Importance

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Abstract

The proposed invention is an airflow straightening assembly for a turbine engine comprising: —a cylindrical platform (15) centered on an axis (X-X), —at least one straightener blade (20) extending from the platform, —a structural unit (30) extending radially relative to the axis, and —a mechanical member (40) protruding from the platform (15), said mechanical member (40) being one of the group comprising: —a radial shaft, —an angle transmission box of a radial shaft, —an electric, hydraulic or pneumatic connection element, —an intermediate gear driving a radial shaft, the straightening assembly further comprising a fairing (50) or the protruding mechanical member, the fairing having a three-dimensional surface defined by: —at least one upstream end point (Ai, A_e) located axially upstream from the mechanical member (40) relative to the direction of air flow in the turbine engine, and —at least one downstream end point (Ci, C_e) located axially downstream from the mechanical member, the three-dimensional surface being tangential to the platform at the upstream and downstream end points (Ai, A_e, Ci, C_e), and having a larger cross-section measured along an axis (Y-Y) orthogonal to the first, and in which the three-dimensional surface is further defined by two lateral end point (B_i, B_e) corresponding to the ends of said larger cross-section respectively on the pressure side and suction side of the structural arm (30), the axial positions or said points being separated by at most 0.1 C_QGV—in which C_OGV is the chord of the straightener blade (20).

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First Claim