Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).

Abstract: A turbine wheel for a turbine engine is provided. The turbine wheel includes a disk carrying blades including internal channels for passing a flow of cooling air, each blade having a platform carrying an airfoil and connected by a tang to a root. The blade roots are engaged in grooves in the periphery of the disk and their tangs define between them spaces for housing sealing and damping members, which cooperate with the inside faces of the platforms to define air flow cavities. The tangs of at least some of the blades include cooling air outlet orifices that open out both into internal channels in the blades and into the cavities.

Abstract: A cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in the region of the distal end of the blade at least one external cavity forming a bathtub-shaped cavity and at least one internal cavity separated by the distal wall, the blade having at least one opening for the introduction of a flow of cooling air into the external cavity, wherein, on the one hand, at least one part of the distal wall is inclined relative to the verticals of the pressure surface wall and, on the other hand, the opening is created in the vicinity of the distal wall so that the flow of cooling air is directed towards the distal end of the pressure surface wall.

Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).

Abstract: Bleeding cooling air to cool a subassembly, e.g. such as a turbine, with automatic adjustment of the air flow section as a function of the speed of the engine. According to the invention, a shutter element is fastened to co-operate with a bleed hole, with the material that constitutes either the shutter element or the wall in which the hole is formed being of a type in which it is possible to create eddy currents, and a magnet is mounted to move past said arrangement.

Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.

Abstract: A turbine ring sector comprising a wall presenting an inside face and an outside face, in which the inside face defines an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage is disclosed. The multiply-perforated metal sheet has a bottom, and the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap. The variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value and then increases from the minimum value to a second maximum value.

Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.

Abstract: A turbine stage for a turbine engine includes a bladed wheel rotatable inside a sectorized ring of composite material carried by a casing. Each ring sector has a downstream circumferential rim held to bear radially against an annular tab that is engaged radially in an annular groove of the downstream circumferential rim of the ring with axial clearance, when cold, that is designed to be reduced to zero in operation when hot, and to enable the annular tab of the casing to be clamped axially in leaktight manner in the annular groove of the ring sector.

Abstract: Bleeding cooling air to cool a subassembly, e.g. such as a turbine, with automatic adjustment of the air flow section as a function of the speed of the engine. According to the invention, a shutter element is fastened to co-operate with a bleed hole, with the material that constitutes either the shutter element or the wall in which the hole is formed being of a type in which it is possible to create eddy currents, and a magnet is mounted to move past said arrangement.

Abstract: The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises: a plurality of segments assembled by means of sealed connection involving sealing strips, provided in the mutually-facing radial faces of said segments the internal lateral faces of which delimit the flow path along which the hot gaseous flow travels; and through-orifices, formed in said segments, to carry external fresh air towards their radial and internal faces. Advantageously, one, the lower one, of the sealing strips of the means of connection is designed to lie close to the lateral internal faces of said segments and to run parallel to them, passing through a cooling chamber formed in the radial faces of the segments and into which said orifices open.

Abstract: A turbine ring sector comprising: a wall presenting an inside face and an outside face, the inside face defining an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage, said multiply-perforated metal sheet having a bottom; wherein the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap; and wherein the variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value, said minimum value defining the minimum of the gap, and then increases from the minimum value to a second maximum value.