A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
申请公布号
WO2015163949(A2)
申请公布日期
2015.10.29
申请号
WO2015US10010
申请日期
2015.01.02
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
THORNTON, LANE;DEVORE, MATTHEW A.;MONGILLO, DOMINIC J.;GAUTSCHI, STEVEN BRUCE