Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.