Snecma

Alexandre Forestier

Roger A Rosa

Alain A Pluquet

Pierre M Teysseyre

Mansour Tabet

Alain M Lardellier

Raymond J Joubert

The rim of the rotor disk has teeth formed by axial grooves. The grooves accept the bases of the blades, which are radially locked by wedges placed between the root and the bottom of the groove. The blade base is extended by a shank bearing the platform and the blade. The locking device comprises locks provided on at least part of the sides of the spindle, and housing provided in the teeth and shaped in such a way that they interact with the locks when the wedge is placed between the blade base and the bottom of the groove. According to one embodiment, the locks are formed by the portions which extend from a locking part lodged in a notch of the blade base and of the shank.

Device for locking a turbine rotor blade

Apparatus for making a soundproof lining for a gas pipe, in particular for a turbojet fan jet, of the type including a multiplicity of thin, perforated panels juxtaposed by tiling, as well as an intermediate layer between the wall of the pipe and each of said panels to delimit with said perforated panel a multiplicity of resonant acoustical cavities in which the acoustical vents consist of the ports in the perforated panel. According to the invention, in order to make the tubular vents, each perforated panel has a short, tubular sleeve at right angles to each port and located on its face opposite the wall of the pipe.

Apparatus for molding and perforating a FRP sheet

A damping device for the turbojet engine fan blades which includes a wedge placed between the platforms of the blades, the shanks of the blades, and the disc. The wedge consists of a hollow, bellows-shaped body fitted with an axial stop member, the body being inflated after mounting so that it takes up all the space between the platforms of the blades, the blade shanks and the teeth of the disc. The invention is used for damping device of turbojet engine blades.

Damping device for turbojet engine fan blades

A device is disclosed for vibration damping, especially in fans of turbojets. The root engaged inside a rotor support disk slot is kept against the upper walls of the slot under the exertion of pressure acting on the lower side of the blade root due to the present device. The device includes a torsion bar which is placed beneath the root of the blade and of which one of the ends is attached to a cam resting against the base of the root of the blade. The other end of the torsion bar is provided with a cam inserted on said bar against the base of the root of the blade under stress that was previously conveyed to the bar.

Vibration damping device, especially for a blade of a turbojet engine

The outside retainer of the bearing is mounted at the end of a relatively elastic squirrel cage attached by a flange to a rigid support; the radial movements of the retainer are limited by an annular stop. In accordance with the invention, parts are arranged so as also to serve as stops for the circumferential and axial movements of the bearing.

Turbine bearing

Soundproof lining for a gas pipe, in particular for a turbojet fan jet, of the type including a multiplicity of thin, perforated panels juxtaposed by tiling, as well as an intermediate layer between the wall of the pipe and each of said panels to delimit with said perforated panel a multiplicity of resonant acoustical cavities in which the acoustical vents consist of the ports in the perforated panel. According to the invention, in order to make the tubular vents, each perforated panel has a short, tubular sleeve at right angles to each port and located on its face opposite the wall of the pipe.

Growing community of inventors

Vaux Le Penil, France

Alexandre Forestier