Injector for a high-pressure turbine
AssigneeSafran Aircraft Engines
InventorsJérôme Claude George Lemonnier, Franck Davy Boisnault, Nicolas Li Yen Kuhn, Antoine Bruno Van Noort
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Abstract
The present invention relates to a turbine injector comprising an annular ring extending around a longitudinal axis and having a radially outer edge and a radially inner edge. The crown has a plurality of channels for fluidly connecting the radially outer edge to the radially inner edge, each channel extending in a radial plane of the ring and having an inlet opening near the outer edge and an outlet opening near the radially inner edge, the orientation of each channel varying progressively according to a tangential component between the inlet section of the inlet opening and the outlet section of the outlet opening.
Claims8
A turbine injector comprising an annular ring extending about a longitudinal axis and having a radially external rim and a radially internal rim, wherein the ring has at least two channels intended to fluidly connect the radially external rim to the radially internal rim, each channel extending in a radial plane of the ring and having an inlet opening in the vicinity of the external rim and an outlet opening in the vicinity of the radially internal rim, each channel presenting a gradual variation in the orientation of the channel according to a tangential component between an inlet section of the inlet opening and an outlet section of the outlet opening, wherein each inlet section has substantially the shape of a parallelogram surmounted by a triangle or the shape of a triangle and wherein the injector is obtained by additive manufacturing.
Dependencies are inferred from the claim text.