Abstract: A method for coating a turbomachine guide vane including a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, the method including completely covering one of the faces of the vane with a polymer coating of thickness (e1) provided with grooves, removing the grooves from a part of the polymer coating in such a way that the polymer coating includes a grooved zone and a non-grooved zone, coating the non-grooved zone with a coat of paint of thickness (e3) such that the thickness of the coat of paint superimposed on the non-grooved zone is substantially equal to the thickness (e1) of the grooved zone.

Abstract: A turbine engine extends along an axis (X) and includes a flow path of a primary flow (F1) that has a compressor, a combustion chamber, and a turbine. The turbine engine further includes an outflow region of a secondary flow (F2) that surrounds the primary path, a blower or a propeller located upstream of the primary path and the outflow region of the secondary flow (F2), at least one arm extending radially through the primary path, and at least one fluid circulation pipe extending inside the arm. The arm includes an inlet for air from the primary path so as to cool the fluid circulating in the pipe.

Abstract: A composite vane for a turbomachine, in particular an aircraft turbomachine, this vane including an aerofoil having a pressure side and a suction side connected together by a leading edge and by a trailing edge, the aerofoil been formed from a fibrous preform obtained by weaving fibres in three dimensions, which is embedded in a polymer matrix, the vane further including a first metal shield extending over and along the leading edge of the aerofoil, the vane further including at least one cover element extending over and along the trailing edge of the aerofoil.

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: Turbines for an aircraft include a supply device of compressed air configured to supply compressed air to the aircraft, a cooling system of the compressed air supplied to the aircraft, having a scoop configured to collect cooling air in a flow duct of a secondary flow, and a management system configured to be supplied with the cooling air collected from the flow duct and configured to control radial clearances between a turbine casing and turbine rotor vanes tips. The management system is supplied with cooling air by the scoop of the cooling system.

Abstract: A method for coating a turbomachine guide vane including a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, the method including completely covering one of the faces of the vane with a polymer coating of thickness (e1) provided with grooves, removing the grooves from a part of the polymer coating in such a way that the polymer coating includes a grooved zone and a non-grooved zone, coating the non-grooved zone with a coat of paint of thickness (e3) such that the thickness of the coat of paint superimposed on the non-grooved zone is substantially equal to the thickness (e1) of the grooved zone.

Abstract: Turbines for an aircraft include a supply device of compressed air configured to supply compressed air to the aircraft, a cooling system of the compressed air supplied to the aircraft, having a scoop configured to collect cooling air in a flow duct of a secondary flow, and a management system configured to be supplied with the cooling air collected from the flow duct and configured to control radial clearances between a turbine casing and turbine rotor vanes tips. The management system is supplied with cooling air by the scoop of the cooling system.