| Citation: | Liang Hongxia, Liu Fusheng, Lu Jingxu, et al. Study on the influence of aerodynamic and working parameters on the tangential effusion cooling combustor performance[J]. Journal of Aerospace Power, 2026, 41（X）：20250169 doi: 10.13224/j.cnki.jasp.20250169
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To address the thermal protection requirements of combustor liners under high-temperature and elevated heat loads, the single-tube combustor model incorporating tangential effusion cooling technology was developed. A conjugate heat transfer analysis was employed to numerically investigate the influence of varying inlet temperature, inlet pressure, and fuel-air ratio on liner wall temperature and cooling performance. The results show that the higher inlet temperatures reduced cooling film coverage effectiveness, weakened heat transfer intensity within effusion holes and on the outer liner wall, decreased average integrated cooling efficiency, and increased both wall temperature and thermal gradients. Under the condition of this paper, variations in inlet pressure exhibited minimal influence on near-wall flow and heat transfer, with negligible differences in effusion cooling effectiveness. Under extreme conditions that the proportion of cooling air is only about 19%, fuel-air ratio of 0.042, and combustor temperature rise approaching
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