Abstract: A turbomachine casing (10) comprising an endoscopy port (12) and a member (14) mounted on and fixed to the casing and comprising a duct (16) that communicates with the port and that comprises an internal thread into which a cap (28) can be screwed, and means (22, 26) for fixing the member to the casing, characterised in that it further comprises a cover (30) mounted on the member and at least partially covering the fixing means in order to hinder, or indeed prevent, access to same when the cover is mounted on the member, the cover being arranged to allow free access to the duct when the cap is not screwed into the duct.

Abstract: A turbomachine element includes a stator, a rotor, and a first sealing means for sealing between the rotor and the stator. The element is arranged to be active when the rotor is in the operating position of same around the axis of rotation thereof. The element includes an auxiliary pressure sealing means, sealing between the rotor and the stator and is arranged so that the two sealing means are active when the rotor is placed along the axis of rotation thereof during an assembly operation in a test position. In the test position, the rotor and the stator form an enclosure between said two sealing means.

Abstract: A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to the shaft. An air guide is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide passes between the first seal and the shaft, the air guide being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.

Abstract: An extraction sleeve for extracting two rotationally symmetrical parts that are joined together by interference fit, the extraction sleeve including: a head having a conical part; a cylindrical body, the internal part of the cylindrical body having a screw thread suitable for the screwing of an extraction screw; the conical part of the head of the extraction sleeve forming a friction component suitable for coming into contact with one of the rotationally symmetrical parts, the friction component being designed so as to determine a limit slipping torque greater than the friction torque generated at the screw thread of the sleeve by screwing of the extraction screw.

Abstract: An extraction sleeve for extracting two rotationally symmetrical parts that are joined together by interference fit, the extraction sleeve including: a head having a conical part; a cylindrical body, the internal part of the cylindrical body having a screw thread suitable for the screwing of an extraction screw; the conical part of the head of the extraction sleeve forming a friction component suitable for coming into contact with one of the rotationally symmetrical parts, the friction component being designed so as to determine a limit slipping torque greater than the friction torque generated at the screw thread of the sleeve by screwing of the extraction screw.

Abstract: A turbomachine element includes a stator, a rotor, and a first sealing means for sealing between the rotor and the stator. The element is arranged to be active when the rotor is in the operating position of same around the axis of rotation thereof. The element includes an auxiliary pressure sealing means, sealing between the rotor and the stator and is arranged so that the two sealing means are active when the rotor is placed along the axis of rotation thereof during an assembly operation in a test position. In the test position, the rotor and the stator form an enclosure between said two sealing means.

Abstract: A device for preventing rotation of a segment of nozzle guide vanes assembly in a form of an annulus sector housed inside an annular casing of a turbo machine with interposing of a heat shield sheet between an internal wall of the casing and an external wall of the segment of nozzle guide vanes assembly, the device including a rotation-proofing peg fitted both into a notch formed in the segment of nozzle guide vanes assembly and in a housing formed in the casing, the heat shield sheet including a tab resting against the rotation-proofing peg. A surface portion radially between the tab and the internal wall of the casing forms an end stop in event of a possible radial movement of the heat shield sheet while the turbo machine is in operation.

Abstract: A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to said shaft. An air guide means is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide means passes between the first seal and the shaft, said guide means being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.

Abstract: A turbomachine casing (10) comprising an endoscopy port (12) and a member (14) mounted on and fixed to the casing and comprising a duct (16) that communicates with the port and that comprises an internal thread into which a cap (28) can be screwed, and means (22, 26) for fixing the member to the casing, characterised in that it further comprises a cover (30) mounted on the member and at least partially covering the fixing means in order to hinder, or indeed prevent, access to same when the cover is mounted on the member, the cover being arranged to allow free access to the duct when the cap is not screwed into the duct.

Abstract: A device for suspending a turbojet casing, the device including a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing. A protection piece for providing protection against wear is mounted on each lug of the clevis and has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes.

Abstract: A device for suspending a turbojet casing, the device including a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing. A protection piece for providing protection against wear is mounted on each lug of the clevis and has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes.

Abstract: A device for preventing rotation of a segment of nozzle guide vanes assembly in a form of an annulus sector housed inside an annular casing of a turbo machine with interposing of a heat shield sheet between an internal wall of the casing and an external wall of the segment of nozzle guide vanes assembly, the device including a rotation-proofing peg fitted both into a notch formed in the segment of nozzle guide vanes assembly and in a housing formed in the casing, the heat shield sheet including a tab resting against the rotation-proofing peg. A surface portion radially between the tab and the internal wall of the casing forms an end stop in event of a possible radial movement of the heat shield sheet while the turbo machine is in operation.

Abstract: External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors (120) positioned circumferentially end to end, and each comprising a circumferentially directed plate (136) bearing a block (138) of abradable material, the plate and the block of each ring sector being offset one with respect to the other in the circumferential direction so that a circumferential end part of the plate of each ring sector overlaps a corresponding end part of the block of an adjacent ring sector.

Abstract: External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors (120) positioned circumferentially end to end, and each comprising a circumferentially directed plate (136) bearing a block (138) of abradable material, the plate and the block of each ring sector being offset one with respect to the other in the circumferential direction so that a circumferential end part of the plate of each ring sector overlaps a corresponding end part of the block of an adjacent ring sector.

Abstract: A joint between a turbine ring. The ring is jointed to a spacer of the turbine by a joint including hooks which fit together on one side, and an abutment of flanges as well as a mortise and tenon joint on the other side. According to the joint, the tenon and mortise are separated from the flanges in abutment to limit the plays in the axial direction, produced by design or by expansions, to increase mechanical strength and simplify manufacturing.