本文的实验结果对于航空发动机涡轮叶片冷却结构设计具有参考价值。
The experimental results are valuable reference for aero-engine turbine blade cooling designers.
通过分析三菱M701F燃气轮机叶片冷却技术的冷却原理和运行方式，为燃气轮机的安全高效运行提供参考。
This essay analyzes the cooling principle and the mode of operation of the M701F gas turbine blade cooling technology to verify its efficiency in enhancing the safety of the gas turbine.
根据燃气轮机透平叶片冷却的实际情况，引入并完善叶片冷却的计算模型，并采用文献报道的数据验证计算模型的正确性。
Based on the gas turbine blade's practical cooling condition, a blade cooling computation model is introduced and perfected, and its validity is verified using reported data.
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