High-pressure gas turbine for a turbomachine extending around a longitudinal axis, the turbine comprising: - a nozzle guide vane assembly comprising an internal annular platform and an annular array of fixed vanes, each fixed vane being connected, radially inwards, to the internal annular platform, - an annular array of movable blades mounted downstream of the nozzle guide vane assembly, comprising a disc from which blades extend radially outwards, - an upstream sealing element applied against a downstream face of the nozzle guide vane assembly, and a downstream sealing element applied against an upstream face of the disc of the annular array of movable blades, the downstream sealing element comprising an upstream deflector arranged, at least in part, radially internally to the internal annular platform of the nozzle guide vane assembly, the upstream sealing element comprising a first downstream deflector arranged, in whole or in part, radially internally to the upstream deflector of the upstream sealing element, the first downstream deflector forming a radially outward projection from the sealing element, a radially external end of said first downstream deflector being arranged radially facing said upstream deflector, thus forming a first annular recirculation cavity which is delimited, longitudinally, by the nozzle guide vane assembly and the first downstream deflector, the upstream sealing element comprising a second downstream deflector forming a projection in the downstream direction, the second downstream deflector being arranged radially internally to the first downstream deflector, the downstream sealing element comprising an upstream face extending radially and without any deflector interposed radially between said first downstream deflector and said second downstream deflector of the upstream sealing element, thus forming a second annular recirculation cavity which is delimited by said first downstream deflector and said second downstream deflector of the upstream sealing element and by the upstream face of the downstream sealing element, an annular bleed cavity being delimited between the nozzle guide vane assembly and the annular array of movable blades and located radially internally to the second annular recirculation cavity, a stream of bleed air or a stream of gas being able to flow: between an annular path located radially externally to the internal platform of the nozzle guide vane assembly and the first annular circulation cavity, through a clearance between the internal platform and the upstream deflector; between the first recirculation cavity and the second recirculation cavity, through a clearance between the first downstream deflector and the upstream deflector; and between the second recirculation cavity and the bleed cavity, through a clearance between the second downstream deflector and the downstream sealing element. - a nozzle guide vane assembly comprising an internal annular platform and an annular array of fixed vanes, each fixed vane being connected, radially inwards, to the internal annular platform, - an annular array of movable blades mounted downstream of the nozzle guide vane assembly, comprising a disc from which blades extend radially outwards, - an upstream sealing element applied against a downstream face of the nozzle guide vane assembly, and a downstream sealing element applied against an upstream face of the disc of the annular array of movable blades, the downstream sealing element comprising an upstream deflector arranged, at least in part, radially internally to the internal annular platform of the nozzle guide vane assembly, the upstream sealing element comprising a first downstream deflector arranged, in whole or in part, radially internally to the upstream deflector of the upstream sealing element, the first downstream deflector forming a radially outward projection from the sealing element, a radially external end of said first downstream deflector being arranged radially facing said upstream deflector, thus forming a first annular recirculation cavity which is delimited, longitudinally, by the nozzle guide vane assembly and the first downstream deflector, the upstream sealing element comprising a second downstream deflector forming a projection in the downstream direction, the second downstream deflector being arranged radially internally to the first downstream deflector, the downstream sealing element comprising an upstream face extending radially and without any deflector interposed radially between said first downstream deflector and said second downstream deflector of the upstream sealing element, thus forming a second annular recirculation cavity which is delimited by said first downstream deflector and said second downstream deflector of the upstream sealing element and by the upstream face of the downstream sealing element, an annular bleed cavity being delimited between the nozzle guide vane assembly and the annular array of movable blades and located radially internally to the second annular recirculation cavity, a stream of bleed air or a stream of gas being able to flow: between an annular path located radially externally to the internal platform of the nozzle guide vane assembly and the first annular circulation cavity, through a clearance between the internal platform and the upstream deflector; between the first recirculation cavity and the second recirculation cavity, through a clearance between the first downstream deflector and the upstream deflector; and between the second recirculation cavity and the bleed cavity, through a clearance between the second downstream deflector and the downstream sealing element.