Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Josette Benoist

Jean-Claude Christian Taillant

Paul Martyez

Gerard M Mandet

Pierre A Glowacki

Jerome E Jolu

Guillaume Henri Chaput

Guy Pierre Queneherve

Didier Desire Pasquiet

A gas mixer (8) which placed in a flow of gases upstream of a ring (3) that is to be heated or cooled, the gas mixer (8) including a succession of mbers (12, 14, 15) having communication or outlet orifices (16, 17, 18) in large numbers in order to render uniform a rate and temperature of the gas flow. The gas mixer (8) is applicable to gas turbine engines.

Device for blowing gases for regulating clearances in a gas turbine

A nozzle of a turbine stator of a turbine engine, wherein at least two of the vanes are fixed to each inner platform and to opposite each outer platform, and a maintaining unit is configured to maintain each sector with respect to a case of the turbine stator and to connect sectors together and has a rotational maintaining element, a radial maintaining element and an axial maintaining element. The radial maintaining element is flexible so as to permit a radial expansion of each sector and is constituted by an elastic joint fixed to the case so as to surround the sectors.

Sectored, one-piece nozzle of a turbine engine turbine stator

A layout for connecting two platforms of a turbomachine which support blades. A common clearance between the blades is occupied by a seal which includes a core placed in channels under the surface of the platforms and strips which close off the clearance and which are embedded in a layer of easily eroded material. Not only do the core and the strips close off the clearances, but the seal can be designed with a sufficient stiffness to oppose any excessive movement of the platforms. The strips can also be used alone without the seal.

Layout for connecting two angular sectors of a turbomachine, and seal

While remaining in one piece and unsectored, a nozzle permits a slight radial expansion of an assembly. The nozzle is formed by an inner platform mounted in a sliding manner with respect to a stator and an outer platform mounted in a free manner with respect to the case of the stator. Rods are fitted in a pivoting manner so as to radially guide and axially block upper parts of vanes, which are mounted in a sliding manner in the inner platform. The assembly is advantageously completed by gaskets. The nozzle can be used in high pressure turbines of turbojets.

Unsectored, one piece distributor of a turbojet turbine stator

The rim of a turbine disc is provided with a circular collar upon which is ngaged the heel of an annular flange having a U-shaped cross section with unequal sectors, i.e., a principal piece forming a circlip and a smaller piece forming a key which completes the flange following the installation of the circlip; the key is retained in its position by cuts of the ends of said key.

Rotor flanges of turbine engines

A device to secure and insure the tightness of vanes of a turbine is an alar plate which carries on the side toward its external edge a plurality of studs and toward its internal edge a plurality of hangers. The disk of the rotor has on its lower edge a series of teeth or indentations, the top of the teeth having a configuration to cooperate with the inner surface of the hangers. The vanes have on their rims a plurality of grooves. Two adjacent vanes form a groove into which the studs enter when the hangers cooperate with the teeth. The studs are borne by tongues cut radially into the annular plate.

Growing community of inventors

Le Mee S/Seine, France

Josette Benoist