Patent ID: 11879341
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbine for a turbine engine extending along an axis, including an annular casing and at least one turbine stage comprising a nozzle and a rotor impeller wheel surrounded by a sealing ring including an abradable element, the impeller wheel and the sealing ring being located downstream from the nozzle, the sealing ring including an upstream end held on the casing by locking means, elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring, the locking means including a radially outer portion with a C-shaped cross-section and a radial portion extending radially inward from the outer portion, the sealing means including a first elastic seal and a second elastic seal, the two elastic seals bearing on said radial portion, respectively, on either side of the radial portion, wherein the first elastic seal extends axially between the nozzle and the radial portion, wherein the second elastic seal extends axially between the sealing ring and the radial portion.