| Citation: | LI Zelin, LIANG Hongxia, LU Jingxu, et al. Effect of effusion hole arrangement pattern on combustion liner cooling performance[J]. Journal of Aerospace Power, 2025, 41（X）：20250336 doi: 10.13224/j.cnki.jasp.20250336
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The wall temperature non-uniformity issue in tangential effusion cooling for a swirl combustor flame tube was addressed. Numerical simulations were employed to investigate the influence of effusion hole arrangement on cooling performance. A zoned refinement strategy was proposed based on near-wall flow characteristics: establishing a dense zone in the high-temperature hotspot region (axial 1/4—2/3 position) with sparse and transition zones at both ends. While maintaining constant total coolant flow rate, the hole spacing in the intensified cooling zone was reduced from 11 times the hole diameter in the baseline configuration to 8 times the hole diameter in the optimized configuration, with corresponding adjustments made to the hole spacing distribution in both the sparse and transition zones. Results demonstrated that the reduced hole spacing in the dense zone significantly decreased the peak wall temperature (up to 50 K reduction) and the high-temperature area, while the tapered hole spacing in transition zones enhanced film-cooling continuity, lowering wall temperature gradient below 44 K/cm to meet thermal protection requirements. The optimized configuration achieved 74% overall cooling efficiency, providing both theoretical foundation and technical support for swirl combustor liner cooling design.
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