Abstract: A turbine engine including a controller controlling clearance between tips of moving blades of a high-pressure turbine and an outer casing surrounding the blades, by cooling the outer casing by the impact of air taken from a high-pressure compressor stage of the engine, and by electric heating of top and bottom portions of the outer casing.

Abstract: An impeller for a turbine engine which includes a disk provided with blade retention teeth, wherein associated with each tooth there is a mechanism for channelling a flow of cooling air which covers the crest of the tooth so that the latter is swept by the air flow. A turbine of turbine engine which includes an impeller of this type, and a turbine engine for aircraft which includes a turbine of this type.

Abstract: A turbine stage in a turbomachine including ring sectors arranged about a turbine impeller, and an annular support supporting the ring sectors and attached to a turbine casing is disclosed. The annular support is able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

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: A turbine engine including a controller controlling clearance between tips of moving blades of a high-pressure turbine and an outer casing surrounding the blades, by cooling the outer casing by the impact of air taken from a high-pressure compressor stage of the engine, and by electric heating of top and bottom portions of the outer casing.

Abstract: A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract: A turbine stator of a gas turbine engine includes a turbine casing, a turbine shroud ring and a shroud ring support connecting the shroud ring to the casing. The stator is one wherein the support is provided with a heat shield positioned on the turbine side. This assembly makes it possible to reduce the take-up of play during transient operating phases.

Abstract: Impeller for turbine engine which includes a disk provided with blade retention teeth, wherein associated with each tooth there are means for channelling a flow of cooling air which covers the crest of said tooth so that the latter is swept by the air flow. Turbine of turbine engine which includes an impeller of this type. Turbine engine for aircraft which includes a turbine of this type.

Abstract: The turbine casing includes a circumferential wall coaxially surrounding a ring that surrounds the moving blades of the turbine. The casing includes a plurality of perforations delivering air for ventilating the outside face of the circumferential wall in uniform manner.

Abstract: High-pressure turbine of a turbomachine A high-pressure turbine (10) of a turbomachine, comprising at least one upstream guide vane element (16) and an impeller (18) mounted so as to rotate inside ring sectors (20) attached to an annular support (24) which is suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means of attachment to an inner casing and, at its radially outer end, means (102, 104) for pressing axially on a fixed element (90) of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract: A turbine stage in a turbomachine comprising ring sectors (20) arranged about a turbine impeller (18), and an annular support (50) supporting the ring sectors and attached to a turbine casing (22), this annular support being able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Abstract: The present invention relates to a turbine stator of a gas turbine engine comprising a turbine casing (9), a turbine shroud ring (13) and a shroud ring support (11) connecting the shroud ring (13) to the casing (9). The stator is one wherein the support (11) is provided with an element that forms a heat shield positioned on the turbine side. This solution makes it possible to reduce the take-up of play during transient operating phases.

Abstract: The turbine casing includes a circumferential wall coaxially surrounding a ring that surrounds the moving blades of the turbine. The casing includes a plurality of perforations delivering air for ventilating the outside face of the circumferential wall in uniform manner.