Safran S.A. is a French multinational aircraft and rocket-engine, aerospace-component, and security company. It was formed by a merger between the aircraft and rocket engine manufacturer and aerospace component manufacturer group SNECMA and the security company SAGEM in 2005. Its headquarters are located in Paris. Wikipedia.
Safran and Snecma | Date: 2014-04-28
A tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, the tooling including a blade support for receiving a blade while leaving surfaces of the leading edge of the blade disengaged; and a leading edge reinforcement support on which the blade support is designed to be mounted, and including two lateral wedges between which the metal reinforcement for the leading edge of the blade is positioned, the wedges being suitable for being capable of moving towards each other and apart from each other and each of them being provided with a suction grid for gripping the metal reinforcement, the leading edge reinforcement support further including heater elements for polymerizing an adhesive film applied on the leading edge surfaces of the blade.
Snecma and Safran | Date: 2015-09-24
A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.
Snecma and Safran | Date: 2014-02-04
A mold comprises a first shell and a second shell that are suitable, in the closed position, for imparting a shape to a part that is to be molded in the mold, a main axis A being perpendicular to the main plane in which the first shell and the second shell extend. The mold further comprises at least one slide that is situated between the first shell and the second shell and that is in contact with the first shell and the second shell when the mold is in the closed position, and that is to come into contact with the molded part, the or each slide presenting a first face that constitutes its interface with the first shell, the first face presenting a primary direction along which the slide is suitable for sliding along the first face when the mold is in the open position.
Safran | Date: 2014-02-26
Snecma and Safran | Date: 2014-10-10
The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.