| The main work of this paper is the heat transfer experiment in rotating cavity of an advanced aero-engine of RRD company.(1) A pair of heat transfer disks were designed for the experiment, thermal couple and thermal imaging vedio were applied to test the disks, the results indicated that the designed disks could be used in the experiment.(2) The computation how thermal boundary conditions affected heat transfer coefficient in rotating cavity was carried out through four types of CFD conditions on the disk surfaces: certain temperature, certain heat flux, linear distributing temperature and linear distributing heat flux, abundant results clearly verified the affection. Different thermal boundary conditions affected the flow field, then affected the heat transfer, rotation was the main reason of the affection, viscous heating and buoyancy were two important factors. The configuration called "micro-turbine" conduced the heat transfer in the rotating cavity.(3) The heat transfer coefficient on the left and right disks at different rotate speed were gained in the heat transfer experiment in rotating cavity. The higher heat transfer coefficient the higher rotate speed, the distribution of heat transfer coefficient was comparatively flat at lower rotate speed, but there were distinct peak value and descend at higher rotate speed. As a result of micro-turbine, there were material change of flow field at the speed of approximate 2000rpm. The distribution of heat coefficient on the left and right disks were similar at different flow flux, but the values were obviously different, the higher heat coefficient the higher flow flux. The change of flow flux did not affect the flow structure in the cavity. It was the same as different flow flux to different heat flux, so it verified the computation result that thermal boundary conditions affect heat transfer coefficient in rotating cavity.The experimental results accord with the computational results well. |
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