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
EP3108103(A4)
申请公布日期
2017.02.22
申请号
EP20140883154
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.