Safran Aircraft Engines

Snecma

Sebastien Digard Brou De Cuissart

Patrice Eneau

Charlotte Marie Dujol

Matthieu Jean-Luc Vollebregt

David Mathieu

Eric Herzer

Sami Kelim Benichou

Patrick Emilien Huchin

Arnaud Nicolas Negri

Serge Alain Fargeas

Ba-Phuc Tang

David Locatelli

Christian Bariaud

Guillaume Klein

Damien Alquier

Anthony Texier

Vincent Marc Herb

Bruno Richard

Marie Mineur-Panigeon

Josserand Bassery

Philippe Metron

Celine Jeanne Marcillaud

Matthieu Le Ray

Bruno Marie Benjamin Jacques Richard

Stephanie Deflandre

Sibylle Doremus

Francois Casteilla

Chantal Sylvette Marie-Noël Langlois

Benoit Georges Marie

Valery Piaton

Eric Rene Herzer

Bruno Marie Richard

Arnaud Negri

Serge Fargeas

Yvan Rappart

Vincent Herb

Chantal Sylvette Langlois

A turbine blade for a turbomachine such as a turboprop or a turbojet, the blade including a root, a vane carried by the root and extending in a spanwise direction, ending at a tip, the vane including a pressure-side wall and a suction-side wall spaced apart from each other, and at least one duct configured to collect cooling air at the root and to make same flow in the vane in order to cool same; holes and/or slots made in the walls of same in order to discharge the cooling air out of the vane; an upper inner cavity located at the tip of the vane in order to cool same; and wherein at least one of the ducts directly supplies the upper cavity with cooling air collected in the root.

Turbine blade with optimised cooling

A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.

Method for manufacturing a two-component blade for a gas turbine engine and blade obtained by such a method

A method of fabricating at least one metal part for a turbine engine, the method including the steps of casting a metal alloy by centrifuging into a permanent metal mold for making a blank; obtaining a cast blank of elongate shape and of section that is circular or polygonal; and machining the blank to make the part.

Method for manufacturing at least one metal turbine engine part

A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.

Turbomachine rotor blade

A method of manufacturing a core for molding a blade of a turbomachine, including placing a flexible ceramic sheet in a cavity of a mold in such a way as to shape the ceramic sheet, introducing a ceramic paste into the cavity of the mold, the ceramic paste forming at least one frame in contact with the ceramic sheet, and co-sintering the ceramic sheet and the frame in such a way as to rigidly join together the ceramic sheet and the frame, the frame maintaining the shape of the ceramic sheet given by the mold during the preceding co-sintering phases.

Method for manufacturing a core for moulding a blade

A casting method for obtaining a part that includes a tapering portion, and a turbine engine blade obtained by casting and including a tapering trailing edge, are provided. The method includes: providing an insert element having a tapering section; making a shell around the insert element; and casting a molten material into the shell including the insert element.

Casting method for obtaining a part including a tapering portion

The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-side wall in pressure-side cavities, and radially toward the inside along the suction-side wall in a suction-side cavity that is separated from the pressure-side cavities by an internal wall of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-side and suction-side walls thereby limiting the inhomogeneity.

Turbomachine turbine blade comprising a cooling circuit with improved homogeneity

A turbine nozzle for a turbomachine, the nozzle including two coaxial platforms interconnected by radial vanes, an inner platform being connected to an annular partition that is festooned or crenellated and on which there is fastened an annular support carrying elements made of abradable material. The support is capable of sliding circumferentially over the partition between a mounting-and-dismounting position and a position for locking the support on the partition.

Turbine nozzle for a turbomachine

A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold.

Method of manufacturing a blading component

The invention relates to a sectored distributor () for a turbomachine, including two coaxial platforms mutually connected by radial blades, the inner platform () being connected to an annular partition () for suspending an annular mounting () carrying elements () made of material subject to abrasion, this mounting sliding circumferentially on the partition and comprising a means engaging with means corresponding to the inner periphery of the partition to ensure radial restraint of the mounting on this partition.

Sectored distributor for turbomachine

Growing community of inventors

Paris, France

Sebastien Digard Brou De Cuissart