Turbomachine blade comprising an internal fluid flow passage equipped with a plurality of optimally arranged disruptive elements
AssigneeSafran Aircraft Engines
InventorsSébastien Vincent François Dreano, Mohammed-Lamine Boutaleb
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Abstract
An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.
Claims11
Aircraft turbomachine vane comprising an aerodynamic part (32) extending along a span axis (EV) and made of one piece by additive manufacturing, said aerodynamic part comprising a lower surface wall (37) and an upper surface wall (38) comprising respectively an inner lower surface face (67) and an inner upper surface face (68), these inner lower and upper surface faces (67, 68) facing one another and delimiting jointly an internal fluid passage (43) comprising at least one channel (44;
- 46) defining a general fluid propagation direction (X1;
- X2) therein, this channel being traversed by a plurality of flow disruption elements (66) connecting the lower and upper surface walls (37, 38) each having a first connection point (66a) on the inner lower surface face (67), and a second connection point (66b) on the inner upper surface face (68),
- wherein the disruptive elements extend in relation to the general fluid propagation direction (X1;
- X2) by forming a variable angle from one disruptive element to another, and in that the disruptive elements (66) are irregularly spaced from one another such that the first connection points (66a) are arranged in a disorganised manner on the inner lower surface face (67), and/or the second connection points (66b) are arranged in a disorganised manner on the inner upper surface face (68).
Dependencies are inferred from the claim text.