Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: A sealing device for an enclosure of a turbine engine formed by an assembly of juxtaposed rotating and/or static bodies is provided. The sealing device includes at least one brush seal having a brush body, carried by at least one first member, and bristles extending from the brush body and arranged so as to rub against at least one second member rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure and its outer environment. The device further includes a labyrinth-type seal, the labyrinth being positioned in series with the brush seal between the inside of the enclosure and its outer environment.

Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterised in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Abstract: Sealing device for an enclosure (E1, E2) of a turbine engine (1) formed by an assembly of juxtaposed rotating and/or static bodies, the sealing device comprising at least one brush seal (10) having a brush body (101), carried by at least one first member (11), and bristles (102) extending from said brush body and arranged so as to rub against at least one second member (12) rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure and its outer environment (E3), characterised in that said device further comprises a labyrinth-type seal (6), said labyrinth being positioned in series with said brush seal between the inside of said enclosure and its outer environment.

Abstract: A casing for a turbomachine rotor wheel includes a plurality of circumferential grooves, each of substantially constant section, with the section areas of the circumferential grooves decreasing from upstream to downstream on going from the first groove to the last groove. By treating the casing in this way, the efficiency of the rotor wheel is optimized and its surge margin is improved.

Abstract: A system for ventilating a downstream cavity of an impeller of a centrifugal compressor in a turbomachine, this cavity being delimited by the downstream face of the impeller and by an annular end-piece of a diffuser and being ventilated by taking air from the outlet of the compressor, the system comprising at least one annular deflector mounted in this cavity in order to oppose the rise of hot air along the downstream face of the impeller and in order to cause the diverted hot air to be driven by the air taken from the outlet of the compressor.

Abstract: A turbomachine compressor, including an air bleed device including a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor is disclosed. A screen sheet of annular shape is mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor.

Abstract: The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (22), an inner casing (21) and at least one shock absorbing ring (5) connecting the casings, the module also comprising an annular cavity (43) on the downstream side of the ring (5), with a passage (42) formed in it through which an airflow (4) is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (5), downstream from it, this device comprising at least one coat of thermal insulation (8), and at least partly delimiting the annular cavity (43) on the downstream side of it (43).

Abstract: System for cooling a downstream cavity of a centrifugal compressor impeller in a turbomachine, this compressor being connected to a diffuser comprising a downstream annular flange, an annular plating being mounted coaxially around the flange of the diffuser and substantially extending over the entire axial dimension of the flange so as to define an annular ventilation passage fed with air which is cooler than the air exiting the centrifugal compressor.

Abstract: A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system including flow diversion system mounted fixedly in the downstream cavity of the impellor in order to divert the ventilation air taken from the outlet of the compressor and cause it to circulate radially from the inside to the outside along the downstream face of the impellor.

Abstract: A system for cooling the impeller of a centrifugal compressor in a turbomachine is disclosed. The compressor supplies an annular diffuser. The diffuser includes an end-piece that extends downstream and along the impeller of the compressor and is covered on the upstream side by an annular metal sheet. The sheet delimits, with the impeller of the compressor, a first annular passageway to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway to carry away a portion of the air flow coming out of the diffuser.

Abstract: A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a centrifugal compressor, a diffuser, a combustion chamber, and an annular case arranged radially between the combustion chamber and a downstream end-piece of the diffuser. The annular case includes a radially external wall for the guidance of an air flow coming out of the diffuser, and a radially internal wall delimiting with the end-piece of the diffuser a channel for the air coming out of the diffuser to pass through.

Abstract: A casing for a turbomachine rotor wheel includes a plurality of circumferential grooves, each of substantially constant section, with the section areas of the circumferential grooves decreasing from upstream to downstream on going from the first groove to the last groove. By treating the casing in this way, the efficiency of the rotor wheel is optimized and its surge margin is improved.

Abstract: A system for ventilating a downstream cavity of an impeller of a centrifugal compressor in a turbomachine, this cavity being delimited by the downstream face of the impeller and by an annular end-piece of a diffuser and being ventilated by taking air from the outlet of the compressor, the system comprising at least one annular deflector mounted in this cavity in order to oppose the rise of hot air along the downstream face of the impeller and in order to cause the diverted hot air to be driven by the air taken from the outlet of the compressor.

Abstract: A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system comprising flow diversion means (70, 84) mounted fixedly in the downstream cavity (38) of the impellor (36) in order to divert the ventilation air taken from the outlet of the compressor (10) and cause it to circulate radially from the inside to the outside along the downstream face (34) of the impellor.

Abstract: The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (22), an inner casing (21) and at least one shock absorbing ring (5) connecting the casings, the module also comprising an annular cavity (43) on the downstream side of the ring (5), with a passage (42) formed in it through which an airflow (4) is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (5), downstream from it, this device comprising at least one coat of thermal insulation (8), and at least partly delimiting the annular cavity (43) on the downstream side of it (43).

Abstract: A turbomachine compressor, such as a high-pressure compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor, a screen sheet of annular shape being mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor.

Abstract: System for ventilating a combustion chamber wall A system for ventilating a combustion chamber wall in a turbomachine comprising a centrifugal compressor (10) supplying, via a diffuser (12), a combustion chamber (14), this system comprising an annular case (90) arranged radially between the combustion chamber and a downstream end-piece (26) of the diffuser and that comprises a radially external wall (92) for the guidance of an air flow coming out of the diffuser, and a radially internal wall (94) delimiting with the end-piece of the diffuser a channel (88) for the air coming out of the diffuser to pass through.

Abstract: A system for cooling the impeller of a centrifugal compressor in a turbomachine, this compressor (10) supplying an annular diffuser (12) comprising an end-piece (26) that extends downstream and along the impeller of the compressor and that is covered on the upstream side by an annular metal sheet (90) that delimits, with the impeller of the compressor, a first annular passageway (39) to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway (98) to carry away a portion of the air flow coming out of the diffuser.

Abstract: System for cooling a downstream cavity of a centrifugal compressor impeller in a turbomachine, this compressor (10) being connected to a diffuser (12) comprising a downstream annular flange, an annular plating (70) being mounted coaxially around the flange of the diffuser and substantially extending over the entire axial dimension of the flange so as to define an annular ventilation passage (72) fed with air which is cooler than the air (61) exiting the centrifugal compressor.