Blade for a turbine engine, associated turbine engine distributor and turbine engine
AssigneeSafran Aircraft Engines
InventorsMatthieu SIMON, Jean-Luc BACHA, Paul DANRE, Léandre OSTINO
Life of this patent
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Abstract
A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.
Claims12
A blade for a turbomachine configured to be disposed about an axis and to extend radially between a radially outer end and a radially inner end, the blade comprising at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade comprising at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade, the blade having a camber such that a central axis of said blade has a radius of curvature between 30 and 500 mm.
Dependencies are inferred from the claim text.