21
Anne Marie Arraitz, Eric Stephan Bil, Michel Gerard Paul Hacault, Laurent Philippe Yves Leray, Michel Jean Loubet, Marc Roger Marchi, Jean Manuel Morcillo, Didier Marie Mortgat, Michel Jean Pierre Pernot, Thierry Christian Sanz: Method of reducing the gap between a liner and a turbine distributor of 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 P C, December 26, 2000: US06163959 (34 worldwide citation)

A method of reducing the gap between a liner and a turbine distributor of a turbojet engine. The method allows for the improvement of the seal on the inside of the distributor of the high pressure turbine at the lower platform. The method includes the steps of: applying a protective deposit to the l ...


22
Jean G Bouiller, Francois E G Crozet, Marcel R Soligny: System for cooling a gas turbine by bleeding air from the compressor. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, November 15, 1983: US04415310 (33 worldwide citation)

A system for cooling a gas turbine by bleeding air from the compressor and channeling the air at the center of the engine towards the turbine in order to cool it. The air is bled from the plane of the disc bearing the blades of the compressor, said disc having radial ducts for the flow of the air. T ...


23
Gerard Porcelli: Safety device for a rotating element of a turbine engine. Societe Nationale d etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, March 22, 1983: US04377370 (33 worldwide citation)

A ring is secured to the casing of the compressor or of the turbine of a turbine engine, and has an inner envelope, a first ring of segments of a honeycomb material, a winding of wire sections encased in a polymerizable resin, a second ring of honeycomb segments and an external envelope of a thin ma ...


24
Jean Paul D Alary, Gerard Y G Barbier, Corine G Delahaye, Jacques G W R Havard, Paul Mackovic, Bruno R H Masse, Didier Merville, Francois J P Mirville, Serge R Y Muccioli, Denis J M Sandelis, Ralph M Stelter: Gas turbine engine having an integral guide vane and separator diffuser. Societe Nationale D Etude et de Construction de Moteurs F Aviation S N E C M A, Bacon & Thomas, January 14, 1997: US05592821 (32 worldwide citation)

A separator-diffuser for a gas turbine engine is disclosed wherein the diffuser includes axial walls which function as a guide vane stage for the oxidizer compressor. By incorporating the last, or downstream, guide vane stage into the diffuser structure, the overall axial length and bulk of the gas ...


25
Jean Marc Domergue, Jean Michel Georges, Michel Laxague: Friction element in composite carbon/carbon-silicon carbide material and method for manufacturing same. Societe Nationale d&apos Etude et de Construction de Moteurs d&apos Aviation S N E C M A, Weingarten Schurgin Gagnebin & Hayes, April 24, 2001: US06221475 (32 worldwide citation)

A friction element is made out of a composite material comprising carbon fiber reinforcement and a matrix which, at least in the vicinity of the or each friction face, comprises: a first phase in the vicinity of the reinforcing fibers and containing pyrolytic carbon obtained by chemical vapor infilt ...


26
Jean Paul D Alary, Guy D Agostino, Henry R Leclerc, Denis Sandelis, Pierre M V E Schroer: System for cooling a high power fuel injector of a dual injector. Societe Nationale D Etude et de Construction de Moteurs D Aviation S N E C M A, Bacon & Thomas, November 26, 1996: US05577386 (31 worldwide citation)

The present invention relates to a system for cooling a high power fuel injector of a dual fuel injector wherein the system comprises a first fuel supply circuit having a first conduit connecting a fuel feed supply and the high power fuel injector, the first conduit having a terminal end adjacent to ...


27
Raymond J M Joubert, Marcel R Soligny: Retaining device for the compressor casing of a turbine engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, October 25, 1983: US04411589 (31 worldwide citation)

A ferrule surrounding the blading of a rotor is lined externally with an assembly of elements of revolution. These elements are in the form of cylindrical rings, circular rings or of tori supported between blocking elements. The assembly is formed by alternating rings made of a composite or metallic ...


28
Jean M Surdi: Fan blade axial and radial retention device. S N E C M A, Oblon Fisher Spivak McClelland & Maier, October 23, 1984: US04478554 (30 worldwide citation)

Axial and radial fan blade retention device, the blade comprising a root of dovetail or other re-entrant form capable of being engaged by axial sliding in corresponding bores of the rim of the disc.


29
Mehdi Bensaadi, Michel Andre Albert Desaulty, Sebastien Pierre Jean Pitrou, Pierre Marie Victor Emile Schroer: Aerodynamic fuel injection system for a gas turbine engine. Societe National D Etude et de Construction de Moteurs D Aviation S N E C M A, Bacon & Thomas PLLC, March 14, 2000: US06035645 (30 worldwide citation)

A fuel injection system is disclosed for a gas turbine engine having a fuel injector issuing a primary fuel flow during all operating modes of the gas turbine engine and a secondary fuel flow when operating parameters of the gas turbine engine exceed predetermined values. The fuel injection system i ...


30
Jean Paul D Alary, Michel Desaulty, Denis J M Sandelis, Pierre Schroer: Gas turbine diffuser. Societe National D Etdue et de Construction de Moteurs D Aviation S N E C M A, Bacon & Thomas, January 14, 1997: US05592820 (30 worldwide citation)

A diffuser for a turbojet engine is disclosed in which a plurality of diffuser inlets are arranged in a substantially circular array bounded by inner and outer diffuser walls and by a plurality of partitions extending generally radially from the axis of the annular diffuser. The plurality of diffuse ...