| 摘要 |
FIELD: engines and pumps.SUBSTANCE: turbo machine stage comprises rotor ring fitted inside ring divided into sectors, and nozzle diaphragm. Said ring is fitted on turbine housing. Nozzle diaphragm is arranged at turbine wheel inlet and composed of circular row of fixed vanes. Nozzle diaphragm rear end has outer circular collar with attachments to turbine housing. Seals are arranged between nozzle diaphragm outer collar and ring front end to constrict radial gas passage between said pouter collar and ring. Said seals comprises circular sheet extending radially, in fact, between nozzle diaphragm outer collar and ring front end. Said circular sheet inner and outer peripheries comprises means for axial thrust onto outer collar rear side. Sheet medium part is spaced axially from said outer collar to axially thrust on ring front end. Said sheet is preliminary subjected to elastic strain in axial direction on ring front end side. Invention covers also aircraft turbojet or turboprop incorporating above described turbine stage.EFFECT: better seal.8 cl, 5 dwg |
