Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.

Abstract: A turbomachine including a high pressure compressor with a downstream cone, a diffuser extending downstream by an inner casing disposed radially outside the downstream compressor cone, a combustion chamber disposed radially outside the inner diffuser casing, and a high pressure turbine whose rotor is connected to the downstream cone of the compressor by a connection drum, the inner diffuser casing and the downstream compressor cone defining between them an under-chamber cavity that is situated downstream from a discharge labyrinth in which cooling air flows downstream, wherein the engine also includes a stator shroud that is installed under the inner diffuser casing downstream from the discharge labyrinth.

Abstract: The invention relates to a blade for a turbine, the blade being fitted with a dovetail root to fix it into a compartment of a turbine disk, the blade being fitted with an internal air cooling circuit comprising air inlets located on the blade dovetail root and facing the compartment, and air outlets. The blade dovetail root is fitted with a device capable of homogenising the pressure and temperature of cooling air entering the air inlets.

Abstract: A ventilation circuit of a turbomachine turbine rotor having a turbine disk and an upstream flange disposed upstream from a combustion chamber from which it is spaced apart by a cavity. A first cooling air circuit delivers air into the cavity via main injectors and holes in the flange. A second cooling air circuit delivers air through enclosures delimited by the combustion chamber inner casing and the rotor via a discharge labyrinth, an under-injector labyrinth, and at least one labyrinth downstream from the main injectors between an annular structure and the flange. Three single-wiper labyrinths delimiting two cavities upstream from the venting cavity of the turbine disk are provided downstream from the main injectors. One of the cavities is fed with air from the second circuit upstream from the under-injector labyrinth by bore holes in the annular structure sloping tangentially in the rotation direction of the rotor.

Abstract: The invention relates to a turbomachine of axis X and comprising, from upstream to downstream, a high pressure compressor whose rotor presents a downstream cone (4), a diffuser (3) extending downstream beside the axis X by an inner casing (5) disposed radially outside said downstream compressor cone, a combustion chamber disposed radially outside said inner diffuser casing, and a high pressure turbine whose rotor is connected to the downstream cone of the compressor by a connection drum, the inner diffuser casing and the downstream compressor cone defining between them an under-chamber cavity that is situated downstream from a discharge labyrinth (13) in which cooling air flows downstream, the turbomachine being characterized in that it also comprises a stator shroud (20) that is installed under the inner diffuser casing (5) downstream from the discharge labyrinth (13).

Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.

Abstract: The invention relates to a device for ventilating a high pressure turbine rotor which comprises a turbine disk and an upstream end plate. A first circuit for cooling blades delivers a first air flow via main injectors and holes formed in the end plate. A second cooling circuit delivers a second air flow through a discharge baffle situated downstream from the compressor, a fraction of this second flow serving to cool the upstream top face of the end plate through a second baffle situated beneath the main injectors. A branch connection is provided between the first circuit and the enclosure situated downstream from the second baffle and it delivers a third flow which is set into pre-rotation by additional injector means formed in the form of inclined bores.

Abstract: The invention relates to a blade (11) for a turbine, the blade being fitted with a dovetail root (13) to fix it into a compartment (14) of a turbine disk (12), the blade being fitted with an internal air cooling circuit comprising air inlet means (15) located on the blade dovetail root and facing the compartment, and air outlet means. The blade dovetail root (13) is fitted with means (20) capable of homogenising the pressure and temperature of cooling air entering the air inlet means.

Abstract: The invention relates to a device for ventilating a high pressure turbine rotor which comprises a turbine disk and an upstream end plate. A first circuit for cooling blades delivers a first air flow via main injectors and holes formed in the end plate. A second cooling circuit delivers a second air flow through a discharge baffle situated downstream from the compressor, a fraction of this second flow serving to cool the upstream top face of the end plate through a second baffle situated beneath the main injectors. A branch connection is provided between the first circuit and the enclosure situated downstream from the second baffle and it delivers a third flow which is set into pre-rotation by additional injector means formed in the form of inclined bores.

Abstract: A joint between a turbine ring. The ring is jointed to a spacer of the turbine by a joint including hooks which fit together on one side, and an abutment of flanges as well as a mortise and tenon joint on the other side. According to the joint, the tenon and mortise are separated from the flanges in abutment to limit the plays in the axial direction, produced by design or by expansions, to increase mechanical strength and simplify manufacturing.