Abstract: A turbojet engine, having a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes extending in the secondary duct downstream of a fan, at least one servo extending in the secondary duct downstream of the guide vanes and housed in a profiled casing, and at least one air sampling scoop located in the region of the casing and equipped with a control valve. Where at least one guide vane located in the vicinity of the casing has a variable geometry zone, the geometry of which can be adjusted during operation.

Abstract: A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

Abstract: A front part of an aircraft turbomachine of the bypass type including a single fan, a gas generator positioned downstream of the fan, a reducer interposed between the gas generator and the fan, a flow splitter and a structure with structural outlet guide vanes. The vanes each have a root arranged upstream of the flow splitter and the reducer is also arranged at least half upstream of the flow splitter.

Abstract: A variable-orientation stator vane of a turbine engine, comprising a wall that extends between a leading edge and a trailing edge forming a chord line. The chord line increases from a root end towards a tip end of said vane. This vane is fitted pivotably in a turbine engine casing so as to divert a flow of cold air circulating in an annular duct thereof.

Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P?) perpendicular to the axis of elongation and intersecting the platform, the dist

Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P?) perpendicular to the axis of elongation and intersecting the platform, the dist

Abstract: A front part of an aircraft turbomachine of the bypass type including a single fan, a gas generator positioned downstream of the fan, a reducer interposed between the gas generator and the fan, a flow splitter and a structure with structural outlet guide vanes. The vanes each have a root arranged upstream of the flow splitter and the reducer is also arranged at least half upstream of the flow splitter.

Abstract: A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

Abstract: A variable-orientation stator vane of a turbine engine, comprising a wall that extends between a leading edge and a trailing edge forming a chord line. The chord line increases from a root end towards a tip end of said vane. This vane is fitted pivotably in a turbine engine casing so as to divert a flow of cold air circulating in an annular duct thereof.