Abstract: A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.

Abstract: The present invention relates to a turbine rotor (1) comprising a rotor disc (2), provided at its periphery with a plurality of axial cells (23) for receiving a bilobed root (30) of a blade (3), each cell (23) comprising a radially inner cavity (232) and a radially outer cavity (231). This rotor is characterised in that it comprises a ring (4) for axially retaining the blade roots and an annular flange (5), the ring (4) comprising a radially inner portion provided with notches (43) and being arranged against the upstream face (21) of the disc (2), so that each of its notches (43) is located opposite a cell (23) of the disc (2), the flange (5) being secured against the upstream face of the ring (4), forming a space (E) with said disc (2), and comprising at least one air-intake opening (54) which opens into said space (E), and in that each blade (3) comprises a groove (33) for receiving the outer circumferential edge (46) of said ring (4).

Abstract: In one embodiment, a method comprises: obtaining a plurality of results for a corresponding plurality of independent tests performed on a corresponding plurality of services in a computer network, the plurality of results comprising one or more determined pathways through the computer network; determining a specified subset selection regarding the plurality of results, the specified subset selection corresponding to at least two independent service-related tests; combining a portion of the plurality of results into an aggregated results subset according to the specified subset selection; generating a graphical representation visualization of the aggregated results subset, the graphical representation visualization illustrating a plurality of specific pathways through the computer network corresponding to the aggregated results subset; and providing, to a graphical user interface, the graphical representation visualization of the aggregated results subset, the graphical user interface providing for further spe

Abstract: The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising: a flange extending radially relative to the axis; —a ring seal mounted on the flange and comprising an inner face that is configured to bear an abradable element; —a ventilation cavity delimited radially on the inside by an outer face of the ring seal and downstream by an upstream face of the flange; —a baffle configured to guide an airflow toward the ventilation cavity; and—at least one through-opening formed in the ring seal and configured to put the ventilation cavity in fluidic communication with the inner face of the ring seal.

Abstract: In one embodiment, a method comprises: obtaining a plurality of results for a corresponding plurality of independent tests performed on a corresponding plurality of services in a computer network, the plurality of results comprising one or more determined pathways through the computer network; determining a specified subset selection regarding the plurality of results, the specified subset selection corresponding to at least two independent service-related tests; combining a portion of the plurality of results into an aggregated results subset according to the specified subset selection; generating a graphical representation visualization of the aggregated results subset, the graphical representation visualization illustrating a plurality of specific pathways through the computer network corresponding to the aggregated results subset; and providing, to a graphical user interface, the graphical representation visualization of the aggregated results subset, the graphical user interface providing for further spe

Abstract: A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.

Abstract: A turbine stator assembly including a guide vane assembly and a sealing ring bearing an abradable element of a dynamic sealing ring. The assembly includes pins secured to the sealing ring and cooperating with respective oblong openings formed in the guide vane assembly so as to allow a radial movement of the ring with respect to the guide vane assembly in order to compensate for differential thermal expansions. A seal is arranged so as to compensate for circumferential spaces between ring sectors forming the guide vane assembly.

Abstract: The present invention relates to a rotating assembly of a turbomachine, comprising:—a shaft configured to drive a propeller of the turbo machine around an axis and comprising a first flange radially extending from the shaft, the first flange being monolithic with the shaft;—a sleeve fitted onto the shaft and comprising a second flange radially extending from the sleeve, the sleeve being attached to the first flange of the shaft by means of the second flange; and—at least one component connected to the shaft by means of the sleeve so as to be rigidly connected to the shaft to move therewith, the component comprising at least one sealing element.

Abstract: A device for machining material includes a rotatable turret including a plurality of plank holding positions, each plank holding position including a plank holding device. A projector is configured to project at least one cut line on a first surface of a plank. A cutting device is positioned adjacent to the turret, the cutting device includes a cutting tool configured to cut a trim section along a second surface of the plank to establish a substantially planar portion and/or to locate defects of the first edge. A sensor is configured to scan the first edge of the plank and determine whether the groove and the substantially planar portion are within a predetermined tolerance. A jointing device is positioned adjacent to the turret, the jointing device includes a joint cutting tool configured to cut at least one groove on the second surface.

Abstract: A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.

Abstract: The invention relates to a casing (3) of an aircraft turbomachine, said casing comprising: —an annular shell (9) extending around an axis A and made of a composite material comprising fibres which are woven and embedded in a resin, —an annular layer (4) made of abradable material extending inside the shell, around axis A, and obtained by spreading and polymerising a paste, and—support panels (10) which extend around axis A and are interposed between the shell and the abradable layer.

Abstract: A turbomachine blade is made of composite material formed of woven fibers and embedded in a polymerised resin. The blade includes a root connected by a stilt to a vane which comprises a pressure side and a suction side. At least one anti-wear strip of fabric is located on a surface of the root and/or the stilt. At least one anti-wear strip is secured to the root surface in a unitary manner by the resin.

Abstract: A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.

Abstract: A turbine stator assembly including a guide vane assembly and a sealing ring bearing an abradable element of a dynamic sealing ring. The assembly includes pins secured to the sealing ring and cooperating with respective oblong openings formed in the guide vane assembly so as to allow a radial movement of the ring with respect to the guide vane assembly in order to compensate for differential thermal expansions. A seal is arranged so as to compensate for circumferential spaces between ring sectors forming the guide vane assembly.

Abstract: A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.

Abstract: An approach to automatically provision a data service name (APN or DNN) when an endpoint device connects to a mobile network is described. A methodology includes receiving from an endpoint device a first request to connect to a mobile network, the first request including an identifier of the endpoint device and a default data service name, responsive to detecting the default data service name, determining, from the identifier of the endpoint device, a group to which the endpoint device belongs along with a corresponding group identifier for the group, querying a repository with the group identifier, and receiving, in response, an assigned data service name that is associated with the group identifier, providing the assigned data service name to the endpoint device, and receiving from the endpoint device a second request to connect to the mobile network, the second request including the assigned data service name.

Abstract: A liquid lens including a first liquid comprising a polyfluoroaromatic compound represented by formula (I): Fx—(aromatic)—Y—R1. “x” is within a range of from 2 to 5. Y is one of CH2, Si(Alk)2, Ge(Alk)2, O, and S. “Alk” is a linear aliphatic chain. R1 is any organic group, but can be one of a linear aliphatic chain, a cycloaliphatic, a fluorocycloaliphatic, and an aromatic residue. “Aromatic” is any six carbon aromatic ring. Examples of the chemical compound represented by formula (I) include butylpentafluorobenzene; dimethylnonafluorohexylpentafluorophenylsilane; trimethylpentafluorophenylgennane; butoxypentafluorobenzene; cyclopentoxypentafluorobenzene; 1-n-octyloxypentafluorobenzene; cyclooctyloxypentafluorobenzene; 1-n-dodecyloxypentafluorobenzene; cyclopentylpentafluorophenylsulfide; phenoxypentafluorobenzene; 2,4-difluoroanisole; and heptafluoropentyloxypentafluorobenzene. The first liquid has a density in a range of from 0.95 g/mL to 1.35 g/mL (at 20° C.).

Abstract: In one embodiment, a method includes receiving, by a network orchestrator, trace parameters from a user device. The method also includes determining, by the network orchestrator, to initiate a network path trace for the application, generating, by the network orchestrator, a filter policy for the network path trace using the trace parameters, and allocating, by the network orchestrator, a trace identification to the network path trace. The method also includes initiating, by the network orchestrator, the network path trace within a network by communicating the filter policy and the trace identification to a first node of the network and receiving, by the network orchestrator, network path trace data from a plurality of nodes of the network. The method further includes generating, by the network orchestrator, a trace report for the application using the network path trace data.

Abstract: A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.

Abstract: A method for manufacturing a part made of composite material for a turbomachine, in particular of an aircraft, includes the steps of: b) arranging a preform made of fibers in a mold, c) injecting polymerizable resin into the mold, d) machining the part, and e) visually checking the part. Step b) is preceded by a step a) in which at least one compliance coating is deposited in the mold. The compliance coating has a calibrated thickness (X) and at least one visual aspect identifiable by an operator. The coating is configured to cover at least one area of the preform and to be rigidly attached thereto by the resin at the end of step c) Step e) includes verifying, by the operator, the presence of the aspect in the area.