Tandem stator
AssigneeSafran Aero Boosters SA
InventorsJulien Marande, Rémy Henri Pierre Princivalle
Life of this patent
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Abstract
A stator assembly including an upstream blade and a downstream blade axially overlapping and defining between them a channel. The inlet surface of the channel is greater than or equal to the outlet surface of the channel, preferably with a factor of 2. A turbomachine provided with such an assembly, arranged upstream of a high-pressure compressor.
Claims19
A turbomachine comprising an impeller and a separation nozzle, the separation nozzle being arranged downstream of the impeller and separating an air flow into an internal flow traveling through an internal vein and an external flow traveling through an external vein, wherein the turbomachine comprises a stator assembly, the assembly comprising:
- an inner support and an outer support;
- an upstream blade extending substantially radially from the inner support to the outer support, and comprising a trailing edge and an intrados;
- and
- a downstream blade extending substantially radially from the inner support to the outer support, and comprising a leading edge and an extrados;
- wherein the upstream blade and the downstream blade overlap axially over at least part of their radial height, from the inner support to the outer support, a channel thus being defined between the upstream blade and the downstream blade, the channel being circumferentially delimited by the intrados of the upstream blade and the extrados of the downstream blade, and delimited radially by the inner support and the outer support;
- the channel defining:
- a plurality of curves equidistant from the intrados and the extrados in respective planes parallel to an axial direction and located at a given radial coordinate;
- a plurality of input segments perpendicular to each curve and passing through a point of the leading edge contained in the respective plane;
- a plurality of output segments perpendicular to each curve and passing through a point of the trailing edge contained in the respective plane;
- an inlet surface, locus of the input segments on all the radial coordinates of the blades;
- an outlet surface, locus of the output segments on all the radial coordinates of the blades;
- an area of the input surface being between two and four times an area of the output surface,
- the turbomachine further comprising a high-pressure compressor arranged downstream of the stator assembly, the stator assembly being separated from the high-pressure compressor by a swan-neck shape.
Dependencies are inferred from the claim text.