Abstract: A turbine for a turbomachine includes an annular row (20) of moving blades (20a) surrounded by a support ring (26) of abradable material (24) carried by a housing (10). The turbine also includes a distributor (30) mounted downstream of the moving blades (20a) and having an attachment mechanism with a radially outer spoiler (38) coming to bear radially inwards on a cylindrical wall (12) connected to housing (10). An annular wall (14) extends radially inwards from the cylindrical wall (12) and engages at its radially inner end in an annular groove (28) of the support ring (26), and in which a free annular space (40) is formed between a radially outer face (26b) of the ring (26) and the cylindrical wall (12).

Abstract: An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.

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: An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.

Abstract: A turbine for a turbomachine comprising an annular row (20) of moving blades (20a) surrounded by a support ring (26) of abradable material (24) carried by a housing (10) and a distributor (30) mounted downstream of said annular row (20) of moving blades (20a) and comprising a means of attachment to a means of support of the housing (10), the said means of attachment comprising a radially outer spoiler (38) coming to bear radially inwards on a cylindrical wall (12) of said means of support, the said means of support further comprising an annular wall (14) extending radially inwards from the cylindrical wall (12) and engaged at its radially inner end in an annular groove (28) of the ring (26), and in which a free annular space (40) is formed between a radially outer face (26b) of the ring (26) and the cylindrical wall (12) of the means of support.

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).