Safran Aircraft Engines

Safran Helicopter Engines

Gilles Gérard Claude Lepretre

Nicolas Paul Tableau

Lucien Henri Jacques Quennehen

Matthieu Arnaud Gimat

Sébastien Serge Francis Congratel

Antoine Claude Michel Etienne Danis

Clément Jarrossay

Thierry Guy Xavier Tesson

Aurélien Gaillard

Hubert Jean-Yves Illand

Denis Daniel Jean Boisseleau

Turbine comprising a casing and a nozzle including a metal outer shroud integral with the casing, a metal inner shroud, and a plurality of nozzle sectors of CMC forming a ring extending between the metal outer shroud and the metal inner shroud, each sector including a mast, an inner platform, an outer platform and at least one airfoil having a hollow profile defining an inner recess, each of the inner and outer platforms having an opening communicating with said inner recess, and the mast passing through said openings and the inner recess and being attached to said casing and connected with said nozzle sector. The mast comprises at least one fastening projection having at least one portion extending from a radially outer end of the mast in a direction opposite to the center of the mast and in a plane orthogonal to the radial direction.

Turbomachine turbine having CMC nozzle with load spreading

A turbine comprises a casing, an outer metal shroud, an inner metal shroud and an annular distributor having a plurality of CMC ring sectors, each sector comprising a mast, an inner platform, an outer platform and at least one blade having a hollow profile that defines an inner housing, the inner and outer platforms each having an opening communicating with said inner housing, and the mast passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder projecting axially towards the outside of the mast configured to radially cooperate with a first shoulder and radially press the blade against the mast.

Turbomachine turbine having a CMC nozzle with load spreading

The invention relates to an assembly comprising a turbomachine casing () and a nozzle made of ceramic matrix composite material having a blade (), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part () of the nozzle to the casing (), said connecting part () extending substantially radially outwards, the blade () and said connecting part () being formed in one piece, said assembly being characterized in that the connecting part () is fastened to a first radial wall () integral with the casing () by fastening means ().

Attachment of a nozzle to a casing of a turbomachine

A turbine of a turbomachine includes a ceramic matrix composite sector of a stator includes an outer platform and an inner platform connected via at least one vane. The outer platform has means for attaching to a sector of a metallic support, the attachment means having at least one central rim and two lateral rims. The central rim is radially offset with respect to said lateral rims along a directrix line such that the central rim is radially on one side of said directrix line and the lateral rims on the other. The central rim and said central hook bear radially against one another and are located radially on either side of said directrix line. The lateral rim and said corresponding lateral hook bear radially against one another and are located radially on either side of said directrix line.

Connection between a ceramic matrix composite stator sector and a metallic support of a turbomachine turbine

An assembly comprising ring sectors made of a first material, the sectors being placed circumferentially end to end and suspended from an outer casing, and radial positioning means comprising at least one annular tongue made of a different material, for fastening the ring sectors to the outer casing, by an annular support. The radial positioning means further comprise an eccentric spreader engaged on one side with said at least one annular tongue and, on the other side, with the sectorized annular element, and acting to enable the distance between the annular tongue and the sectorized annular element to be adjusted radially.

Growing community of inventors

Moissy-Cramayel, France

Gilles Gérard Claude Lepretre