| Citation: | JIANG Jintao, DONG Suyan, DONG Rongxiao, et al. Optimization design and experiment on the cooling structure of turbine guide vane in an engine[J]. Journal of Aerospace Power, 2026, 41（3）：20240833 doi: 10.13224/j.cnki.jasp.20240833
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To address the issue of ablation and cracks on the trailing edge of the turbine guide blade in an aeroengine, the process characteristics of rapid prototyping of complex surfaces were combined using additive manufacturing, numerical simulation methods were employed to optimize the design of turbine blade cooling structures, and experimental research on the cooling structure schemes of turbine guide blades was conducted. The constructed experimental platform can simulate real engine operating parameters for turbine blade cooling efficiency. Based on this experimental platform, experiments were conducted on the effects of parameters such as pressure ratio, temperature ratio, and flow ratio on the overall cooling efficiency and dimensionless temperature distribution of the blade. The experimental results indicated that the effect of flow rate ratio on the cooling efficiency of the turbine blades was greater than that of temperature ratio and pressure ratio. Within the experimental operating range, as the flow ratio increased from 0.75% to 1.50%, the blade cooling efficiency increased from 0.123 to 0.183, representing an improvement of 48.78%. When the temperature ratio increased from 1.5 to 2.0, the blade cooling efficiency rose from 0.165 to 0.199, an increase of 20.61%. As the pressure ratio increased from 1.4 to 2.2, the blade cooling efficiency grew from 0.141 to 0.162, an enhancement of 14.08%.
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