| 摘要 |
Lubrication system for a device (e.g. bearing) 13 located between an internal shaft 12a and an external shaft 12b of an aircraft turbine 10, the shafts are free to rotate, concentric and arranged at least partially one around the other; the device further comprises an annular element 30 provided with an external groove 31 which is mounted integral with the external shaft, the external groove is supplied with lubricant from a fixed part of the turbine; a grooved element 25 is included mounted integral with the internal shaft, the grooved element having a relief 70 which directs the lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating; the external groove is in fluid communication with an external surface 70 of the grooved element through at least two conduits 22 arranged through the external shaft. The grooved element may comprise a helical groove. An accumulation ring 24 may form a lubricant reservoir mounted on the external shaft. The internal and external shafts may rotate in opposite directions. |
