51
Guillaume H Chaput, Paul Martyez, Jean Claude C Taillant: System for removably mounting a pre-vaporizing bowl to a combustion chamber. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, June 29, 1993: US05222358 (25 worldwide citation)

A system is described for removably attaching a pre-vaporizing bowl to the wall of the combustion chamber. The system prevents relative rotation between the pre-vaporizing bowl and the combustion chamber, as well as any relative axial movement between these elements. The system enables the pre-vapor ...


52
Gerard E A Jourdain, Marc G Loubet: Heat protective lining for an afterburner or transition duct 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, December 3, 1991: US05069034 (24 worldwide citation)

A heat protective lining for the afterburner or transition duct of a turbojet engine comprises an assembly of tiles overlapping laterally and longitudinally to form overlapping rings of tiles in which the tiles of each ring are offset laterally from those of each adjacent ring by half a tile width. ...


53
Denis R G Laffitte, Guy H Louis, Alain M M Raybaud: Turbine distributor vane. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, September 13, 1983: US04403917 (24 worldwide citation)

A turbine nozzle vane of the kind which includes at least one inner hollow portion inside which a corrugated sleeve positioned against the sides thereof against protruding components. The protruding components against which the sleeve stands are arranged along the inner side and the outer surface ac ...


54
Christine J M Ambrogi, Denis R H Ansart, Serge M Meunier, Denis J M Sandelis: Double wall construction for a gas turbine combustion chamber. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, February 4, 1997: US05598697 (24 worldwide citation)

A wall structure for a wall bounding a combustion chamber of a gas turbine engine is disclosed having a first wall with an inner surface facing towards the interior of the combustion chamber and an outer surface facing away from the interior of the combustion chamber such that the inner surface form ...


55
Francis L Gonthier, Bernard Mariner: Control mechanism for variably settable vanes of a flow straightener in a turbine plant. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, September 27, 1988: US04773821 (24 worldwide citation)

The connection between the actuating link of each variably settable vane of a compressor flow straightener in a turbine plant and the control ring for the vanes comprises a cylindrical roller rotatably mounted in a bore in the ring parallel to the axis of the compressor, the roller having a radial b ...


56
Claude M Mons, Michel J Pernot, Roland R Spinat: Abradable seal and its method of production. Societe Nationale D Etude Et De Construction De Moteurs D Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, December 27, 1983: US04423097 (24 worldwide citation)

A seal intended to wear from abrasion for use in contact with a rotor zone of a rotating machine, of the type made up of a dispersion of hollow microspheres in a binder providing cohesion of the microspheres among themselves and their attachment to a metallic support. In order to make it possible to ...


57
Yves R Halin, Rene M J Hersen: Device for the detection of the position of the thrust reverser of a turbojet engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, March 20, 1984: US04437783 (24 worldwide citation)

Device for the detection of the position of the thrust reverser of a turbojet engine and its locking element, which includes an element integral with the moving part of the reverser, which cooperates with a mechanical locking device and a stationary electrical detection device for detecting the posi ...


58
Michel A A Desaulty, Denis J M Sandelis, Pierre M V E Schroer: Perforated wall for a gas turbine engine. Societe National D Etdue et de Construction de Moteurs D Aviation S N E C M A, Bacon & Thomas, January 7, 1997: US05590531 (24 worldwide citation)

A wall structure for a gas turbine engine structure, such as a combustion chamber or an afterburner duct is disclosed having a plurality of cooling orifices formed through the wall located in a plurality of odd and even transverse rows, each row having a plurality of cooling orifices located in a pl ...


59
Jean M Surdi: Device to lock the blades of a turboblower and to fasten the front cowl of a turbojet engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, September 20, 1983: US04405285 (24 worldwide citation)

Device for the locking of blade roots and the fastening of the forward cowl consisting of a fastening piece comprising a parallelepipedic part (16) engaging radial slots (5) of the teeth (4) of the rim, a prismatic part (17), the convergent faces of which are resting against the sides of the groove ...


60
Bruno A Beutin, Joel Creti, Jean Pierre Donnadieu, Francis G A Garnier, Michel G Hugues, Jean Loic H Lecordix, Claude P H Maignan, Gilles C G Massot, Jean Marie N Pincemin, Christophe J F Thorel, Carole C Touron, Gerard M R M Vennin: System for regulating oil and fuel temperatures of a turbojet engine. Societe Nationale D Etude et de Construction de Moteurs D Aviation S N E C M A, Bacon & Thomas, April 1, 1997: US05615547 (24 worldwide citation)

A system is disclosed for regulating oil and fuel temperatures in a turbojet engine having an engine accessory driven at constant speed by a power transmission which is driven by the turbojet engine. The system has a first closed oil circuit for circulating oil through the turbojet engine, a second ...