61
Jacky Naudet: Stator for directing the inlet of air inside a turbo-engine and method for mounting a vane of said stator. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, July 12, 1994: US05328327 (23 worldwide citation)

A stator for a turbo-engine and a method for mounting the stator serve to improve fixing of the vanes of the stator and resistance of these vanes to impact in the event foreign bodies enter the turbo-engine. The stator includes several vanes radially maintained by their external and internal pivots ...


62
Roland M E Grateau, Alain J E Guibert, Alain J C Henu, Patrick Kapala, Jean Pierre L Mareix, Florence J A Monchois, Michel M Ribault: Turbine casing delimiting an annular gas flow stream divided by radial arms. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, May 17, 1994: US05312227 (23 worldwide citation)

A turbine casing includes circumferential walls delimiting an annular stream for the flow of gases. The radial arms traversing the stream are completed by a channeling part on the downstream side which is bolted to the arms. The walls are formed of butt-joined tiles assembled together and joined to ...


63
Guy R Pachomoff: Rear hanging structure for a turbojet engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, August 24, 1993: US05238206 (23 worldwide citation)

The rear hanging structure by which a turbojet engine is suspended from a mast under the wing of an aircraft includes a brace which is fixed to the mast and to which the engine is attached by at least three suspension links, the brace includes two parts which are fitted one within the other and are ...


64
Guy d Agostino, Andre Dhainaut, Daniel G A Kettler, Henry R Leclerc: Compound seal with pressure equalization aperture. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, July 21, 1987: US04681327 (22 worldwide citation)

A compound seal for affecting a seal on a translating shaft movable within a sleeve to separate high pressure and low pressure zones. The compound seal includes a sealing member and a clamping member disposed in a groove formed in one of the elements. The sealing member defines sealing sides which c ...


65
Ollivier Carletti, Michel E A J Thomas: Turbomachine stator element. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, January 28, 1992: US05083900 (22 worldwide citation)

A turbo-machine stator element comprising an array of fixed blades mounted on a ring has the head of each blade embedded in an aperture in the ring by fixing member comprising first and second interfitting members each consisting of a plate portion and an integral socket portion. The socket of one o ...


66
Andre C F Collot, Bernard P C Sohier, Danilo Varela: Method of manufacturing a hollow blade for a turboshaft engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, October 19, 1993: US05253419 (22 worldwide citation)

A hollow blade for a turboshaft engine, such as a fan rotor blade of large chord, is manufactured by a method in which primary components including two outer metal sheets and at least one intermediate sheet are hot formed so that the components are curved and twisted to a desired shape, diffusion ba ...


67
Stéphane Goujard, Alain Caillaud, Sébastien Bertrand, René Pailler, Jean Luc Charvet: Composite material with ceramic matrix and SiC fiber reinforcement, method for making same. Societe Nationale d&apos Etude et de Construction de Moteurs d&apos Aviation S N E C M A, Weingarten Schurgin Gagnebin & Hayes, September 18, 2001: US06291058 (22 worldwide citation)

The material comprises fiber reinforcement made of fibers that are essentially constituted by silicon carbide, and an interphase layer between the fibers of the reinforcement and the matrix. The reinforcing fibers are long fibers containing less than 5% atomic residual oxygen and they have a modulus ...


68
Robert Kervistin, Philippe J Lefebvre, Alain F Teissier: Automatic control device of a labyrinth seal clearance in a turbo jet engine. Societe Nationale d Etude et de Construction de Moteur d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, May 5, 1987: US04662821 (21 worldwide citation)

Apparatus associated with a labyrinth seal of a turbo machine for automatically maintaining a desired clearance between lip members and a wear seal of the labyrinth seal over a range of operational states of the turbo machine. The wear seal comprises a first part made of honeycomb material and a sec ...


69
Andre M Barbot, Jacques E J Caruel, Marcel R Soligny: Device for cooling and gas turbine rotor. Societe National d Etude et de Construction de Moterus d Aviation S N E C M A, Bacon & Thomas, December 23, 1997: US05700130 (21 worldwide citation)

This device embodies a centrifugal compressor secured to a joint-carrier disk secured to an upstream flange of the rotor disk to be cooled. The recompressed air is ejected through channels near the roots of the blades of the disk.


70
Pierre C Mouton: Turbojet compressor blow off valves with water collecting and discharge means. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, September 3, 1991: US05044153 (21 worldwide citation)

In a turbojet aero-engine of the bypass type in which the compressor includes pivotally mounted blow-off valves for discharging air from the primary air flow path through the compressor to prevent surging, the compressor further includes pivoted means associated with the blow-off valves such that th ...