1
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 ...


2
Gerard M F Mandet, Marcel R Soligny: Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, June 24, 1986: US04596116 (40 worldwide citation)

The rotor of each stage of a turbine is surrounded, with a clearance by a fixed ring, formed by a metal ring supporting internally an annular thermal screen, in the form of ceramic segments. Expansions and contractions of the metal ring under the action of air which is supplied thereto in order to c ...


3
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 ...


4
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 ...


5
Louis F Jumelle, Marcel R Soligny: Sealing device for turbine blades of a turbojet engine. Societe Nationale d Etude et Je Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, July 9, 1985: US04527385 (29 worldwide citation)

A sealing device is disclosed for maintaining a small positive clearance between the sealing sectors and the turbine blade tips of a turbojet engine. The sealing segments are connected to an internal ring structure and an external ring structure located within the casing of the jet engine. The two r ...


6
Gerard E A Jourdain, Marcel R Soligny: Injection device for the combustion chamber of turbine engines. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E L M A, Bacon & Thomas, October 18, 1983: US04409791 (23 worldwide citation)

A fuel intake tube passes radially through an engine casing. It is surrounded between the casing and an injector head by a second tube attached to the casing. Guidance means and a sealing element are provided between the fuel intake tube and the second tube. The device is equipped with one or more i ...


7
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.


8
Gerard E A Jourdain, Jean Paul Lagrange, Gerard M F Mandet, Jacques H Mouchel, Jean Philippe E Richard, Marcel R Soligny: Gas turbine engine rotor blading sealing device. Societe National d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, January 14, 1997: US05593278 (20 worldwide citation)

The disclosed invention relates to a sealing device for the rotor blades of a gas turbine engine which permits real time adjustment to be made of the clearances between the rotor blade tips and the sealing structure. The sealing shroud around the turbine wheel is formed of sectors, each sector being ...


9
Jean Pierre Ruis, Marcel R Soligny: Stator assembly for an axial compressor. Societe National d Etude et de Construction de Moteurs d Aviation S N E C M A, Bacon & Thomas, September 24, 1985: US04543039 (15 worldwide citation)

A device for attaching the stator vanes of an axial compressor to an external housing is disclosed. The attachment utilizes an inner casing, having the vanes mounted on it, and an outer casing surrounding the inner casing in such a manner that differential thermal expansion between the various eleme ...


10
Jean G Bouiller, Marcel R Soligny: Inter-shaft journal assembly of a multi-spool turbo-machine. Societe Nationale d Etude et de Construction de Moteurs d Aviation S N E C M A, Oblon Fisher Spivak McClelland & Maier, December 17, 1985: US04558564 (14 worldwide citation)

In a multi-spool turbo machine, a first shaft of the low pressure spool is supported for rotation with respect to a second shaft of the high pressure spool and is located with respect to the second shaft by means of a roller bearing. Rollers of the bearing are inserted between an internal ring mount ...