41
Gerard M F Mandet, Jacques R Serre: Low pressure turbine rotor suspension in a twin hub turbo-engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, December 24, 1991: US05074109 (28 worldwide citation)

The suspension of the rotor of the low pressure turbine of a twin hub turbo-engine includes a cylindrical support arranged coaxially with the axis of the turbine and firmly attached to the stator by radial spacers at the rear of the turbine, the rotor being carried on a front bearing and a rear bear ...


42
Albert L P Veau: Heat protective lining for a passage in 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, January 14, 1992: US05079915 (28 worldwide citation)

A heat protective lining for a passage in a turbojet engine is formed of tiles arranged side by side to form rings which are themselves arranged end to end. Each tile comprises a panel provided at its upstream and downstream edges with radially outwardly directed flanges forming circumferential stif ...


43
Paul J Legrand, Andre R Notheaux, Guy R Pachomoff, Alexis M G Romanoff: Apparatus for the installation of a jet engine in an aircraft compartment. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, November 1, 1983: US04412774 (28 worldwide citation)

A dolly for use in the installation of a jet engine in an aircraft compartment. The dolly has longitudinal guide rails placed in the compartment and a device including two lateral guide rails and a lower, median guide rail; a foldable and removable front cradle carrying two runners and capable of be ...


44
Marc R Marchi, Jean Claude C Taillant: Seal for gas turbine rotor blades. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, February 4, 1997: US05599170 (27 worldwide citation)

A seal for sealing the gaps between adjacent turbine blade structures is disclosed in which the seal is disposed in a compartment formed between adjacent turbine blade structures having first and second sealing surfaces adjacent to a generally axially extending gap and a generally radially extending ...


45
Francois M P Marlin: Bladed disc for a turbomachine rotor. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, September 17, 1991: US05049035 (27 worldwide citation)

A bladed disc of a turbomachine rotor comprising an array of blades evenly disposed around the rim of the disc and separate platforms secured to the disc between the blades, each platform comprising a plate and a mounting foot at each axial end of the plate by which the platform is secured to the ri ...


46
Jacques R Bart, Gerard E A Jourdain, Daniel Rambach: Sealing device for turbine blades of a turbojet engine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, January 21, 1986: US04565492 (27 worldwide citation)

A sealing device is disclosed for maintaining a small positive clearance between packing segments and the turbine blade tips of a turbojet engine. The packing segments are connected to an inner ring which is, in turn, connected to an outer ring, all disposed within the turbojet casing. The coefficie ...


47
Georges Mazeaud, Francois J P Mirville, Patrick W R Saillot: Cooling system for a gas turbine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, November 17, 1992: US05163285 (26 worldwide citation)

A cooling system is disclosed including a drive shaft interconnecting a turbine rotor wheel with a compressor rotor wheel, a heat exchanger, and an auxiliary air compressor formed as part of the drive shaft which draws air from a portion of the compressor, through the heat exchanger and directs it o ...


48
Alexandre Forestier: Damping device for turbojet engine fan blades. S N E C M A, Oblon Fisher Spivak McClelland & Maier, January 22, 1985: US04494909 (26 worldwide citation)

A damping device for the turbojet engine fan blades which includes a wedge placed between the platforms of the blades, the shanks of the blades, and the disc. The wedge consists of a hollow, bellows-shaped body fitted with an axial stop member, the body being inflated after mounting so that it takes ...


49
Jacques Lesgourgues, Jacques P H Tirole: Gas turbine blade with chamber for circulation of cooling fluid and process for its manufacture. S N E C M A, Oblon Fisher Spivak McClelland & Maier, March 26, 1985: US04507051 (26 worldwide citation)

A gas turbine blade in which are provided inter alia two chambers for the circulation of cooling fluid, lying in proximity to the leading and trailing edges of the blade respectively, two conduits disposed respectively between the first chamber and the leading edge and between the second chamber and ...


50
Mischael F L Derrien: Cooled turbine guide vane. Societe Nationale D Etude et de Construction de Moteurs D Aviation S N E C M A, Oblon Spivak McClelland Maier & Neustadt, June 1, 1993: US05215431 (25 worldwide citation)

A hollow turbine guide blade or vane is provided with three separate cooling circuits formed by virtue of two radial partitions extending the length of the blade within the cavity bounded by the outer wall of the blade and dividing the cavity into first, second and third ducts, and radial passages e ...