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Pantin, France

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.


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.


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.


Patent
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.


Grant
Agency: Cordis | Branch: H2020 | Program: RIA | Phase: MG-1.1-2014 | Award Amount: 3.05M | Year: 2015

The ability to simulate aerodynamic flows using CFD methods has progressed rapidly over the last decades and has given rise to a change in design processes in aeronautics already. But more improvement is necessary to overcome the (still) existing lack in confidence in CFD usage, based on turbulence modelling. The TILDA project will offer methods and approaches combining advanced and efficient high-order numerical schemes (HOMs) with innovative approaches for LES and DNS in order to resolve all relevant flow features on tens of thousands of processors in order to get close to a full LES/DNS solution for 1billion degrees-of-freedom (DOF) not exceeding turn-around times of a few days. The TILDA project will provide both an improved physical knowledge and more accurate predictions of non-linear, unsteady flows near borders of the flight envelope - which will directly contribute to an enhanced reliability. The main highly innovative objectives, targeting at industrial needs read: Advance methods to accelerate HOM for unsteady turbulence simulations on unstructured grids. Advance methods to accelerate LES and future DNS methodology by multilevel, adaptive, fractal and similar approaches on unstructured grids. Use existent large scale HPC networks to enable industrial applications of LES/DNS close(r) to daily practice. Compact high-order methods offer a very high ratio between computational work per DOF combined to a low data dependency stencil, making these methods extremely well adapted for shared-memory parallel processors, and allow for efficient redistribution over an increased number of processors. Provide grid generation methods for HOM on unstructured grids with emphasis on valid curvilinear meshes for complex geometries, and accounting for mesh and solution quality. Provide suitable I/O and interactive co- and post-processing tools for large datasets. Demonstration of multi-disciplinary capabilities of HOM for LES in the area of aero-acoustics.


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