公开(公告)号：EP3108111A4

公开(公告)日：2017-03-01

申请号：EP15752124

申请日：2015-02-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  BRILLIANT LISA I ,  STRACCIA JOSEPH C ,  BALAMUCKI STANLEY J ,  STEPHENS MARK A ,  HUDON KATE

IPC: F01D5/14 ,  F04D29/38

CPC classification number: F04D29/324 ,  F01D5/141 ,  F01D17/162 ,  F02C3/04 ,  F02C7/36 ,  F04D19/02 ,  F04D29/325 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2260/4031 ,  Y02T50/672 ,  Y02T50/673

Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% span.

Abstract translation: 具有齿轮结构的涡轮发动机的压缩机翼型包括压力面和吸力面，所述压力面和吸力面沿从0％跨度位置到100％跨度位置的径向方向延伸。 翼型具有前缘二面角与由前缘二面角包括10°或更小的曲线定义的跨度位置之间的关系，所述前缘二面角从0％跨度到60％跨度变化。