A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.
申请公布号
WO2014011246(A3)
申请公布日期
2014.03.27
申请号
WO2013US33241
申请日期
2013.03.21
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
SUCIU, GABRIEL, L.;MERRY, BRIAN, D.;BRILLIANT, LISA, I.