Abstract: A method for transporting a turbine engine held by a transport kit by a carriage. The transport kit connected to a connection member hoists the engine to connect to an aircraft fuselage. The transport kit is a structure which includes a hoisting interface (328) arranged on a rigid hoisting arm (318) which extends over the turbine engine and is connected to a rigid transport arm (316) which extends over a lateral side of the turbine engine. The transport arm is connected to at least two engine mounts (340) solid with the turbine engine. The transport arm (316), or one of the engine mounts connected to the transport arm, includes a transport interface (324) that can be supported by a bearing element (332) of a truck (326) used for transporting the turbine engine.

Abstract: The invention relates to an assembly for the removal, transportation and maintenance of an aircraft turbine engine (10) on a maintenance trolley (34), comprising a turbine engine (10) comprising an upper means (14) for attaching the housing (16) of the turbine engine (10) to the aircraft and a first lower means (20) dedicated to transportation for attaching the housing (16) of the turbine engine (10), a maintenance trolley (34), and a member (32) comprising a means for attaching said member (34) to the housing (16) and at least one means for support and articulation of said member (32) and of the turbine engine (10) on the trolley (34), allowing the turbine engine (10) to pivot to the vertical; characterised in that the member comprises a first attachment means designed to engage with the upper means (14), a second attachment means designed to engage with the first lower means (20), and a pivot means forming the support and articulation means engaging with a complementary receiving means (44) of the trolley (

Abstract: The invention relates to an assembly for the removal, transportation and maintenance of an aircraft turbine engine (10) on a maintenance trolley (34), comprising a turbine engine (10) comprising an upper means (14) for attaching the housing (16) of the turbine engine (10) to the aircraft and a first lower means (20) dedicated to transportation for attaching the housing (16) of the turbine engine (10), a maintenance trolley (34), and a member (32) comprising a means for attaching said member (34) to the housing (16) and at least one means for support and articulation of said member (32) and of the turbine engine (10) on the trolley (34), allowing the turbine engine (10) to pivot to the vertical; characterised in that the member comprises a first attachment means designed to engage with the upper means (14), a second attachment means designed to engage with the first lower means (20), and a pivot means forming the support and articulation means engaging with a complementary receiving means (44) of the trolle

Abstract: Structure (310) for transporting and hoisting a turbomachine (312), said structure comprising a hoisting interface (328) arranged on a rigid hoisting arm (318) which extends over the turbomachine and is connected to a rigid transport arm (316) which extends over a lateral side of the turbomachine, this transport arm being connected to at least two engine mounts (340) solid with the turbomachine. The transport arm (316), or one of the engine mounts connected to this transport arm, comprises a transport interface (324) that can be supported by a bearing element (332) of a truck (326) used for transporting the turbomachine.

Abstract: A layout for cooling a blade having a cavity surrounded by an internal wall including cooling fins which are spaced apart from each other by a pitch (p) and each have a thickness (e). The blade has, inside the cavity, a jacket passed through by emission holes each having a diameter (d). When the jacket is in place in the cavity of the blade, and in respect of the critical operating point of the turbine engine, each emission hole of the jacket is opposite a place on the internal wall of the blade which is located between cooling fins.

Abstract: A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, each tube including a bellows between its ends and accommodating relative displacements and changes of alignment between the orifices in the casing and the orifices in the nozzle.

Abstract: A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, one end of each tube being engaged in a ring having an outer collar movable in sliding between two surfaces carried by the nozzle, the guide surface situated beside the casing being held stationary relative to the nozzle, while the other guide surface is movable axially relative to the nozzle and is associated with return means urging it towards the casing.

Abstract: The present invention relates to a bladed stator for a turbo-engine, in particular a bladed stator sector comprising an inner platform (3) and an outer platform (4), at least one blade (2) fixed between said platforms (3, 4), at least one of said platforms (3, 4) comprising at least one flange (5, 6) having a first end (5a, 6a) fixed to the platform (3, 4) and a second, free end (5b, 6b), said flange (5, 6) comprising at least one non-opening free flexibility-increasing cutout (10).

Abstract: The layout for cooling a blade (10), said blade (10) having a cavity (12) surrounded by an internal wall (14) comprising cooling fins (24) which are spaced apart from each other by a pitch (p) and each have a thickness (e), said blade (10) having, inside said cavity (12), a jacket (26) passed through by emission holes (28) each having a diameter (d), is characterised in that, when the jacket (26) is in place in the cavity (12) of the blade (10), and in respect of the critical operating point of the turbine engine, each emission hole (28) of the jacket (26) is opposite a place on the internal wall (14) of the blade (10) which is located between cooling fins (24).

Abstract: A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, each tube including a bellows between its ends and accommodating relative displacements and changes of alignment between the orifices in the casing and the orifices in the nozzle.

Abstract: A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, one end of each tube being engaged in a ring having an outer collar movable in sliding between two surfaces carried by the nozzle, the guide surface situated beside the casing being held stationary relative to the nozzle, while the other guide surface is movable axially relative to the nozzle and is associated with return means urging it towards the casing.

Abstract: The invention relates to a part (110) of the distributor of the first stage of a turbojet low-pressure turbine. A part of this type comprises an outer platform segment (104) and an inner platform segment (102) between which a plurality of hollow blades (106), intended to be supplied with cooling air, extend, a cap (132) covering a base portion (138) of the outer platform segment (104) so as to define with this base portion a chamber (140), which communicates with the interior of said blades (106) via communication openings (130), air inlets (137) being provided in said cap (132) in order to allow said chamber (140) to be supplied with cooling air.