Back to results
US 12,305,515 B2Granted
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.
Claims10
A turbine engine nozzle extending around a longitudinal axis, the nozzle 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,
- a support element carrying the abradable element,
- wherein the support element comprises a flange connected to said main flange to enable a relative radial movement relative to one another,
- wherein the abradable element is arranged opposite two wipers carried by a rotor of the turbine engine and which define therebetween an inter-wiper cavity, and
- 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, and
- a section extending in the flange of the support element.
8 more elements
Dependencies are inferred from the claim text.