Abstract: A measuring comb for temperature and/or pressure and/or chemical composition of the gases flowing at the outlet of a turbine engine flow path, in which the flow path extends around an axis of revolution of the flow path, is provided. The measuring comb includes: a comb body with an elongated shape, intended to face the outlet of the flow path, the comb body including at least one measuring opening arranged along an axis, the measuring opening being configured to tap gases flowing at the outlet of the flow path; and an adjusting system configured to adjust an angle between the axis of the at least one measuring opening and the axis of revolution, so as to allow orientation of the at least one measuring opening in the flow direction of the gases at the outlet of the flow path.

Abstract: A combustion chamber for a turbine engine, including an annular end wall provided with injection systems each centred on a respective axis and each having an upstream end forming a bushing for receiving a head of a fuel injector, and an annular shroud covering the end wall and including injector ports respectively arranged facing the injection systems, wherein the annular shroud includes air intake ports separate from the injector ports, and the bushing of each injection system crosses the corresponding injector port and includes at its upstream end a collar having a free end remote from the axis of the injection system by a first distance greater than a second distance separating a rim of the injector port from the axis.

Abstract: A fuel injection device is provided. The device includes a pilot injector opening out into a venturi and an annular row of multipoint injection orifices opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall. The outer peripheral edge of the separation wall has a diameter greater than the diameter of the annular row of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.

Abstract: A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.

Abstract: In known types of injection systems for a turbine engine combustion chamber, the secondary fuel flow strikes the venturi before entering into the combustor. A new injection system is disclosed to overcome this problem, comprising a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. This first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius ? of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector.

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: 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: 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: 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 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 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 rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

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 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 fuel injection device (110) for a turbine engine, the device comprising a pilot injector opening out into a venturi (120) and an annular row of multipoint injection orifices (136) opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall (140), the device being characterized in that the outer peripheral edge (142) of the separation wall has a diameter (B?) greater than the diameter of the annular row (A) of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.

Abstract: A baffle for the bottom of a combustion chamber of a gas turbine engine is disclosed. The baffle includes a flat portion of wall with an opening for an injector of the combustion chamber to pass through, two longitudinal edges for the assembly to two adjacent baffles and two transverse edges. At least one of the edges includes a joint cover arranging a housing along the edge for an edge of an adjacent baffle so as to seal the junction between the two edges. A combustion chamber incorporating the baffles is also disclosed.

Abstract: A baffle for the bottom of a combustion chamber of a gas turbine engine is disclosed. The baffle includes a flat portion of wall with an opening for an injector of the combustion chamber to pass through, two longitudinal edges for the assembly to two adjacent baffles and two transverse edges. At least one of the edges includes a joint cover arranging a housing along the edge for an edge of an adjacent baffle so as to seal the junction between the two edges. A combustion chamber incorporating the baffles is also disclosed.

Abstract: A turbomachine combustion chamber including a substantially L-shaped fuel injector and a device for mounting and fastening the injector in an orifice of the casing of the chamber, is disclosed. The device includes 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: An air bleed device for cooling components in a turbine engine, including an annular conduit having a substantially rectangular cross-section formed in a housing and having a radially internal wall swept by an airflow is disclosed. The device includes an air inlet orifice, and a flap valve for controlling the airflow entering through the orifice, formed by a plate borne by a maneuvering member mobile in translation parallel to the axis of the orifice between a position in which the plate closes off the orifice and a position in which the plate opens the orifice.

Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air inlet orifice (20) formed in an upstream radial wall (38) of the conduit (18), a flap valve (40) for controlling the airflow entering through the orifice (20) and of which the flapper (41) includes a plate (42) applied against the wall (38) and capable of being moved by sliding on said wall (38) by a maneuvering member (50) mobile in translation parallel to the wall (38) between a position in which the plate (42) closes off the orifice (20) and a position in which the plate (42) opens said orifice.