Abstract: The present invention relates to a turbomachine rotor balancing system comprising a balancing flange (52) provided with through-passageways (78), the system further comprising balance weights (54) each mounted fixedly on the flange (52) by means of a first and a second screw/nut assembly (56a, 56b) having a first and a second screw (84, 84) passing through a first and a second passageway (78, 78). According to the invention, said first screw is pressing against a first tangential end side (116) of the first through-passageway, and at a distance from a second tangential end side, and the second screw is pressing against a second tangential end side (118) of the second through-passageway, and at a distance from the first tangential end side.

Abstract: A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing.

Abstract: A turbomachine rotor balancing system including a balancing flange provided with through-passageways, and balance weights mounted fixedly on the balancing flange by at least one screw/nut assembly passing through one of the passageways is disclosed. For each of the passageways, the flange has on its first face a first recess passing via the radial summit of the passageway. This first recess being deprived of contact with the screw head pressing on this first face. The flange has on its second face a second recess passing via the radial summit. The second recess being deprived of contact with the balance weight pressing on this second face.

Abstract: A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing.

Abstract: Turbine engine, including a final centrifugal compressor stage associated with a diffuser for supplying air to a combustion chamber, and ventilation means for ventilating a high-pressure turbine wheel, including injection means for injecting air onto the wheel and take-up means for taking up a flow for cooling the impeller of the compressor, wherein these take-up means comprise a labyrinth seal mounted at the outlet of the injection means and the air outlet orifices installed between the injection means and said labyrinth seal and leading upstream of the turbine wheel.

Abstract: A method for bonding a first part made of a composite to a second part to a predetermined dimension is disclosed. The method includes placing an insert into the first part, a first surface of the insert protruding beyond the predetermined dimension; machining the insert until the first surface is at the predetermined dimension; placing the second part on the insert; and fastening the second part via the insert. The use of an insert makes it possible to produce, with high precision, a reproducible assembly, which can still be dismantled.

Abstract: A device attaching an afterburner to a turbojet casing. The device comprises a transverse plate for attachment to the casing and at least two side brackets for supporting two legs of the afterburner. The brackets and the two legs extend longitudinally. The afterburner includes a flame-arrestor arm with the two legs.

Abstract: An exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held by an elastically deformable element that acts axially.

Abstract: The invention relates to a turbomachine blade made of composite material including fiber reinforcement, the blade being obtained by three-dimensionally weaving yarns and densifying with a matrix. The blade comprises a single piece constituting both the airfoil and the root of the blade. The blade root has two substantially plane opposite side flanks that are formed in register with the pressure side and suction side surfaces respectively of the airfoil and it is clamped between two metal plates that are fastened against the side flanks of the root.

Abstract: The invention relates to a turbomachine rotor wheel (1) having composite material blades, the wheel comprising a slideway disk (10) having a circumferential groove (12) at its outer periphery, the groove having an opening that is narrower than its bottom, with a plurality of composite material blades (100) each having a blade root (102) engaged in the groove of the slideway disk and presenting a longitudinal section adapted to the longitudinal section of the slideway disk in order to be held radially therein by co-operating shapes, and an orientation disk (200) fastened coaxially around the slideway disk and including, in its outer periphery, a plurality of axial slots (208) each of which is open at one end, each slot presenting a cross-section that is adapted to the cross-section of a corresponding blade root so as to hold it angularly by co-operating shapes.

Abstract: The invention provides a turbine machine rotor having blades of composite material, the rotor comprising an assembly disk, a plurality of composite material blades mounted on the assembly disk via their roots and each provided at its free end with a platform, and a metal shroud positioned on the blade platforms concentrically around the assembly disk and including labyrinth teeth that project radially outwards in order to abrade an abradable material carried by a casing surrounding the rotor, the casing being held stationary both axially and circumferentially relative to the blade platforms and being suitable for moving radially outwards in operation relative to the blade platforms.

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: 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.

Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a substantially rectangular cross-section formed in a housing (12) and having a radially internal wall (22) swept by an airflow (24), and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the airflow entering through the orifice (20), formed by a plate (44) borne by a maneuvering member (50) mobile in translation parallel to the axis (21) of the orifice (20) between a position in which the plate (44) closes off said orifice and a position in which the plate (44) opens said orifice.

Abstract: The present invention relates to a turbomachine rotor balancing system (61) comprising a balancing flange (52) provided with through-passageways (78) and also comprising balance weights (54) mounted fixedly on the balancing flange by means of at least one screw/nut assembly (56) passing through one of the passageways. According to the invention, for each of the passageways (78), the flange (52) has on its first face (90) a first recess (94) passing via the radial summit (80) of the passageway, this first recess being deprived of contact with the screw head (86) pressing on this face (90), the flange (52) having on its second face (92) a second recess (98) passing via the radial summit (80), this second recess being deprived of contact with the balance weight (54) pressing on this face (92).

Abstract: A convergent turbojet exhaust nozzle comprising a ring of hinged flaps made up of controlled flaps and of follower flaps disposed in alternation and co-operating at their upstream ends with a peripheral sealing gasket arranged at the outlet from an afterburner channel, each flap being made out of a ceramic-matrix composite material, and at its upstream end, each flap being made integrally with bearing means for bearing against the above-mentioned peripheral gasket, and with spherical-joint means between their upstream ends.

Abstract: Gate valve (10) for a system controlling cooling in a turbomachine, comprising a gate (20) mounted so that it can pivot about an axis (16) between a position in which it shuts off an air passage orifice (72) and a position in which it opens the orifice (72), and means (12, 14, 18) for rotating the gate (20) about the axis (16), these means comprising two superposed coaxial rotary members (14, 18) collaborating with one another via cam surfaces (40, 46) designed such that rotating the first rotary member (14) from the shut-off position causes a translational movement of the second rotary member (18) and of the gate (20) along the axis of rotation (16) followed by a rotation of this member (18) and of the gate (20) about this axis. Application of the invention to the cooling of turbojet jet pipe nozzle flaps.

Abstract: Mounting an exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held in particular by elastic stress means that act axially.

Abstract: The present invention relates to a turbomachine rotor balancing system comprising a balancing flange (52) provided with through-passageways (78), the system further comprising balance weights (54) each mounted fixedly on the flange (52) by means of a first and a second screw/nut assembly (56a, 56b) having a first and a second screw (84, 84) passing through a first and a second passageway (78, 78). According to the invention, said first screw is pressing against a first tangential end side (116) of the first through-passageway, and at a distance from a second tangential end side, and the second screw is pressing against a second tangential end side (118) of the second through-passageway, and at a distance from the first tangential end side.

Abstract: The invention relates to a device for attaching an afterburner to a turbojet casing (C), the afterburner comprising a flame-arrestor arm (1) comprising two longitudinal legs (7,8). According to the invention, the device (40) comprises a transverse plate (20) for attachment to the casing (C) and at least two side brackets (30,30?) for supporting the legs (7,8), the support brackets (30) extending longitudinally.