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 turbomachine stator element extends around a longitudinal axis and includes a first stator vane and a second stator vane circumferentially adjacent to the first stator vane. Each of the first and second stator vanes include a platform and a blade extending radially from the platform. The stator element also comprising at least one inter-platform seal, arranged between the platform of the first stator vane and the platform of the second stator vane. The inter-platform seal has a flat support provided with an upper surface on which there extends a fin.

Abstract: A turbomachine stator element extends around a longitudinal axis and includes a first stator vane and a second stator vane circumferentially adjacent to the first stator vane. Each of the first and second stator vanes include a platform and a blade extending radially from the platform. The stator element also comprising at least one inter-platform seal, arranged between the platform of the first stator vane and the platform of the second stator vane. The inter-platform seal has a flat support provided with an upper surface on which there extends a fin.

Abstract: A disclosed propulsion unit includes a pylon having a blade presenting a chord Cx and a downstream arm having a structural arm. The pylon has a first distance D between a trailing edge of a fan blade and a leading edge of the fan blade, a second distance d between said trailing edge of the blade and a leading edge of the structural arm, and a third distance L between the trailing edge of the blade and a mark located at a maximum thickness of the downstream arm. The pylon is dimensioned according to: a first quotient between D and Cx between 2.2 and 2.6, a second quotient between d and Cx between 1 and 1.2, and a third quotient between L and Cx between 4 and 7.

Abstract: A disclosed propulsion unit includes a pylon having a blade presenting a chord Cx and a downstream arm having a structural arm. The pylon has a first distance D between a trailing edge of a fan blade and a leading edge of the fan blade, a second distance d between said trailing edge of the blade and a leading edge of the structural arm, and a third distance L between the trailing edge of the blade and a mark located at a maximum thickness of the downstream arm. The pylon is dimensioned according to: a first quotient between D and Cx between 2.2 and 2.6, a second quotient between d and Cx between 1 and 1.2, and a third quotient between L and Cx between 4 and 7.