摘要：
A guide vane for an aircraft turbomachine, where the vane comprises a body 32a which is formed of an intrados (inner curved surface of an arch) 70 and an extrados (outer curved surface of an arch) 72 wall pair, where a heat conducting matrix 80 is inserted into a fluid flow channel 50a formed between the two walls, the matrix contacting each wall and disrupting the fluid flow to improve the heat conduction between the fluid and the walls. There may be several heat conduction matrices which are spaced along the passage. The contact points between the matrix and the walls may be tapered, or alternatively they may be flat. There may be a turbomachine which has a plurality of the guide vanes. A method of fabricating a guide vane including deforming the conduction matrix when the wall pair are closed together, and then fixing them together is also disclosed. The fixing may be brazing, welding or gluing. The conduction matrix may be cold rolled. The deformation may be elastic.
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 vane, said aerodynamic part of the vane comprising at least one internal lubricant cooling passage (50a, 50b) in a part delimited by an intrados wall (70) and an extrados wall (72) of the vane, the intrados wall (70) forming part of a body (32a) of the vane and the extrados wall (72) forming part of a closing cover (32b) of this body, or vice versa.
characterised in that said internal passage (50a, 50b) is equipped with at least one heat conducting matrix (80) compressed between the intrados wall (70) and the extrados wall (72), said matrix separating a first lubricant circulation space (81a) also delimited by the intrados wall (70) on one side of it, and a second lubricant circulation space also delimited by the extrados wall (72) on the other side of it, and in that said matrix (80) defines firstly first intrados wall (70) contact elements (82a) located in the first space (81a) and between which the lubricant in the first space will circulate, and secondly second extrados wall (72) contact elements (82b) arranged in the second space (81b) and between which the lubricant in the first space will circulate.
2. Vane according to claim 1, characterised in that said internal passage (50a, 50b) is provided with several heat conduction matrices (80) compressed between the intrados wall (70) and the extrados wall (72), said matrices being separated from each other along a length direction (25) so as to define a lubricant zone (86) that firstly collects lubricant from the first and second circulation spaces (81a, 81b) in the upstream matrix (80), and secondly to distribute lubricant to the first and second circulation spaces (81a, 81b) in the downstream matrix (80), between any two directly consecutive matrices.
3. Vane according to claim 1, characterised in that the first and second contact elements (82a, 82b) are each generally tapered in shape, with a section that narrows towards its associated intrados or extrados wall.
4. Vane according to claim 1, characterised in that the first and second contact elements (82a, 82b) each have an approximately plane contact end (84a, 84b) bearing on its associated intrados or extrados wall.
5. 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.
6. Method of fabrication of a vane (24) according to claim 1, characterised in that it comprises the following steps:
a) make said at least one heat conduction matrix (80);
b) place the matrix (80) in a part (88) of said internal passage (50a, 50b) defined by the body (32a) of the vane;
c) place said closing cover (32b) on the vane body (32a), so as to compress and deform the heat conduction matrix (80); and
d) fix the closing cover (32b) on the vane body (32a).
7. Method according to claim 6, characterised in that step a) is done by forming sheet metal (80°), preferably by cold forming.
8. Method according to claim 6 to fabricate the vane according to claim 4, characterised in that step b) is done such that each of the first and second contact elements (82a, 82b) of the matrix (80) has a curved contact end (84a, 84b), and such that after step c) to put said closing cover into place, this contact end (84a, 84b) is approximately plane and bears on its associated intrados or extrados wall.
9. Method according to claim 6, characterised in that step c) is performed such that the strain of the matrix (80) is an elastic strain.
10. Method according to claim 6, characterised in that step d) is done by welding, brazing or gluing.