Abstract: A device for holding (101) at least one cooling tube (120) of a turbomachine casing (10) cooling system (100), the holding device including a fixing frame (104), a holding member (160) being configured to hold two cooling tubes (120), and a connection assembly (140) between the holding member (160) and a fixing frame (104), extending on either side of the frame, the connection assembly (160) comprising a connection part (150) extending through an opening (108) of the fixing frame from an outer portion (141) to the inner portion (142) of the connection assembly, the inner portion (142) being disposed between two cooling tubes (120) and secured to the holding member (160) while the outer portion (141) comprises a resilient return member (170) urged in compression towards the fixing frame by the connection part (150).

Abstract: Drive equipment for rotating by friction an aircraft wheel equipped with a drive track and mounted to turn about an axis (X) on an axle of an aircraft undercarriage. The equipment comprise a base (22), a slide (24) mounted on the base on a sliding axis extending in a radial direction (R1, R1), a support (26) pivotable on the slide on an axis parallel to the rotation axis of the wheel; two rollers (21) rotatable on rotation axes parallel to the pivot axis; a central shaft (28) mounted for rotation on the support and being in engagement with the two rollers to provide their rotation; and an actuator (23A, 23B, 30) for moving the slide and the support between a disengagement position with the rollers distant from the wheel drive track and an engagement position with the rollers are held in contact with the drive track of the wheel.

Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.

Abstract: Relates to a vane for a turbomachine. The vane (12?) has a blade (13?) and a root (18?) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450?) of the root is connected to a radially internal end (430?) of the leading edge (431?) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.

Abstract: The invention relates to a rotary assembly for a turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of slots (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (24) of which are engaged axially and retained radially in the slots (22) of the disk, upstream and/or downstream of the disk, an annular sealing flange (52) of cavities (36) formed radially between, respectively, the roots of the vanes and the bottoms of the slots of the disk, said flange comprising an external part (56) arranged axially facing the upstream and/or downstream ends, respectively, of the teeth of the disk and of the roots of the vanes.

Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.

Abstract: A drive roller (1) comprising a central hub (4), a body (5) extending around the central hub, the body (5) being made of a deformable material, a deformable band (8) extending over a circumference of the drive roller, and first rigid fins (17) and second rigid fins (18) arranged in alternation and extending radially inside the body (5). Each first fin presents a proximal end (17a) fastened to the central hub, and each second fin presents a distal end (18b) that extends in the proximity of the deformable band.

Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.

Abstract: A turbine assembly for a turbine engine, includes a rotor disk having a plurality of CMC material blades, a stationary nozzle made of CMC material having a plurality of vanes with outer platforms forming a nozzle ring, a turbine ring made as a single piece of CMC material, and a casing of material presenting a coefficient of thermal expansion that is strictly greater than the coefficient of thermal expansion of the ceramic matrix composite material forming the blades of the rotor disk, the nozzle, and the turbine ring, the casing extending around the nozzle ring and the turbine ring, at least the nozzle ring or the turbine ring being connected to the casing via at least one sliding connection having a degree of freedom to move radially.

Abstract: A system for attaching electrical equipment to a metallic support and including a pin designed to be inserted through a through-housing of the metallic support and a metallic insert of the electrical equipment, and a device for insulating the metallic support, extending between the metallic support and the metallic insert. The system also includes a mechanical retention device designed to apply load to the insulating device so as to keep them in contact with the metallic support and with the metallic insert.

Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.

Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.

Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.

Abstract: Relates to a vane for a turbomachine. The vane (12?) has a blade (13?) and a root (18?) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450?) of the root is connected to a radially internal end (430?) of the leading edge (431?) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.

Abstract: A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion.

Abstract: The invention concerns a tubular shaft (8) of a turbomachine, comprising, at the inner periphery of same, a bath (11), substantially perpendicular to said splines (9), characterised in that said bath (11) comprises cavities (17) distributed over a circumference centred on the axis of rotation (LL) of the shaft (8). The invention also concerns an assembly comprising said turbomachine shaft, a turbomachine and a method for detecting an oil imbalance.

Abstract: A turbomachine turbine blade includes a suction face, a pressure face, a leading edge and a trailing edge as well as a squealer at the tip thereof. The squealer tip includes at least one internal rib that extends from a point of attachment of the rim of the squealer on the suction-face side to a point of attachment of the rim of the squealer on the pressure-face side, and includes a portion for absorbing the load of leakage flows which extends from the suction face and a deflector-forming portion which extends the load absorber portion with an inflection and guides the leakage flows toward the pressure face.

Abstract: The invention relates to a rotary assembly for a turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of slots (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (24) of which are engaged axially and retained radially in the slots (22) of the disk, upstream and/or downstream of the disk, an annular sealing flange (52) of cavities (36) formed radially between, respectively, the roots of the vanes and the bottoms of the slots of the disk, said flange comprising an external part (56) arranged axially facing the upstream and/or downstream ends, respectively, of the teeth of the disk and of the roots of the vanes.

Abstract: A turbine wheel including a plurality of blades having roots engaged axially and held radially in slots in a disk alternating between teeth of the disk, in which the blades have platforms arranged circumferentially end to end and each connected to a blade root by a tang, is provided. Separator walls extend from the tangs in a circumferential direction and from upstream to downstream so as to define radially between the platforms and the teeth of the disk at least a radially inner cavity and a radially outer cavity between two adjacent tangs.

Abstract: A drive roller (1) comprising: a central hub (4); a body (5) extending around the central hub, the body (5) being made of a deformable material; a deformable band (8) extending over a circumference of the drive roller; and first rigid fins (17) and second rigid fins (18) arranged in alternation and extending radially inside the body (5), each first fin presenting a proximal end (17a) fastened to the central hub, and each second fin presenting a distal end (18b) that extends in the proximity of the deformable band.