摘要：
A guide vane (24, fig 2) suitable to be positioned in a twin-spool aircraft turbomachine fan, comprising an aerodynamic flow straightening part (32) located between the root (34) and the tip (36). The aerodynamic part comprises a lubricant cooling passage (50a) which extends in a first lubricant flow direction 52a from the root to the tip of the blade and is limited by intrados 70 and extrados 72 blade walls. The aerodynamic part is made in a single piece. It comprises heat transfer fins 80a, 80b, which connect said walls and extend parallel to the first direction. The fins are distributed in successive rows in the first direction. For a first row R1 and a second row R2 of staggered directly consecutive fins, the first row comprises several fins 80a which form a positive acute angle A1 with a plane and the second row comprises several fins forming a negative acute angle A2 with the same plane, where said plane is a dummy reference plane Pf of the vane which is parallel to the first direction.
权利要求：
CLAIMS
1. Guide vane (24) designed to be positioned in all or some of an air flow in a twin-spool aircraft turbomachine fan (15), the guide vane comprising a root (34), a tip (36) and an aerodynamic flow straightening part (32) located between the root and the tip of the blade, said aerodynamic part of the blade comprising a first internal lubricant cooling passage (50a) extending along a first main lubricant flow direction (52a) from the root (34) towards the tip (36) of the blade, said first internal passage (50a) being partly limited by an intrados wall (70) and an extrados wall (72) of the blade,
characterised in that the aerodynamic part (32) of the vane is made in a single piece and also comprises heat transfer fins (80a, 80b) arranged in the first passage (50a) connecting the intrados and extrados walls (70, 72) and extending approximately parallel to the first direction (52a), said fins being distributed in successive rows of fins following each other along the first principal direction (52a) and made such that for a first row (R1) and a second row (R2) of staggered directly consecutive fins, the first row (R1) comprising at least several fins (80a) forming a positive acute angle Al with a dummy reference plane (Pf) of the vane parallel to the first direction (52a), while the second row (R2) comprises at least several fins (80b) forming a negative acute angle A2 with said dummy reference plane (Pf).
2. Vane according to claim 1, characterised in that each of the fins (80a, 80b) of the vane forms a positive acute angle Al or a negative acute angle A2 with the dummy reference plane, these angles Al, A2 being between 30 and 60°.
3. Vane according to claim 1, characterised in that for a first row (R1) and a second row (R2) of directly consecutive staggered fins, all fins (80a) in the first row (R1) form a positive acute angle Al with the dummy reference plane (Pf), while all fins (80b) in the second row (R2) form a negative acute angle A2 with said dummy reference plane (Pf).
4. Vane according to claim 3, characterised in that the positive acute angle Al is almost identical for all fins (80a) in the first row (R1), while the negative acute angle A2 is almost identical for all fins (80b) in the second row (R2).
5. Vane according to claim 3, characterised in that the fins (80a) in the first row (R1) are at a uniform spacing from each other along a transverse direction(60) of the vane from a leading edge (64) towards a trailing edge (62) of its aerodynamic part (32), in that the fins (80b) in the second row (R2) are at a uniform spacing from each other along the transverse direction (60), and when viewed along the first direction (52a), the fins (80a) in the first row (R1) are arranged between the fins (80b) of the second row (R2), so as to jointly form a broken line.
6. Vane according to claim 1, characterised in that, for a first row (R1) and second row (R2) of directly consecutive staggered fins, each of these rows comprises fins (80a) in alternation along a transverse direction (60) of the vane from a leading edge (64) towards a trailing edge (62) of its aerodynamic part (32), with each fin forming a positive acute angle Al with the dummy reference plane (Pf) and fins (80b) with each fin forming a negative acute angle A2 with said dummy reference plane (Pf).
7. Vane according to claim 6, characterised in that, when viewed along the first direction (52a), the fins (80a, 80b) in the first row (R1) jointly form a first broken line (L1) and the fins (80a, 80b) in the second row (R2) jointly form a second broken line (L2), the first and the second broken lines (L1, L2) being offset from each other along the transverse direction (60) such that at least some of the fins (80a, 80b) in the first row cross (R1) at least some of the fins (80a, 80b) in the second row (R2).
8. Vane according to claim 6, characterised in that the first broken line (L1) and the second broken line (L2) are periodic with the same period T, and they are offset from each other along the transverse direction (60) by a value equal to T/n, where n is a positive integer number preferably between two and four.
9. Vane according to claim 1, characterised in that the aerodynamic part (32) made in a single piece also includes heat transfer fins (80a, 80b) made in a second internal lubricant cooling passage (50b) extending along a second principal lubricant flow direction (52b) from the tip (36) towards the root (34) of the vane, in which there is a fluid connection between said second internal passage (50b) and the first internal passage (50a) through a bend (54) in which there are no heat transfer fins.
10. Turbomachine (1) for an aircraft, preferably a turbojet, comprising a plurality of guide vanes (24) according to claim 1, located downstream or upstream from a fan (15) of the turbomachine.
11. Method of fabrication of a guide vane (24) according to claim 1, characterised in that said aerodynamic part (32) of the vane is made in a single piece by additive fabrication, with the dummy reference plane (Pf) of the vane being located parallel to a vane support surface during fabrication.