A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge (110, 200, 202), an outer diameter edge (208), a trailing edge (102) and a leading edge (100). The leading edge (100) has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge (100). The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.
申请公布号
EP2995771(A1)
申请公布日期
2016.03.16
申请号
EP20150183680
申请日期
2015.09.03
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
VAN NESS, DANIEL K.;STEPHENS, MARK A.;GALLAGHER, EDWARD J.;STRACCIA, JOSEPH C.;KUMAR, VIKRAM A.