Abstract: A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.

Abstract: A hub of an intermediate casing for a dual-flow turbine engine includes a discharge flow duct extending between an inner shroud and an outer shroud of the hub, the discharge flow duct leading into the secondary flow space through an outlet opening formed in the outer shroud, the outlet opening included in a discharge plane substantially tangential to the outer shroud; and discharge fins including an upstream fin and a downstream fin. An upstream acute angle between the discharge plane and the skeleton line of the upstream fin is smaller than a downstream acute angle between the discharge plane and the skeleton line of the downstream fin.

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, Ae) 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, Ce) located axially downstream from the mechanical member, the three-dimensional surface

Abstract: The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line (24), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm (30) comprises: an upstream end (31) having a guide vane profile (21) and comprising a leading edge (32) aligned with that of the vane; and a shoulder (35) located on the lower surface of the arm, defining a neck in the channel. The assembly is characterized in that the area (Aneck) of the section of the channel at the neck is between 0.7 and 0.9 times the area (Ainlet) of the section of the channel at the leading edges.

Abstract: The proposed invention is an air-flow straightening assembly for a turbine engine comprising:—a cylindrical platform (15) centred on an axis (X-X),—at least one straightener blade (20) extending from the platform,—a structural arm (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) of the protruding mechanical member, the fairing having a three-dimensional surface defined by:—at least one upstream end pont (Ai, Ae) 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, Ce) located axially downstream from the mechanical member, the three-dimensional surface being tange

Abstract: A hub of an intermediate casing for a dual-flow turbine engine includes a discharge flow duct extending between an inner shroud and an outer shroud of the hub, the discharge flow duct leading into the secondary flow space through an outlet opening formed in the outer shroud, the outlet opening included in a discharge plane substantially tangential to the outer shroud; and discharge fins including an upstream fin and a downstream fin. An upstream acute angle between the discharge plane and the skeleton line of the upstream fin is smaller than a downstream acute angle between the discharge plane and the skeleton line of the downstream fin.

Abstract: A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.

Abstract: The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line (24), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm (30) comprises: an upstream end (31) having a guide vane profile (21) and comprising a leading edge (32) aligned with that of the vane; and a shoulder (35) located on the lower surface of the arm, defining a neck in the channel. The assembly is characterised in that the area (Aneck) of the section of the channel at the neck is between 0.7 and 0.9 times the area (Ainlet) of the section of the channel at the leading edges.

Abstract: The bypass turbomachine comprises, between a primary flowpath (2) and a secondary flowpath (3), a structural intermediate casing (14). A bleed passage (29) allows the diversion of a portion of the gas stream toward the secondary flowpath (3), downstream of support arms (18) situated at the periphery of the intermediate casing. A bleed opening (28) emerges upstream of the support arms (18). A slide valve (22) slides between three positions, namely a closed position in which the slide valve (22) completely blocks off the bleed passage and opening, an intermediate position in which the bleed opening (28) emerging upstream of the support arms (18) is blocked off, while the bleed passage (29) for diverting a portion of the gas stream downstream of the support arms (18) is open, and an open position in which the bleed opening (28) emerging upstream of the support arms (18) and the bleed passage (29) emerging downstream of the support arms are both open.