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
EP3108115(A2)
申请公布日期
2016.12.28
申请号
EP20150792194
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