A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
申请公布号
WO2014092833(A2)
申请公布日期
2014.06.19
申请号
WO2013US61123
申请日期
2013.09.23
申请人
UNITED TECHNOLOGIES CORPORATION;CHUANG, SUE-LI;DONG, YUAN;HINGORANI, SANJAY S.;PRASAD, DILIP