Snecma

Snecma Moteurs

Denis Gabriel Trahot

David Mathieu

Didier Hippolyte Hernandez

Arnaud Nicolas Negri

Ba-Phuc Tang

Guillaume Klein

Alexandre Gimel

Sebastien Congratel

Raphael Dupeyre

Thomas Lardellier

Denis Jean Maurice Sandelis

Christophe Pieussergues

Patrice Andre Commaret

Christophe Remy

Patrice André Commaret

Gilles Lepretre

Damien Alquier

Romain Biebel

Pierre Pascal Sablayrolles

Yannick Collin

Laurent Marnas

Martine Bes

Slim Bensalah

Xavier Godfrind

Romain Bard

Pierre Sablayrolles

A turbomachine rotor blade, said blade having, at the distal end thereof, a heel comprising: a platform () having a first edge () on the lower side and a second edge () on the upper side, at least one sealing member having a first end portion () on the lower side and a second end portion () on the upper side, said sealing member having a sealing top that extends radially outwards from said platform () between said first and second end portions (), characterized in that, for at least one sealing member, the heel () comprises, on at least at one of the edges (), a portion forming a bowl () extending along the end portion () of the sealing member which corresponds to the edge (), the portion forming the bowl () being suitable for receiving a deposit of anti-wear material.

Turbomachine rotor blade

A blank casting for producing a turbine engine rotor blade, with a vane connected by a platform to a root, is provided. The root has an axial machining allowance intended to be removed by machining from each of its axial extremities. At least one of the axial extremities of the root includes at least one transverse channel that extends over the entire transverse width of the root and whose depth is greater than the machining allowance. A process for obtaining the blade by machining this blank casting is also provided.

Blank casting for producing a turbine engine rotor blade and process for manufacturing the rotor blade from this blank

A turbine engine blade includes an airfoil connected by a platform to a middle radial wall extending axially and prolonged radially inwards by a blade root that is mountable in a slot of a disk, and the platform and the middle radial wall defining two lateral cavities situated on either side of the middle radial wall and opening out circumferentially to receive scaling members. The cavities are open downstream with two fins projecting on either side of the middle radial wall at downstream end of the middle radial wall, the fins coming to bear against two adjacent teeth of the disk between which the slot is formed. The downstream end of the middle radial wall includes a setback extending between at least one rib of the platform and the fins.

Turbine engine blade

A turbomachine vane for cooperating with a vane retention disk including a plurality of peripheral teeth, the vane including a shank including a neck and a bulb for cooperating with a socket of the disk so as to radially hold the shank in the socket, the socket being a space bounded by two successive teeth of the disk, a pole on top of the neck, including two side walls facing the active surface side of the vane and two side walls facing the passive surface side of the vane, each wall having a rib at a lower end of the pole, the rib extending in the direction of the side wall facing the wall and providing a function of holding the vane when the vane is retained in the disk.

Turbomachine vane cooperating with a vane retention disk

A movable blade for a turbomachine, the blade including at its distal end a top portion including opposite first and second side edges and upstream and downstream sealing wipers. Each of the first and second side edges has a substantially Z-shaped profile between the upstream and downstream wipers. On a side of the first side edge, the platform includes a first outwardly projecting rim not connected to either of the upstream and downstream wipers. The platform includes a second outwardly projecting rim, the second rim including a downstream portion connected to the downstream wiper and extending along the second edge, and an upstream portion extending the downstream portion as far as the upstream wiper, and set back relative to the second side edge.

Movable blade for a turbomachine

A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device has symmetry of revolution about an axis and includes radial swirl inducers of outside diameter D, a bowl spaced axially from the radial swirl inducers, and a support ring for supporting the injection device, which is arranged around the bowl. The bowl has a cylindrical wall extended by a flared wall, the flared wall being provided with air intake holes. The support ring includes a first cylindrical portion of outside diameter D, connected to a second cylindrical portion of outside diameter Dspaced axially from the first cylindrical portion, the first cylindrical portion being connected to the cylindrical wall of the bowl by a plurality of support tabs.

Device for injecting a mixture of air and fuel, and a combustion chamber and turbomachine provided with such a device

The present invention is concerned with an annular combustion chamber of a gas turbine engine with an external annular wall and an internal annular wall, including an upstream fairing for separating the gas stream at the inlet of the chamber into a combustion stream and a bypass stream which bypasses the inlet of the chamber, the fairing including an annular wall forming a cap, which includes a downstream portion for fastening to a wall of the chamber and an upstream portion forming an edge of the flow cross section for the combustion stream, wherein the upstream portion is continued into at least one additional downstream portion for fastening to the wall of the chamber.

Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas stream, annular wall forming a cap of the upstream fairing of the chamber, and gas turbine engine with the chamber

An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and outer fastener flanges for fastening respectively to inner and outer shells of a turbomachine casing in order to hold the combustion chamber in position, the inner flange being provided with a plurality of holes for feeding cooling air to a high pressure turbine of the turbomachine, the air feed holes through the inner flange being distributed circumferentially over at least two rows disposed in a staggered configuration.

Annular combustion chamber for a turbomachine with an improved inner fastening flange

A turbojet diffuser disposed between a compressor and a combustion chamber, and secured to an outer upstream annular flange of an outer casing of the combustion chamber by suspension means which comprise a first frustoconical wall extending from the outer longitudinal wall of the diffuser towards the combustion chamber, and a second frustoconical wall extending towards the compressor between the first frustoconical wall and the outer casing of the combustion chamber.

Turbojet diffuser

Growing community of inventors

Herblay, France

Denis Gabriel Trahot