Turbomachine blade comprising an internal fluid flow passage equipped with a plurality of optimally arranged disruptive elements
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.
1. 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 (X 1 ; X 2 ) 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 ( 66 a ) on the inner lower surface face ( 67 ), and a second connection point ( 66 b ) on the inner upper surface face ( 68 ),
wherein the disruptive elements extend in relation to the general fluid propagation direction (X 1 ; X 2 ) 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 ( 66 a ) are arranged in a disorganised manner on the inner lower surface face ( 67 ), and/or the second connection points ( 66 b ) are arranged in a disorganised manner on the inner upper surface face ( 68 ).
2. Vane according to claim 1 , wherein the internal fluid passage ( 43 ) comprises a first and a second channel ( 44 , 46 ) each defining a fluid propagation direction (X 1 , X 2 ) substantially parallel with the span axis (EV), these first and second channels ( 44 , 46 ) being traversed by disruptive elements ( 66 ) the first and second connection points ( 66 a , 66 b ) whereof do not follow a specific alignment along the fluid propagation direction (X 1 , X 2 ).
3. Vane according to claim 1 , wherein for any connection point ( 66 a , 66 b ) among the first connection points ( 66 a ) and/or the second connection points arranged in a disorganised manner, this connection point has around same a number N of connection points forming a closed line, delimiting internally a space wherein the single any connection point is found, the distance between the latter is each of said N points is different for at least three thereof, and preferably for each thereof.
4. Vane according to claim 1 , wherein,
in a view from inside the fluid passage ( 43 ), along a direction locally substantially orthogonal to and oriented towards the inner lower surface face ( 67 ), all the first connection points ( 66 a ) thereof are each arranged at the intersection between a primary imaginary line (L 1 , L 2 , L 3 , L 4 , L 5 ) extending parallel with the fluid propagation direction (X 1 , X 2 ), and a secondary imaginary line (F 1 , F 2 , F 3 , F 4 , F 5 ) perpendicular to the primary imaginary line, all of the first imaginary lines being all distinct from one another and all of the second imaginary lines being all distinct from one another; and/or
in a view from inside the fluid passage ( 43 ), along a direction locally substantially orthogonal to and oriented towards the inner upper surface face ( 68 ), all the second connection points ( 66 b ) thereof are each arranged at the intersection between a primary imaginary line extending parallel with the fluid propagation direction (X 1 , X 2 ), and a secondary imaginary line perpendicular to the primary imaginary line, all of the first imaginary lines between all distinct from one another and all of the second imaginary lines being all distinct from one another.
5. Vane according to claim 1 , wherein the disruptive elements are spaced pairwise at the nearest point by a distance enabling fluid flow, this distance being preferentially between 2 and 10 mm.
6. Vane according to claim 1 , wherein the value of the angle formed between each disruptive element ( 66 ) and the fluid propagation direction (X 1 ; X 2 ) is between 70 and 110°.
7. Vane according to claim 1 , wherein the disruptive elements ( 66 ) extend by forming an angle greater than a predefined angle A with respect to a parallel plane with the successive manufacturing layers forming the aerodynamic part of the vane below which these disruptive elements should be supported during manufacture, the angle A being preferentially greater than 30°.
8. Vane according to claim 1 , wherein the disruptive elements ( 66 ) extend by forming an angle of less than 70° with respect to a parallel plane with the successive layers forming the vane.
9. Vane according to claim 1 , wherein the disruptive elements are bars with a cylindrical cross-section of diameter of the order of 1 mm.
10. Aircraft engine comprising at least one vane according to claim 1 .
11. Additive manufacturing method of a vane according to claim 1 , by stacking on a plate T of material layers forming the vane from the leading edge thereof, during which the span axis (EV) is parallel with the plate T and the upper surface wall forms with the plate T an angle which decreases with the stacked layers.