Turbojet with a discharge duct
AssigneeSafran Aircraft Engines
InventorsFrederic Jacques Eugene Goupil, Noel Joseph Camille Robin, Regis Eugene Henri Servant
Life of this patent
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Abstract
A unit including an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream, is provided. The upstream end of the duct is fastened to the downstream endplate of the hub by releasable elastic engagement.
Claims17
A unit comprising:
- an intermediate casing for a turbine engine including a hub arranged between a low-pressure compressor casing and a high-pressure compressor casing and provided with a downstream transverse endplate having formed therein at least one first opening putting an inside of the hub into communication with a duct extending downstream from the downstream transverse endplate and opening out at a downstream end thereof via a second opening formed in an outer annular shroud disposed downstream from the hub, said shroud defining an inside of an annular flow space for a secondary stream,
- wherein an upstream end of said duct is fastened to the downstream transverse endplate of the hub by releasable elastic engagement.
Dependencies are inferred from the claim text.