摘要：
A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.
权利要求：
CLAIMS
1. A guide vane (24) to be arranged in all or part of an air flow of an 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 in 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 it comprises a first heat conduction matrix housed in said first inner duct (50a) and including rows of main heat transfer fins (80) succeeding each other in the first direction (52A) parallel to the direction that such main fins (80) extend, these being spaced from each other in the first direction (52A) as well as in a transverse direction (60) of the vane from a leading edge (64) to a trailing edge (62) of its aerodynamic part (32) so that at least some of the said main fins (80) are laid out significantly staggered, and that each row includes junction fins connecting each two main fins (80) directly in a consecutive manner in the transverse direction (60), said junction fins being alternatively in inner contact with the pressure side wall (70) and the suction side wall (72) in order to form, with the main fins (80) that they connect, a transverse structure in a general cradle form.
2. The guide vane includes, at the level of the foot or the head of the vane, an opening for the introduction of the first heat conduction matrix in the first inner duct (50a).
3. A guide vane according to claim 1, or claim 2, characterised in that the first heat conduction matrix (50a) includes at least one zone in which such main heat transfer fins (80) are planned in a density between 1 and 5 fins/cm?2.
4. A guide vane according to one any of the preceding claims, characterised in that the first heat conduction matrix has main fins (80) with a variable density.
5. A guide vane according to claim 4, characterized in that said first inner duct (50a) has at least a first zone (Z1) and second zone (Z2) offset from the first zone in the transversal direction (60), the second (Z2) 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 zone (Z1) presents an average fin density greater than that of the second zone (22).
6. A guide vane according to any preceding claim, characterized in that said first duct (50a) defines a lubricant thawing channel (90a) extending in the first main direction (52a), said channel (90a) being devoid of fins on its entire length. and follows along the first heat conduction matrix.
7. A guide vane according to one any of the preceding claims, characterised in that the aerodynamic part (32) of the vane also has a second inner duct (50b) for cooling lubricant, extending in a second main lubricant flow direction (52b) ranging from the head (36) to the foot (34) of the vane, said second inner duct (50B) being partly bounded by the vane pressure side wall (70) and a suction side wall (72), a second heat conduction matrix being lodged in said second inner duct (50b) and including rows of main heat transfer fins (80) succeeding each other in the second direction (52b) in parallel with said main fins (80), these being spaced from each other similar to the second direction (52b) as well as in the transverse direction (60) so that at least some of the said main fins (80) are arranged substantially in staggered in the second inside duct (50b), and that each row includes junction fins connecting each two main fins (80) directly in a consecutive manner in the transversal direction (60), said junction fins being alternately in contact with the pressure side wall (70) and the suction side wall (72) in order to form, with the main fins (80) that they connect to, a structure in a general cradle form.
8. A guide vane according to claim 7, characterised in that each of the first and second inner ducts (50a, 50b) extend separately throughout the entire aerodynamic part (32) of the vane,
or in that the first and second inner ducts (50a, 50b) are connected to each other near the vane head (36), 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 any of the preceding claims, 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 any preceding claim, arranged downstream or upstream of a fan (15) of the turbine engine.
11. Manufacturing method of a guide vane (24) according to any of claims 1 to 9, characterized in that said aerodynamic part (32) of the vane is made in one piece so as to reveal the first inner duct (50a), then the first heat conduction matrix is inserted in said first inner duct (50a).