A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a 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.
申请公布号
WO2015126798(A1)
申请公布日期
2015.08.27
申请号
WO2015US16086
申请日期
2015.02.17
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
GALLAGHER, EDWARD J.;BRILLIANT, LISA I.;STRACCIA, JOSEPH C.;BALAMUCKI, STANLEY J.;STEPHENS, MARK A.;HUDON, KATE