Snecma Moteurs

Jean-Baptiste Arilla

Alain Dominique Gendraud

Paul Rodrigues

Jean-Philippe Julien Maffre

Marc R Marchi

Jean-Claude Christian Taillant

Pierre Debeneix

Thierry Fachat

Anne-Marie Arraitz

Sylvie Coulon

Patrice Rosset

Pierre-Yves Maillard

Patrice Jean Marc Rosset

Jean-Philippe-Julien Maffre

Michel-G&eacute;rard-Paul Hacault

Alain Marc Lucien Bromann

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

Alain Galland

Michel Gerard Paul Hacault

Somphone Sombounkhan

The system enables an increase in the guidance length of the outer pivot of the vane, so that the bushing can be extracted without needing to open the stator casing. It mainly includes a bushing placed inside a bossing of the stator, the length of which is greater than the length of the bossing projecting outwards from the bossing. Thus, the contact length of the outer pivot is prolonged. The bushing is terminated at its end by a gripping hook to enable extraction of the bushing by means of a claw. It is advantageously also provided with a positioning edge.

Guide system for the outer pivot of a variable stator vane, for a turbojet stator

A gas turbine stator including at least a first injector providing a passage for a main cooling air stream into a pressurized chamber. An evacuation mechanism discharges air coming from an internal labyrinth gland of a first cavity towards a lower-pressure second cavity. A second injector evacuates the air contained in the second cavity towards a main duct. The stator further includes a third injector designed to generate an overpressure close to the internal labyrinth gland in the pressurized chamber.

Gas turbine stator

A turbomachine includes a casing, a rotor, and a plurality of cooled ring segments installed between the casing and the rotor, each ring segment containing a main cooling cavity and being attached to the casing by a fastening device. The fastening device can include a clamping screw positioned more or less radially and pinning the ring segment against the casing. The clamping screw is crossed through by a cooling airway that communicates with the main cooling cavity of the ring segment.

Turbomachine with cooled ring segments

An assembly for ventilating a stator ring having branched pipes that include feed pipes, distributors, and a plurality of manifolds adjacent to the stator ring and provided with drilled holes. The distributors connect the feed pipes to the plurality of manifolds, and the plurality of manifolds include pairs of half-shells, each of the half-shells including an end plate having an opening and a rim surrounding the end plate, and the half-shells in each of the pairs being joined to each other at the rims. The distributors include ducts mounted between adjacent ones of the plurality of manifolds and have open ends fitted into openings of the end plates and have abutment portions to the end plates.

Stator ring ventilation assembly

A flange covering a disc of a turbine blade to allow ventilation. A diverted face of the disc is provided with a labyrinth seal with lickers to form a seal. Cutters of the lickers are inclined axially and staggered axially and radially, to off-set the center of gravity of a flexible web of the disc and to encourage deformation of the web towards the disc under the effect of centrifugal forces, to reinforce the contact of a bearing face with a pressure plate of the disc. Thus, hooks usually used to unite the periphery of the web to the disc become superfluous.

Bladed rotor disc side-plate and corresponding arrangement

The support spacer sector ( ) minimizes functional clearances (J) between the end of the blades ( ) and the ring ( ) of the high-pressure turbine and the assembly clearances of the support spacer sectors ( ) on the casing of the high-pressure turbine ( ). Each support spacer sector ( ) has a tab ( ) on the upstream side one end ( ) of which is supported on the inside wall ( I) of the casing of the high-pressure turbine ( ) thus forming an intimate contact between the attachment parts of this support spacer sector ( ) with the corresponding parts of the casing of the high-pressure turbine ( ). This invention applies to turbo-machines fitted on an aircraft.

Stay sector of stator shroud of the high-pressure turbine of a gas turbine engine with clearance control

An arrangement for adjusting the diameter of a gas turbine stator includes a casing having a main portion and rings bordering a vein of a gas flow and located in front of respective levels of mobile blades of a rotor, and communication passages of a gas flow under pressure. The rings are surrounded by the casing and fixed thereto by circular groups of spacers. The rings include a wall extending from the casing to one of the rings and separating two chambers. The wall includes an outside edge curved into a spacer hook and engaged between the main portion of the casing and a respective appendage curved into a casing hook associated with the spacer hook. The communication passages of the gas flow under pressure exist between the chambers. At least one of the communication passages is realized by cavities through a junction of hooks.

Arrangement for adjusting the diameter of a gas turbine stator

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

An apparatus for axially retaining rotor blades to an annular radially extending disk having a recess and a flange. An annular retaining ring is disposed in the recess and includes an axially extending lip and an axially outer side forming an annular bevel surface along a radially outer edge. A retaining plate having an axially extending base, a radially extending outward arm and a radially extending inward leg having an annular bevel surface along an axially inner, radially inner edge is affixed to the disk and the leg cooperates with the lip of the ring. Wherein, the bevel surfaces of the retaining plate and retaining ring are arranged outwardly opposite to one another so that the bevel surfaces are radially compressed along each other as the base slidably engages with the recess walls.

Growing community of inventors

Soisy Sur Seine, France

Jean-Baptiste Arilla