Abstract: A cooling device (11) for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet (14) and one radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16). Each channel (17) includes at least one air inlet and air ejection orifices (19), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct (21) intended for the circulation of cooling air, the duct (21) located radially outside said metal sheets (14, 15) and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (21), the cooling duct (21) extending axially and arranged toward the circumferential end regions of the channels (17).

Abstract: A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.

Abstract: The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the casing (18), at least one cooling tube (23) extending circumferentially, at least one attachment member (25) comprising a radially inner portion (36) at least partially surrounding the tube (23), and a radially outer portion (37) attached to the support (24), the radially outer portion (37) of the attachment member (25) being attached to the support (24) through connecting means (30) formed by L-shaped sheets.

Abstract: Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (25), comprising a radially inner portion (36) at least partially surrounding the tube, and a radially outer portion (37) secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the support (24) via the intermediary of a connection member (30) comprising a central portion (31) having a circumferential end portion (32) and a second circumferential end portion (32) which are circumferentially opposite, the first end portion (32) and the second end portion (32) each extending in an opposite axial direction, the first and second end portions (32, 32) each being secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the central portion (31) of th

Abstract: The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the timer (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inter platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).

Abstract: The invention relates to a turbomachine assembly comprising: —a casing comprising: —an internal hub (10), —an external ferrule (20) extending around and at a distance from the internal hub (10), —a hollow arm (30), provided with a longitudinal cavity (40) and connecting the internal hub (10) and the external ferrule (20), —a tube (50) configured to extend in the interior of the longitudinal cavity (40) of the hollow arm (30) of the casing and comprising a central support (60) comprising two elastic blades (61) and configured to exert a pressure on the wall (42) of the longitudinal cavity (40) when the tube (50) is extended in the interior of the longitudinal cavity (40); characterized in that the material(s) of the elastic blades (61) is (are) such that said elastic blades (61) have a stress curve between the minimum and maximum stress curves of table A.

Abstract: The invention relates to a cooling device (11) for a turbine of a turbomachine extending along an axis, comprising at least one radially inner metal sheet (14) and one radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16), each channel (17) comprising at least one air inlet and air ejection orifices (19), that are designed to be oriented toward a region that is to be cooled, characterized in that it comprises means for cooling said metal sheets comprising at least one cooling duct (21) intended for the circulation of cooling air, said duct (21) being located radially outside said metal sheets (14, 15) and close to or in contact with said metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (21), the cooling duct (21) extending axially and being arranged toward the circumferential end regions of the channels (17).

Abstract: The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the casing (18), at least one cooling tube (23) extending circumferentially, at least one attachment member (25) comprising a radially inner portion (36) at least partially surrounding the tube (23), and a radially outer portion (37) attached to the support (24), the radially outer portion (37) of the attachment member (25) being attached to the support (24) through connecting means (30) formed by L-shaped sheets.

Abstract: Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (25), comprising a radially inner portion (36) at least partially surrounding the tube, and a radially outer portion (37) secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the support (24) via the intermediary of a connection member (30) comprising a central portion (31) having a circumferential end portion (32) and a second circumferential end portion (32) which are circumferentially opposite, the first end portion (32) and the second end portion (32) each extending in an opposite axial direction, the first and second end portions (32, 32) each being secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the central portion (31) of th

Abstract: The invention relates to a turbomachine assembly comprising: —a casing comprising: —an internal hub (10), —an external ferrule (20) extending around and at a distance from the internal hub (10), —a hollow arm (30), provided with a longitudinal cavity (40) and connecting the internal hub (10) and the external ferrule (20), —a tube (50) configured to extend in the interior of the longitudinal cavity (40) of the hollow arm (30) of the casing and comprising a central support (60) comprising two elastic blades (61) and configured to exert a pressure on the wall (42) of the longitudinal cavity (40) when the tube (50) is extended in the interior of the longitudinal cavity (40); characterized in that the material(s) of the elastic blades (61) is (are) such that said elastic blades (61) have a stress curve between the minimum and maximum stress curves of table A.

Abstract: The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the timer (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inter platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).

Abstract: A support system (16) for a structural casing of a turbomachine (10), which comprises: a handling fitting (17) comprising a front edge (19) provided with one or more hole(s) (26) for receiving one or more screw(s) (24) for attachment to a flange (23) formed on the casing (10), a rear edge (20) provided with a cavity (32) for receiving a projecting boss (29) formed on the casing (10); a pair of jaws (31) for gripping the boss (29), that are mounted in the cavity (32); at least one screw (33) for adjusting the position of the jaws (31), mounted on the fitting (17) and engaging with at least one jaw (31).

Abstract: The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).

Abstract: A support system (16) for a structural casing of a turbomachine (10), which comprises: a handling fitting (17) comprising a front edge (19) provided with one or more hole(s) (26) for receiving one or more screw(s) (24) for attachment to a flange (23) formed on the casing (10), a rear edge (20) provided with a cavity (32) for receiving a projecting boss (29) formed on the casing (10); a pair of jaws (31) for gripping the boss (29), that are mounted in the cavity (32); at least one screw (33) for adjusting the position of the jaws (31), mounted on the fitting (17) and engaging with at least one jaw (31).

Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.

Abstract: A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube.

Abstract: The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract: A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.

Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.