Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.

Abstract: A stator vane assembly for a compressor of an aircraft turbine engine includes an inner shroud, an outer shroud and stator vanes. The stator vanes are attached only to the inner shroud and are in non-immobilizing mechanical contact with the outer shroud.

Abstract: A compressor casing for a turbine engine, the casing comprising: a housing comprising a radially inner e surface; an upstream ferrule; and a downstream ferrule; each of the ferrules having a respective inner surface capable of defining an air stream, and each of the ferrules having an outer surface facing the inner surface of the housing, the ferrules being attached to the cantilevered housing and being axially arranged so as to be separated by an axial clearance. Additionally, a turbine engine comprising such a casing and a stage of variable-setting vanes.

Abstract: The invention relates to a sandblasting mask (50) as well as its use for the sandblasting of blade tips in a method comprising a step of positioning a plurality of sandblasting masks (50), each blade passing through an opening (58) of a mask and each blade tip extending projecting from the respective mask, the masks being assembled two by two preferably without play; and a step of sandblasting the protruding blade tips of the masks. The masks (50) are preferably produced by plastic additive manufacturing and coated with a polyurea-based coating.

Abstract: A turbomachine compressor module, comprising an annular array of structural arms defining inter-arm spaces between two circumferentially adjacent arms; and an annular array of stator vanes with variable orientation about a respective axis (A) and disposed at least partially within the inter-arm spaces. The arms are provided with flaps pivotable about a respective axis (B). Also, a turbomachine provided with such a module and a row of rotor blades directly downstream of the module.

Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.

Abstract: A system for disengaging a drive shaft from a bearing support. An assembly formed by the drive shaft and the bearing support is placed above a cylinder, which pushes on the drive shaft by passing by the central hole of the bearing support. The bearing support is driven upwards, but is blocked by a first and a second force transfer device, which allows the drive shaft to be disengaged from the bearing support.

Abstract: A tooling holds a blade during friction welding to a rotor element. The tooling includes a fixed jaw having a central part; two arms separated by a distance d for receiving at least one portion of the blade; and a fixed jaw body with bearing surfaces and a bore for receiving at least one portion of the blade. The bearing surfaces are configured to come into contact with the blade. A movable jaw includes a movable bearing surface that comes into contact with the blade, and pressure means that moves the movable jaw towards the fixed jaw body to press the blade.

Abstract: A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root (1), c) is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.

Abstract: A method and system control the thrust of an aircraft turbomachine having a high bypass ratio by direct action on a variable-pitch system. The variable-pitch system varies the pitch of the vanes of a stator of a low-pressure compressor for the open-loop control of the thrust of the turbomachine. The method also provides closed-loop control of the pitch of the blades of a propeller based on a rotational speed of the propeller.

Abstract: Disclosed is a cart (2) for transporting an aircraft engine, comprising a base frame (4) equipped with wheels (6) for riding on a floor; at least two engine arms (14, 16) extending horizontally and movable vertically relative to the base frame, structured and designed for supporting the aircraft engine; and at least two adapter arms (20) extending horizontally at a higher level than the at least two engine arms, structured and designed for supporting an adapter coupled at the top of the aircraft engine. Disclosed is also a method of transporting an aircraft engine to a test cell.

Abstract: A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.

Abstract: An internal gear pump comprising: a ring with internal teeth delimiting a cavity and a gear disposed in the cavity, the gear comprising external teeth cooperating with the internal teeth to drive the ring in rotation, remarkable in that it comprises a pinion disposed in the cavity and driving the gear in rotation. The pinion cooperates with the external toothing of the gear. In an alternative embodiment, the gear comprises an internal toothing which cooperates with the pinion.

Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.

Abstract: A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the first and second fluid have a respective general direction of flow, and the general direction of flow of the first fluid is parallel to the general direction of flow of the second fluid. The present disclosure also concerns a turbine engine comprising the heat exchanger and a manufacturing method for manufacturing the heat exchanger.

Abstract: A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the body of the heat exchanger is of cylindrical shape. The present disclosure also concerns a turbine engine comprising the heat exchanger and a manufacturing method for manufacturing the heat exchanger.

Abstract: A matrix for exchanging heat between a first fluid and a second fluid, in particular for an air-oil application in a turbine engine, includes an envelope defining a flow path of the first fluid and a network extending into the flow path and in which the second fluid flows. Along the axis defined by the curvature of the matrix, the dimensions of the envelope vary circumferentially (T(A)) and radially (R(A)). The matrix may be used with a heat exchanger.

Abstract: A heat exchanger includes a plurality of fins arranged as a network and delimiting corridors, and an envelope having an internal wall and an external wall, the internal and external walls delimiting between them a channel for a flow of a first fluid in a main direction, the network of fins being arranged in the channel and connected to the internal and external walls, at least one passage for a flow of a second fluid being embedded in at least one of the internal and external walls, the channel being, in the main direction, divergent and then convergent.

Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.

Abstract: An assembly for the compressor stator of a turbomachine. The assembly comprises: a shroud, in various instances an inner shroud, that is axially divided into two parts; a pocket formed in the shroud; a bearing located in the pocket; and an orientable vane pivotably mounted in the bearing about a pivot axis. The shroud comprises an axial interface separating the parts that is axially offset from the pivot axis of the orientable vane. The invention also provides a process for assembling the assembly.