An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending 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 has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.
申请公布号
WO2015126837(A1)
申请公布日期
2015.08.27
申请号
WO2015US16187
申请日期
2015.02.17
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.