ,  Christopher R P. HALL ,  Anthony M J. DICKENS ,  James V. TAYLOR

IPC分类号： F04D29/32 ,  F01D5/14

CPC分类号： F04D29/324 ,  F01D5/141 ,  F05D2220/32 ,  F05D2240/301 ,  F05D2240/304 ,  F05D2250/70

摘要： A blade for an axial flow machine having a pressure surface, suction surface and trailing edge. The blade has a cross-sectional aerofoil profile including: a region of maximum curvature corresponding to the trailing edge of the blade and defining a trailing edge radius of curvature r; a trailing edge region extending from the trailing edge and having a chordwise extent equal to curvature r′s trailing edge radius; a taper region adjacent the trailing edge region, the taper region having a chordwise extent greater than the curvature r′s trailing edge radius and no more than 15% of the blade's chord; a body region adjacent the taper region; a pressure surface boundary corresponding to the blade's pressure surface; and a suction surface boundary corresponding to the blade's suction surface. A thickness between the pressure and suction surface boundaries reduces within the taper region towards the trailing edge by at least 50%.