numerical simulation was used to investigate the heat transfer of a typical turbine blade cooling configuration of ribbed passage and staggered pin fin arrays.
the experimental results are valuable reference for aero-engine turbine blade cooling designers.
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。
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.