CPC F01D 9/042 (2013.01) [F01D 9/041 (2013.01); F01D 25/28 (2013.01)] | 16 Claims |
1. An annular intermediate casing for a turbomachine of longitudinal axis X, through which an aerodynamic air flow is intended to circulate at least in part, the intermediate casing comprising:
an annular radially inner shroud,
an annular radially outer shroud,
a stator vane extending substantially along a radial axis Z, the stator vane comprising a blade with a leading edge and a trailing edge, and
an aerodynamic member which is formed of a structural arm extending radially at least in part between the radially inner shroud and the radially outer shroud,
wherein the stator vane extends between a first platform and a second platform and the aerodynamic member comprises a leading edge which is aligned with the leading edge of the stator vane in a plane perpendicular to the longitudinal axis X, the leading edge of the aerodynamic member being borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic air flow, the profiled portion and the structural arm being monobloc,
wherein the aerodynamic member comprises a distal edge which is located downstream the trailing edge of the stator vane, and
wherein the aerodynamic member is monobloc with the radially inner shroud and the radially outer shroud,
wherein the intermediate casing comprising said aerodynamic member and at least a second aerodynamic member, said aerodynamic member and said at least second aerodynamic member are spaced along the circumferential direction about the longitudinal axis X,
wherein the intermediate casing comprising a straightening assembly which is added on and disposed between said aerodynamic member and said at least second aerodynamic member, the straightening assembly comprising the first platform, the second platform and a plurality of said stator vane being distributed regularly along the circumferential direction, each leading edge of the plurality of stator vanes is aligned with the leading edge of the aerodynamic member in the plane perpendicular to the longitudinal axis X.
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