摘要：
A guide vane 24 for the fan of a dual flow or bypass aircraft engine has an aerodynamic part 32 comprising an inner duct 50a for lubricant cooling extending in a main direction 52a parallel to the vane. The aerodynamic part is a single or unitary piece, which comprises heat transfer fins 80 in the duct that expand or extend substantially parallel to the main direction. The fins are spaced from each other in the main direction and a transverse direction from leading 64 to trailing 62 edge and at least some of the fins are arranged staggered. The duct may include a first zone and a second zone offset in a transverse direction, where the second zone has an average height between the pressure and suction side walls less than that of the first zone, and the first zone has a greater average density of fins than the second zone. There may also be a second inner duct similarly configured to the first duct, where the ducts may be separate or in fluid communication. Also claimed is an aircraft engine comprising a plurality of such vanes, and a method of manufacturing the vane by additive manufacturing.
权利要求：
CLAIMS
1. A guide vane (24) to be arranged in all or part of an air flow of a aircraft turbine engine fan (15) with dual flow, the guide vane comprising a foot (34), a head (36), and an aerodynamic part (32) for straightening the flow arranged between the foot and the head of the vane, said aerodynamic part of the vane comprising a first inner duct (50 a) for lubricant cooling extending according to a first main direction (52a) of lubricant flow from the foot (34) to the head (36) of the vane, said first inner duct (50a) being partly bounded by a pressure side wall (70) and a suction side wall (72) of the vane,
characterized in that the aerodynamic part (32) of the vane is embodied as one piece including also heat transfer fins (80), arranged in the first duct (50 a) connecting the pressure side and suction side walls (70, 72) and expanding substantially parallel to the first direction (52a), and that the fins (80) are spaced from each other according to the first direction (52a) as well as in a transverse direction (60) of the vane from a leading edge (64) towards a trailing edge (62) of its aerodynamic part (32), so that at least some of such fins (80) are significantly arranged staggered.
2. A guide vane according to claim 1, characterised in that the first inner duct (50a) includes at least one zone in which such heat transfer fins (80) are planned in a density between 1 and 5 fins/cm?.
3. A guide vane according to claim 1, characterized in that said first inner duct (50a) presents a variable density of fins.
4. A guide vane according to claim 3, characterized in that said first inner duct (50a) has at least a first zone (Z1) and second zone (22) offset from the first zone in the transversal direction (60), the second (Z1) with an average height (Hm2) between the pressure side and suction side walls (70, 72), which is less than the average height (Hm1) of the first zone (Z1) , and that said first box (Z1) presents an average density of fins greater than that of the second zone (22).
5. A guide vane according to claim 1, characterized in that said first duct (50a) defines a lubricant thawing channel (90a) extending according to the first main direction (52a), said channel (90a) being devoid of fins on its entire length.
6. A guide vane according to claim 1, characterised in that the aerodynamic part (32) of the vane also has a second inner duct (50b) for lubricant cooling extending according to a second main flow direction (52b) of the lubricant ranging from the head (36) to the foot (34) of the vane, said second inner duct (50b) being partly bounded by a pressure side wall (70) and a suction side wall (72) of the vane, the heat transfer fins (80) being arranged in said second duct (50b) connecting the pressure side and suction side walls (70, 72) and extending substantially parallel to the second direction (52b), and that the heat transfer fins (80) are spaced between themselves according to the second direction (52b) as well as according to the transverse direction (60) of the vane so that at least some of said fins (80) are arranged substantially staggered in the said second inner duct (50b).
7. A guide vane according to claim 6, characterised in that the first and second inner ducts (50a, 50b) extend each separately throughout the entire aerodynamic part (32) of the vane.
8. A guide vane according to claim 6, characterised in that the fluids of the first and second inner ducts (50a, 50b) are connected to each other near the head (36) of the vane, in that the average density of fins (80) within the first inner duct (50a) is preferably less than the density of fins (80) within the second inner duct (50b).
9. A guide vane according to claim 1, characterised in that it has a structural function.
10. An aircraft turbine engine (1), preferably a turbojet including a plurality of guide vanes (24) according to claim 1, arranged downstream or upstream of a fan (15) of the turbine engine.
11. The manufacturing method of a guide vane (24) according to claim 1, characterized in that said aerodynamic part (32) of the vane is made in one piece by additive manufacturing.