Abstract: The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine nozzle assembly to inner and outer metal shrouds in order to hold said assembly between the shrouds. Locking members are provided to prevent the turbine nozzle from turning about its axis relative to at least one of the metal shrouds so as to prevent the forces that are exerted on the turbine nozzle vanes by the flow of gas coming from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.

Abstract: The present invention provides a fixing or sealing ring for maximizing cooling at the end of a combustion chamber wall. For this purpose, the ring is constituted by a sleeve which is fixed around the end of a wall of the combustion chamber by means of a plurality of orifices for receiving fasteners or by means of any other system for connecting the ring to the wall. The sleeve includes at least one recess in its face facing the wall of the combustion chamber, thereby reducing the area of the sleeve that presses against the wall, and co-operating with said wall to form an open cavity in which a cooling air stream can flow.

Abstract: The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.

Abstract: 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.

Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell (6) of the compressor and an annular structure (7) connected to the shell, and, on the other hand, by the external casing (12) of the diffuser grating and a strut (13) connected to said external casing and to an external engine casing shell (14), this external casing shell (14) being fastened to the annular structure (7) by bolting together flanges, using sealing means provided between the annular structure (7) and the external casing (12) of the diffuser grating.

Abstract: The invention provides a combustion chamber comprising a chamber wall disposed radially inside a casing, an igniter plug for igniting the air-fuel mixture, the plug being mounted on said casing and comprising a body with a free end that is disposed in an opening formed through said chamber wall with a large amount of clearance to accommodate relative displacement between said casing and said chamber wall, and a sealing device provided between said body and the perimeter of said opening, said sealing device comprising an annular plug-guide through which said body passes, the plug-guide being slidably mounted at the radially-outer end of an annular support whose base is secured to said perimeter, wherein the support is secured to the radially-outer portion of a chimney passing through said opening and presenting at its radially-inner end a collar bearing against the inside face of the chamber wall, and wherein a cooling circuit for said collar is provided.

Abstract: The invention relates to an annular combustion chamber for a turbomachine of axis X, in which the chamber end wall is fixed to inner and outer side walls by means of a plurality of radially-inner attachment fittings and by means of a plurality of radially-outer attachment fittings disposed upstream from said chamber end wall by bolting a zone of each of said fittings to said side walls. At least one of said pluralities of attachment fittings is integrated in a ring secured to the chamber end wall and comprises a plurality of pairs of tabs which extend upstream beyond the bolting zones, the two tabs in each pair being disposed circumferentially on either side of a bolting zone and being interconnected at their upstream end to the upstream end of a fixing plate which extends between said two tabs and which presents a bolting zone for being fixed to the adjacent side wall.

Abstract: In a turbomachine comprising a metal material shell containing in a gas flow direction F: a fuel injection assembly; a composite material combustion chamber; and a metal material sectorized nozzle forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held by a sectorized flexible sleeve of metal material having one end fixed to the combustion chamber by first fixing means and a flange-forming opposite end fixed to the shell by second fixing means. The first fixing means also serve to connect the combustion chamber to the sectorized nozzle.

Abstract: In a turbomachine comprising an annular shell of metal material containing in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material; and an annular nozzle of metal material forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held in position inside the annular metal shell by a plurality of flexible metal tongues each comprising three branches connected together in a star configuration, the ends of two of these three branches being fixed securely to a downstream end of the combustion chamber via respective first and second fixing means, and the end of the third branch being fixed securely to the annular shell via third fixing means.

Abstract: A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.

Abstract: The present invention provides a fixing or sealing ring for maximizing cooling at the end of a combustion chamber wall. For this purpose, the ring is constituted by a sleeve which is fixed around the end of a wall of the combustion chamber by means of a plurality of orifices for receiving fasteners or by means of any other system for connecting the ring to the wall. The sleeve includes at least one recess in its face facing the wall of the combustion chamber, thereby reducing the area of the sleeve that presses against the wall, and co-operating with said wall to form an open cavity in which a cooling air stream can flow.

Abstract: A turbomachine comprises an annular shell of metal material containing in a gas flow direction F a fuel injection assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine, said nozzle being supported by the annular shell and being fixed thereto by first releasable fixing means, and provision being made for the combustion chamber to be mounted in floating manner inside the annular shell and held in position solely by the nozzle to which it is fixed in resilient manner by second releasable fixing means.

Abstract: A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

Abstract: In a turbomachine comprising inner and outer annular shells of metal material containing, in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material having a plurality of air feed orifices in a primary zone and/or in a dilution zone; and an annular nozzle of metal material forming the inlet stage with fixed blades for a high pressure turbine, provision is made for the combustion chamber to be held in position between the inner and outer annular metal shells by means of a plurality of flexible metal tongues having first ends interconnected by respective metal rings fixed securely to said inner and outer annular shells by first fixing means, and second ends fixed securely to the composite material combustion chamber at it air feed orifices by second fixing means.

Abstract: An annular combustion chamber has outer and inner axially-extending side walls of composite material and an end wall of metal material held in position on the outer and inner side walls by fixing means. Provision is made for the fixing means to pass through annular cavities that are designed to receive cylindrical end portions of the outer and inner side walls, and that are created between peripheral edges of the end wall and facing portions folded downstream, a determined amount of clearance J being provided between the peripheral edges and the facing faces of the outer and inner side walls in such a manner as to allow expansion to take place freely, in operation, in a radial direction between said end wall and said side walls.

Abstract: In an annular combustion chamber having inner and outer axially-extending side walls of composite material and an end wall of metal material, provision is made to hold the end wall in position between the side walls of the annular combustion chamber by means of a plurality of flexible metal tongues fixed firstly to said side walls by fixing means and secondly to said end wall by brazing or welding, said end wall further comprising means for providing sealing between said end wall and said side walls.

Abstract: In a turbomachine comprising a metal material shell containing in a gas flow direction F: a fuel injection assembly; a composite material combustion chamber; and a metal material sectorized nozzle forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held by a sectorized flexible sleeve of metal material having one end fixed to the combustion chamber by first fixing means and a flange-forming opposite end fixed to the shell by second fixing means. The first fixing means also serve to connect the combustion chamber to the sectorized nozzle.

Abstract: A combustion chamber for a gas turbine made up of outer and inner side walls, the combustion chamber being received in a casing so as to define an annular space between the combustion chamber and the casing in which there flows air for combustion, for dilution, and for cooling the combustion chamber, the side walls of the combustion chamber being pierced by a plurality of holes in which bushings of substantially elliptical right section are fixed to define air injection passages for injecting air into the combustion chamber, each bushing having a peripheral wall in which at least one additional orifice is formed opening out into the combustion chamber in the immediate vicinity of the side wall of the combustion chamber in which said bushing is fixed so that the air passing through said orifice flows substantially along said peripheral wall, the peripheral wall of each bushing having at least one groove opening out into the annular space and into which the or each orifice opens out so as to be fed with air and

Abstract: A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

Abstract: In a turbomachine comprising an annular shell of metal material containing in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material; and an annular nozzle of metal material forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held in position inside the annular metal shell by a plurality of flexible metal tongues each comprising three branches connected together in a star configuration, the ends of two of these three branches being fixed securely to a downstream end of the combustion chamber via respective first and second fixing means, and the end of the third branch being fixed securely to the annular shell via third fixing means.