Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma Moteurs

Snecma

General Electric Company

Pierre Debeneix

Jacky S Naudet

Jean-Louis Charbonnel

Daniel J Marey

Erick Jacques Boston

Yann J Rigaud

Christopher Charles Glynn

Roger C Walker

Alain Marc Lucien Bromann

Jean-Baptiste Arilla

Andre A Camboulives

Paul Rodrigues

Sylvie Coulon

Frederic Paul Eichstadt

Thierry J Niclot

Patrice Jean Marc Rosset

Marcel J Tournere

Jacques Audet

Arnaud Langlois

Claude V Gendronneau

Alain M Bromann

Roger P Hugnet

Philippe Guerout

Gerard Receveur

Jean-Pierre A Mourlan

Florence Ir&egrave;ne No&euml;lle Leutard

Stéphane Caron

Francois Buffenoir

Alain Bromann

Vincent Garnier

Alain Leman

A device for rotationally blocking a retaining ring () on a rotor disk () includes successive first () and second () blocking hooks of the disk (), at least one cleat () of the retaining ring () arranged close to a split () in the ring (). The position of the at least one cleat () on the retaining ring () is such that, when the retaining ring () is in place in a groove () situated in the rotor disk (), the at least one cleat () is in abutment against the first blocking hook (), and the split () is covered by the second blocking hook ().

Device for blocking a ring for axially retaining a blade, associated rotor disk and retaining ring, and rotor and aircraft engine comprising them

A device for guiding pivoting of variable-pitch vanes in a turbomachine, each vane having a pivot formed by a cylindrical axial shank which is guided in a cylindrical chimney of the casing and in a cylindrical orifice of a stationary element which surrounds the outside of the casing and which is centered and fixed relative thereto. The invention improves pivotal guidance of variable-pitch vanes.

Device for pivotally guiding variable-pitch vanes in a turbomachine

A guide device for guiding a variable-pitch blade, in particular in a turbomachine compressor, the blade having a pivot formed by a cylindrical axial shank mounted in a cylindrical housing of a casing and pivotally guided about an axis in said housing by bearings, where the bearings are abutment bearings with conical rollers, the axes of the rollers being substantially perpendicular to the pivot axis of the blade.

Method of guiding a blade having a variable pitch angle

The invention relates to an axial compressor stator for a gas turbine, the stator having a rigid, external, annular frame and axially juxtaposed rings configured within the frame and bearing annuli of stationary vanes. The rings are defined by arcuate segments affixed to the frame. The inside walls of the arcuate segments externally define the aerodynamic conduit for the compressed gaseous fluid. The arcuate segments are brazed segments that include a honeycomb component sandwiched between an inner sheetmetal bounding the aerodynamic conduit and an outer sheetmetal. The outer sheetmetal solely connects the arcuate segments to the frame.

Gas turbine engine axial stator compressor

A joint between a turbine ring. The ring is jointed to a spacer of the turbine by a joint including hooks which fit together on one side, and an abutment of flanges as well as a mortise and tenon joint on the other side. According to the joint, the tenon and mortise are separated from the flanges in abutment to limit the plays in the axial direction, produced by design or by expansions, to increase mechanical strength and simplify manufacturing.

Device for fixing a turbine ferrule

A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring into separate compartments, and each rib having a sealing element disposed alongside it to cover the apertures and seal one compartment from the next. The casing and the ring are fixed together by virtue of bolts which have their axes inclined to the radial direction so that tightening the bolts causes the casing to press radially on the sealing elements at the same time as pressing them axially against the respective ribs.

Turbomachine stator having a double skin casing including means for

A turbjet engine includes various elements for adjustment of play of the stator by having the stator heated or cooled by a gas. The outer housing to which the ferrule bearing the fixed vane stages is secured may be formed of two skins between which the gas is injected. The ferrule may be composed of sectors extending over one circumference fraction and fixed via their center and simply guided at their extremity; finally, it is possible to provide sealing devices between the outer housing and the support bearing surfaces of the ribs of the ferrule elements. The volume between the ferrule and the housing is then sectioned and is able to receive separate gas feedings for play adjustment.

Turbo aero engine equipped with means facilitating adjustment of plays

The exhaust casing of a turbojet engine has a polygonal cross-section and carries at least three hanging lugs provided with holes designed to receive fixing axles of a rear suspension structure for the engine. The axes of these holes are situated at vertices of the polygon defined by the cross-section of the casing, and this polygon is regular except at the position of each of the hanging lugs, where it is deformed to displace the respective vertex radially outward.

Turbojet engine exhaust casing with integral suspension lugs

The exhaust casing of a turbojet engine has a cross-sectional shape in the form of a regular polygon and carries at least three external hanging lugs provided with holes for receiving fixing axles of a rear suspension structure for the engine. The lugs are carried by non-consecutive sides of the casing in ), manner that the geometrical axis of the hole of each lug is situated at the intersection of the median planes of the two sides of the casing adjacent the side carrying the lug.

A multiflow turbojet engine secondary flow adjusting device which includes annular vanes regularly distributed around the secondary duct. The vanes are movable about two fixed axes disposed between one half and one third of the height of the duct when the vane is in the active position. A control mechanism for the vanes are disposed within the interior of the duct and act on the axis of radial symmetry and at two-thirds of the height of the duct when the vane is in the active position. In the inactive position, the vane is parallel to the secondary air flow. The actuator and the fixed support axes form a modular assembly in accordance with another embodiment.

Multiflow turbo jet engine secondary flow adjusting device

The device includes means for transporting and hoisting an engine. The device has common elements constituted by two straps fixed to the housing on a horizontal diameter. The strap fixing lugs have coaxial bores. Each strap receives a removable sleeve which cooperates on its outer surface with the fixing lug bores and with one of the holes of a rod. The other hole of the small rod cooperates with the hoisting means. An element belonging to the transporting means axially transverses the sleeve and retains it in a strap of the transport truck.

Combined fastening device for transporting and hoisting a turbojet engine

An emergency aerosol lubrication device, particularly for airborne engines which includes a mechanism for placing a certain quantity of oil in reserve, an operator-controlled mechanism for atomizing oil in an aerosol container, which is connected to the points to be lubricated, a member for supplying the atomization mechanism with oil drawn from the reserve, and a mechanism for keeping the reserve oil at a suitable temperature.

Growing community of inventors

St Sauveur sur Ecole, France

Pierre Debeneix