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 has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).
申请公布号
WO2015126824(A1)
申请公布日期
2015.08.27
申请号
WO2015US16154
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.