Device for sealing and reinjecting a bypass flow for a turbine nozzle
AssigneeSafran Aircraft Engines
InventorsJérôme Claude George LEMONNIER, Franck Davy BOISNAULT, Antoine Bruno VAN NOORT
Life of this patent
Estimating the term…
Abstract
A turbine comprising a sealing device connected to a nozzle with a radial degree of freedom. The sealing device comprises a reinjection pipe configured to collect a fluid present in a cavity which is located between tongues and is formed by the sealing device, and to reinject the fluid collected in this way into a main duct with a speed which has a large axial component.
Claims12
A turbine engine nozzle extending around a longitudinal axis and comprising a platform, a blade extending radially with respect to the longitudinal axis outwards from the platform, a main flange extending radially inwards from the platform, an abradable element and a support element carrying the abradable element, the support element comprising a flange connected to said main flange, the abradable element being intended to be arranged opposite two wipers carried by a rotor of the turbine engine and which define therebetween an inter-wiper cavity, characterised in that it comprises a reinjection duct comprising an inlet configured to open out into the inter-wiper cavity and an outlet formed at a radially outer end of the flange of the support element and configured to open out into a cavity extending axially downstream of the nozzle, the reinjection duct comprising a section extending in the flange of the support element.
Dependencies are inferred from the claim text.