Abstract: A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.

Abstract: A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.

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: 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 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.