Abstract: An interface element to be mounted between a blade root and a blade root housing provided in a turbine disc of a gas turbine engine to limit wear between the root and the housing. The interface element includes: a base, configured to be aligned with a lower part of the root; and first and second upper side walls connected to the base and configured to surround the blade root up to an upper portion thereof, the first upper side wall including at least one ventilation opening to allow a flow of cooling air flowing through the rotor disc housing to flow over the upper portion of the root via the ventilation opening.

Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.

Abstract: A layout of a blisk includes two inserts housed between the bulb of the blade and the wall of a groove in a disk to compensate for variations in inclination between the overhanging faces of the groove and the upper faces of the bulb at their central part. This construction makes it possible to select blades for which upper faces of the bulb are slightly inclined relative to the radial direction, which facilitates their construction from a composite material.

Abstract: A fuel mixing device for an annular combustion chamber of a turbine engine, including a member for centering a turbine engine injector head, at least one air intake ring including blades allowing swirling of air, a bowl including an annular row of air intake orifices, an annular cavity communicating with the air intake orifices, and channels arranged through the blades to feed air to the annular cavity.

Abstract: A rotor includes a disc, on which are fixed vanes, and platforms between these vanes. The rotor is particularly remarkable in that the platforms are fixed securely and tightly to the disc. To this end, the disc includes between two successive vanes an upstream stop projecting axially from the upstream surface, and each platform includes: a plate, a retaining groove extending axially and in which the upstream stop of the disc is engaged, an axial stop bearing axially against the upstream surface of the disc.

Abstract: A turbomachine including an annular combustion chamber, the combustion chamber presenting a connection flange at its downstream end for connection to an outer casing. The connection flange bears axially against the outer casing and is blocked in an axial direction by the upstream end of an inner casing of a high pressure turbine.

Abstract: A diffuser-nozzle assembly mounted at the outlet from a centrifugal compressor is disclosed. The assembly includes a plurality of vanes carried by a radially inner wall forming a surface of revolution and surrounded by an outer casing, elastically deformable devices interposed between the radially outer ends of the vanes of the nozzle and the outer casing. The elastically deformable devices prevent air from passing between the outer casing and the radially outer ends of the vanes.

Abstract: Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated with each injection system (32), comprising at least one wall (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), and an air inlet opening (88) formed at the upstream end of the air manifold (100) and opening radially outwards from an axis (44) of said injection system.

Abstract: A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

Abstract: An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot.

Abstract: A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.

Abstract: A system for cooling the impeller of a centrifugal compressor in a turbomachine is disclosed. The compressor supplies an annular diffuser. The diffuser includes an end-piece that extends downstream and along the impeller of the compressor and is covered on the upstream side by an annular metal sheet. The sheet delimits, with the impeller of the compressor, a first annular passageway to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway to carry away a portion of the air flow coming out of the diffuser.

Abstract: A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating.

Abstract: A device for injecting an air/fuel mixture into a combustion chamber mounted within a restricted space is disclosed. This injection device includes a bowl having an external cylindrical wall continued at its downstream end by a divergent section provided, downstream, with a collar having the form of a ring extending radially outward. The divergent section of the bowl is connected, immediately upstream of the flange, by a connecting wall to a cylindrical ring. The cylindrical ring and the connecting wall form a connection rim oriented in the upstream direction. At least one row of vortex holes is formed in the external cylindrical wall, close to its upstream end, and the connecting wall of the connection rim of the bowl is provided with a row of cooling orifices inclined axially at an angle ? to the axis of symmetry of the injection device.

Abstract: A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser.

Abstract: A gas turbine engine diffuser defined between an external casing and an internal casing of the engine and supplied with air via an upstream annular diffuser duct is disclosed. The diffuser includes a combustion chamber of the convergent type, forming an external annular duct with the external casing and an internal annular duct with the internal casing, and a cowling partially closing off the external annular duct. The cowling is positioned toward the closed end of the combustion chamber.

Abstract: An arrangement for a turbomachine combustion chamber is disclosed. The arrangement includes a chamber end wall pierced by at least one substantially circular opening, a deflector mounted from the downstream side of the chamber end wall in the opening by an annulus, an injector system associated with the opening and including an annular bowl that is flared downstream, passing through the opening, and a pinch ring that cooperates with the annulus to allow the injector system to shift off-center relative to the chamber end wall. The deflector includes an annular collar extending radially inwards. The bowl of the injector system includes at its downstream end an outwardly-open annular groove radially in alignment with the collar of the deflector in such a manner as to enable it to retract into said groove when the injector system shifts off-center relative to the chamber end wall.

Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.

Abstract: A turbomachine combustion chamber including a substantially L-shaped fuel injector and means for mounting and fastening the injector in an orifice of the casing of the chamber, said means including an outer collar carried by the injector and a removable annular spacer surrounding the injector and designed to be interposed between the collar of the injector and the casing.

Abstract: A system of attaching an injection system to a turbojet combustion chamber base. It comprises a deflector welded onto the chamber base. The deflector comprises an annular portion having an edge forming a retaining shoulder directed toward the front of the turbojet and the injection system comprises a collar on which is formed a retaining shoulder directed toward the rear of the turbojet and pressing against the retaining shoulder of the deflector.