Sealing a rotor ring in a turbine stage
View Patent ↗A turbine stage in a turbomachine is disclosed. The stage includes a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.
1. A turbine stage of a turbomachine, the stage comprising a rotor wheel mounted inside a sectorized ring carried by a turbine casing, and a nozzle situated upstream from the wheel and made up of an annular row of stator vanes, the nozzle including at its downstream end an outer annular rim having fastener means for fastening to the turbine casing, sealing means being provided between the outer rim of the nozzle and the upstream end of the ring to limit the passage of gas in a radial direction between the outer rim of the nozzle and the ring, the stage being characterized in that the sealing means comprise an annular sheet extending substantially radially between the outer rim of the nozzle and the upstream end of the ring, and comprising at its inner periphery and at its outer periphery means for bearing axially against a downstream face of the outer rim of the nozzle, the middle annular portion of said sheet being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring, the sheet being elastically prestressed in the axial direction by the upstream end of the ring.
2. A turbine stage according to claim 1 , wherein the sheet is fastened to the outer rim of the nozzle.
3. A turbine stage according to claim 1 , wherein the sheet is fastened via its inner periphery to a radially inner end portion of the outer rim of the nozzle.
4. A turbine stage according to claim 1 , wherein the sheet is substantially plane and, in the assembled position, is pressed against the downstream face of the outer rim of the nozzle, covering an annular groove in the downstream face of the outer rim.
5. A turbine stage according to claim 1 , wherein the sheet comprises an annular portion of U-shaped or V-shaped section with its opening facing upstream, said annular portion bearing axially against the upstream end of the ring and co-operating with the downstream face of the outer rim of the nozzle to define an annular space.
6. A turbine stage according to claim 1 , wherein the sealing sheet is made up of sheet sectors, each fastened to a nozzle sector.
7. A turbine stage according to claim 1 , wherein the sheet is made of metal.
8. A turbomachine such as an airplane turbojet or turboprop, comprising at least one turbine stage according to claim 1 .