Impeller having spoilers for a turbine engine turbine
AssigneeSafran Aircraft Engines
InventorsJean-Philippe Antoine Beaujard, Roland Gilbert Michel Brault, Nathalie Nowakowski
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AssigneeSafran Aircraft Engines
InventorsJean-Philippe Antoine Beaujard, Roland Gilbert Michel Brault, Nathalie Nowakowski
Estimating the term…
A turbine engine impeller including a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc. The root of each vane is connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades. The impeller further includes two independent annular plates which are fixed to the disc, a first of said plates being mounted upstream of the disc and comprising a transverse annular portion which is supported on an upstream face of the roots of the vanes, and a second of said plates being mounted downstream of the disc and comprising a transverse annular portion which is supported on a downstream face of the roots of the vanes. The integrated platform of each vane stops axially, upstream and downstream, to the right of the upstream and downstream transverse faces of the root, such that said transverse annular portion of each of said plates radially covers at least a space separating the integrated platforms and the disc, and bears, between the integrated platforms and the disc, an annular spoiler which extends in an axial space between the impeller and an adjacent module of the turbine engine without rubbing against an element of said module.
A turbine engine impeller having a longitudinal axis, comprising a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc, the root of each vane being connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades, the impeller further comprising a first and a second independent annular plates which are fixed to the disc,
A turbine engine impeller having a longitudinal axis, comprising a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc, the root of each vane being connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades, the impeller further comprising a first and a second independent annular plates which are fixed to the disc,
Dependencies are inferred from the claim text.