A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.
申请公布号
WO2015175051(A3)
申请公布日期
2016.01.14
申请号
WO2015US16018
申请日期
2015.02.16
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