1
Bernard Fraignier, Daniel E Gery: Multi axis force and moments transducer. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, November 5, 1985: US04550617 (94 worldwide citation)

A multi-axis force and moment transducer having a plurality of flexible plates, orthogonally oriented, interconnected between first and second bodies to measure the forces exerted thereon due to relative movement between the bodies. The interconnection between a first element attached to the first b ...


2
Michel J R Nicolas, Bruno R Sebilet: Spread spectrum coding method and apparatus. Societe Nationale d Etudes et de Construction de Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, August 12, 1986: US04606039 (92 worldwide citation)

In a process for coding of radio transmissions by spectrum spreading, a signal is phase modulated by means of a 0-pi modulator controlled by a psuedo random sequence formed by combining in accordance with a logical majority function an odd number of elementary codes constituted by pseudo random bina ...


3
Henri Bizot, Gery Charles J Brasselet, Jean Paul Louis, Georges Narcy: Process and apparatus for laser drilling. S N E C M A, Bacon & Thomas, August 26, 1986: US04608480 (64 worldwide citation)

A process and apparatus are disclosed for accurately drilling and calibrating holes via a pulsed laser beam to form a perforated work piece. The sounds emitted by the melting of the work piece due to its contact with the laser beam are sensed, converted into digital form, compared with a reference v ...


4
Marcel R Soligny: System for attaching two rotating parts made of materials having different expansion coefficients. S N E C M A, Oblon Fisher Spivak McClelland & Maier, June 5, 1984: US04452038 (56 worldwide citation)

A system is disclosed for attaching a cap of composite material to the exhaust housing of a turbojet. The system consists of three triangular rod assemblies arranged between the housing and the cap. The triangular rod assemblies bear at their ends eyelets pivotally connected to brackets attached to ...


5
Henry Naud: Structural cowlings of twin flow turbo jet engines. Societe Nationale d Etude et de Construction de Moteur d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, August 4, 1987: US04683717 (47 worldwide citation)

A twin flow turbo-jet engine which includes an inner structural cowling formed by two lateral shells and which is secured through the intermediary of a securing mechanism such as fluid actuators between a forward flange and a rear flange of the casing of the engine. At least one of the securing devi ...


6
Joel M D Benoit, Bruno J G Dambrine, Laurent J P David, Patrick Fouche, Daniel G Girault, Christophe G R Grosbois, Catherine L F Guet: Gas turbine blade comprising layers of composite material. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, May 3, 1994: US05308228 (47 worldwide citation)

A gas turbine blade includes a central core covered by a plurality of layers of composite material, and optionally also an outer sleeve of woven composite material. A network of transverse seams pass through the layers of composite material, and preferably also the core and the outer sleeve. This co ...


7
Claude C Hallinger: Gas turbine stages of turbojets with devices for the air cooling of the turbine wheel disc. S N E C M A, Oblon Fisher Spivak McClelland & Maier, July 3, 1984: US04457668 (47 worldwide citation)

A turbojet turbine stage having air cooling of the turbine wheel disc is disclosed which has, on the one hand, devices for blowing in a flow of air A in the direction of the upstream surface of the disc (20) intended in particular to flow into the several passages delimited by the periphery (22) of ...


8
Philippe M D Gastebois, Jean Francois R Imbault: Turbine rotor. Societe Nationale d Etude et Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, February 7, 1989: US04802824 (45 worldwide citation)

A turbine rotor has composite ceramic blades each having a bulb-shaped root with planar flanks which define an angle of convergence between them not exceeding ten degrees, and by which the root is held in a dovetail section socket in the periphery of the rotor disc by means of wedge-shaped members a ...


9
Jacques Lesgourgues: Diffusion brazing process for pieces of superalloys. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, September 30, 1986: US04614296 (45 worldwide citation)

A diffusion brazing process for superalloy parts is performed on the one hand by the interposition between the pieces to be joined of a joining layer having a composition close to that of the parts and containing a "fluxing" element, which renders it more readily meltable, and on the other hand, a h ...


10
Alain J E Guibert, Roland R Mestre, Remy P C Ritt: Turbine ring for a gas turbine engine. S N E C M A, Oblon Fisher Spivak McClelland & Maier, July 14, 1987: US04679981 (45 worldwide citation)

A turbine ring has an annular metallic carrier which is mounted within the inside of the turbine casing and within the carrier there is provided a ceramic abradable ring. A cooling air circuit is provided to regulate the temperature of only the annular carrier such that the latter always exerts a ce ...