Abstract: 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.

Abstract: The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).

Abstract: Turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner platform (24), an outer platform (26) and at least one blade (28) having a hollow profile that defines an inner housing (280), the inner and outer platforms each having an opening (245, 265) communicating with said inner housing, and the mast (6) 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 (72) projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder (71) projecting axially towards the outside of the mast (6) configured to radially cooperate with a first shoulder (72) and radially press the blade (28) against the mast (6).

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).

Abstract: 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.

Abstract: The stator shroud is made up of components (2) juxtaposed so as to form circumferences, which are successive and assembled separately to a common housing which surrounds them. Characteristically, the assembly is made with only one single fixing point (7) per component (2), while being completed by a support point (21) sliding along the circumference. The result is a more flexible component assembly and a more even distortion, which allows better control of the clearances between the shroud and the rotor blades it surrounds.

Abstract: A system is disclosed for injecting air and fuel into a combustion chamber of a turbojet engine in which the system includes a fuel injector having an axis A, a first radial swirler located rearwardly of the fuel injector having a plurality of first air passages to direct air into the fuel emanating from the fuel injector in a first plane generally perpendicular to the axis A, a housing located rearwardly of the first radial swirler and forming a pre-mixing chamber bounded by a converging-diverging wall forming a venturi with a throat, the housing having a plurality of second air passages forming a second radial swirler to direct air into the pre-mixing chamber forwardly of the venturi throat in a second plane generally perpendicular to the axis A. The housing also has a plurality of third air passages forming an axial swirler, the second passages and the third passages alternating in a circumferential direction around the housing.