An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE-Xd)/(Xd-XTE) at 100% span position is about 1 and (XLE-Xd)/(Xd-XTE) at 90% span position is about 1.
申请公布号
WO2015126451(A1)
申请公布日期
2015.08.27
申请号
WO2014US52325
申请日期
2014.08.22
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
GALLAGHER, EDWARD J.;MONZON, BYRON R.;LIU, LING;LI, LINDA S.;WHITLOW, DARRYL;FORD, BARRY M.