| Citation: | WU Jiazhou, ZHANG Jingyu, WANG Long, et al. Cooling characteristics analysis on impingement film with effusion under constant pressure difference[J]. Journal of Aerospace Power, 2024, 39（10）：20220785 doi: 10.13224/j.cnki.jasp.20220785
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In response to the problem of short continuous liner wall and poor film stacking effect in a certain type of oblique flow vortex combustor, a combined impingement film and effusion cooling structure was constructed. Under the conditions of equal pressure difference, experimental study of multiple cooling schemes on the overall cooling effectiveness was carried out, and the influence laws of pressure difference between coolant and hot gas, the distance ratio between slit and effusion, and the impact spacing ratio on the flow and overall cooling effectiveness were obtained by combining the numerical simulation. The results showed that compared with the single effusion or impingement film structure, the impingement film composite effusion scheme solved the problems of low cooling effectiveness in the film initial section and uneven distribution of axial wall temperature, and average area overall cooling effectiveness was about 3.2% higher than effusion cooling. The increase of the pressure difference significantly improved the overall cooling effectiveness. The larger distance ratio between slit and effusion was not conducive to the stacking of the downstream cooling-film, while the reduction of the impact spacing ratio can improve the overall cooling efficiency of the impingement film section.
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