Abstract: A turbomachine comprising: a gas generator for producing combustion gas; a turbine section through which the combustion gas passes and comprising first and second rows of contrarotating turbine rotor blades respectively driving first and second low-pressure shafts in rotation; and a fan section comprising a first row of fan blades mounted on a front fan shaft that is connected to an upstream end of the first low-pressure shaft, and a second row of fan blades axially offset from the first row and mounted on a rear fan shaft that is connected to an upstream end of the second low-pressure shaft, the front fan shaft being connected to the upstream end of the first low-pressure shaft via a removable sleeve for transmitting torque.

Abstract: A turbomachine comprising: a gas generator for producing combustion gas; a turbine section through which the combustion gas passes and comprising first and second rows of contrarotating turbine rotor blades respectively driving first and second low-pressure shafts in rotation; and a fan section comprising a first row of fan blades mounted on a front fan shaft that is connected to an upstream end of the first low-pressure shaft, and a second row of fan blades axially offset from the first row and mounted on a rear fan shaft that is connected to an upstream end of the second low-pressure shaft, the front fan shaft being connected to the upstream end of the first low-pressure shaft via a removable sleeve for transmitting torque.

Abstract: A turboshaft engine, such as for example a turbine, including a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring of sectors of vanes and includes a plurality of flexible segments having a straight deformation zone and a straight fluid-tight bearing zone.

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: A turbomachine includes a casing, a rotor, and a plurality of cooled ring segments installed between the casing and the rotor, each ring segment containing a main cooling cavity and being attached to the casing by a fastening device. The fastening device can include a clamping screw positioned more or less radially and pinning the ring segment against the casing. The clamping screw is crossed through by a cooling airway that communicates with the main cooling cavity of the ring segment.

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: A ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream and downstream turbine disks fitted with blades, the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combustion chamber. The circuit is such that the airflow passes through orifices formed in an upstream flange of the upstream disk, such that this airflow circulates in the axial direction towards the downstream side between an inner reaming of the upstream disk and a downstream flange of the downstream disk, the device also comprising a labyrinth inserted between the two disks, such that the airflow is divided into a first flow F1 and a second flow circulating on each side of labyrinth towards the blades.

Abstract: Turboshaft engine, such as for example a turbine, comprising a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring of sectors of vanes and consists of a plurality of flexible segments having a straight deformation zone and a straight fluid-tight bearing zone.

Abstract: The invention relates to ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream (3) and downstream (5) turbine disks fitted with blades (4, 6), the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combustion chamber. According to the invention, the circuit is such that the airflow passes through orifices (74) formed in an upstream flange (66) of the upstream disk, such that this airflow circulates in the axial direction towards the downstream side between an inner reaming (48) of the upstream disk and a downstream flange (78) of the downstream disk, the device also comprising a labyrinth (80) inserted between the two disks, such that the airflow is divided into a first flow F1 and a second flow F2 circulating on each side of the labyrinth towards the blades (4, 6).

Abstract: The invention concerns a turbomachine (100) comprising a casing (102), a rotor (4), and a plurality of cooled ring segments (108) installed between the casing and the rotor, each ring segment containing a main cooling cavity (162) and being attached to the casing by means of a fastening device (132). According to the invention, the fastening device (132) comprises a clamping screw (134) positioned more or less radially and pinning the ring segment against the casing. The clamping screw (134) is crossed through by a cooling airway (174) that communicates with the main cooling cavity (162) of the ring segment.

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 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: Layout for adjusting the diameter of a turbine engine ring (5) positioned facing mobile rotor blades (4) and connected to a case element (7). The latter is provided with a cavity (16) communicating with chambers (21, 23) around a gas flow stream (31). A limited air current traverses the cavity (16) and is sufficiently reduced to ensure the development of a heat convection, which renders uniform the temperature of the case element (7) and the ring (5) and consequently the diameter of the latter.

Abstract: A labyrinth disk includes a main stiffener placed in the middle of the rim immediately below labyrinth elements. Attachment elements are preferably in the form of a bayonet attachment system using teeth fixed on the labyrinth disk crown and teeth fixed on the rotor. Attachment by bolting may optionally be used. The disk may be utilized with turbojets, on the cooling circuit, on the upstream side of the high pressure turbine.