US 12,345,161 B2
High-pressure gas turbine for a turbine engine and turbine engine
Francesco Salvatori, Moissy-Cramayel (FR); Damien Bonneau, Moissy-Cramayel (FR); Nicolas Contini, Moissy-Cramayel (FR); Clément Jarrossay, Moissy-Cramayel (FR); and Pascal Cédric Tabarin, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/694,563
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Sep. 2, 2022, PCT No. PCT/FR2022/051663
§ 371(c)(1), (2) Date Mar. 22, 2024,
PCT Pub. No. WO2023/047034, PCT Pub. Date Mar. 30, 2023.
Claims priority of application No. 2110133 (FR), filed on Sep. 27, 2021.
Prior Publication US 2024/0392692 A1, Nov. 28, 2024
Int. Cl. F01D 11/04 (2006.01); F01D 11/00 (2006.01); F01D 11/02 (2006.01)
CPC F01D 11/04 (2013.01) [F01D 11/001 (2013.01); F01D 11/02 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2240/55 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A high-pressure gas turbine for a turbomachine (10) extending around a longitudinal axis (X), the turbine comprising:
a nozzle guide vane assembly (30) comprising an internal annular platform (34) and an annular array of fixed vanes (32), each fixed vane (32) being connected, radially inwards, to the internal annular platform (34),
an annular array of movable blades (40) mounted downstream of the nozzle guide vane assembly (30), comprising a disc (41) from which blades (42) extend radially outwards,
an upstream sealing element (50) applied against a downstream face of the nozzle guide vane assembly (30), and a downstream sealing element (43) applied against an upstream face of the disc (41) of the annular array of movable blades (40),
the downstream sealing element (43) comprising an upstream deflector (47) arranged, at least in part, radially internally to the internal annular platform (34) of the nozzle guide vane assembly (30),
the upstream sealing element (50) comprising a first downstream deflector (54) arranged, in whole or in part, radially internally to the upstream deflector (47) of the downstream sealing element (43), the first downstream deflector (54) forming a radially outward projection from the upstream sealing element (50), a radially external end (55) of said first downstream deflector (54) being arranged radially facing said upstream deflector (47), thus forming a first annular recirculation cavity (60) which is delimited, longitudinally, by the nozzle guide vane assembly (30) and the first downstream deflector (54),
the upstream sealing element (50) comprising a second downstream deflector (58) forming a projection in the downstream direction, the second downstream deflector (58) being arranged radially internally to the first downstream deflector (54), the downstream sealing element (43) comprising an upstream face extending radially and without any deflector interposed radially between said first downstream deflector (54) and said second downstream deflector (58) of the upstream sealing element (50), thus forming a second annular recirculation cavity (64) which is delimited by said first downstream deflector (54) and said second downstream deflector (58) of the upstream sealing element (50) and by the upstream face of the downstream sealing element (43),
an annular bleed cavity (62) being delimited between the nozzle guide vane assembly (30) and the annular array of movable blades (40) and located radially internally to the second annular recirculation cavity (64),
a stream of bleed air or a stream of gas being able to flow: between an annular path (11) located radially externally to the internal platform (34) of the nozzle guide vane assembly (30) and the first annular recirculation cavity (60), through a clearance between the internal platform (34) and the upstream deflector (47); between the first annular recirculation cavity (60) and the second annular recirculation cavity (64), through a clearance between the first downstream deflector (54) and the upstream deflector (47); and between the second annular recirculation cavity (64) and the bleed cavity (62), through a clearance between the second downstream deflector (58) and the downstream sealing element (43).