重型燃气轮机透平一级动叶冷却结构优化与评估
摘要：目的 重型燃气轮机核心部件国产化对行业技术创新、产业升级，甚至国家安全都有重要意义，而透平一级动叶作为重型燃气轮机典型的热端零部件，其性能直接决定了燃气轮机的效率和可靠性。为此，对某重型燃机透平一级动叶进行了结构优化。 方法 通过增加叶身部分竹节孔竹节的数量，对叶片冷却孔结构进行了优化，同时使用热障涂层来改进叶身涂层。通过流体计算与有限元计算的方法，对叶片服役工况下优化前后叶片的温度、应力分布和气动效率进行了对比分析。 结果 通过对叶片湍流结构的优化，增强了叶片内部换热效率；在冷气进口压力相同的条件下，优化后的叶片表面温度降低了50 ℃以上；由于未改变叶片的气动外形，优化后的叶片对于涡轮气动效率影响较小。相比于优化前的叶片，优化后的叶片在服役过程中的最大等效应力和等效总应变都得到了显著降低。 结论 通过冷却孔的优化和防护涂层的升级，可以显著提升叶片在高温环境中的可靠性。研究结果为燃气轮机的国产化提供了理论依据。
Abstract:Objectives The localization of core components of heavy-duty gas turbines holds significant importance for technological innovation, industrial upgrading, and even national security. As a typical hot-end component of heavy-duty gas turbines, the performance of the turbine first-stage rotor blade directly determines the efficiency and reliability of the gas turbine. Therefore, the structure of the first-stage turbine blades of a certain heavy-duty gas turbine was optimized. Methods By increasing the number of bamboo nodes in the blade body, the blade cooling hole structure was optimized, and the thermal barrier coating was used to improve the blade coating. The temperature, stress distribution and aerodynamic efficiency of the blades before and after optimization under the service condition of the blade were compared and analyzed by fluid calculation and finite element calculation. Results Heat transfer efficiency inside the blade is enhanced by optimization of turbulent structure. Under the condition of the same inlet pressure of the cooling air, the surface temperature of the optimized blade is reduced by more than 50 ℃. Since the shape of the blade is not changed, there is little influence on the aerodynamic efficiency. Compared with the blades without optimization, the maximum equivalent stress and equivalent total strain of the optimized blade during service are significantly reduced. Conclusions By optimizing the cooling structure and upgrading the protective coatings, the reliability of the blades in high-temperature can be significantly improved. The research results provide a theoretical basis for the localization of gas turbines.
标题：重型燃气轮机透平一级动叶冷却结构优化与评估
title:Optimization and Evaluation of Cooling Structure of Stage 1 Blade of Heavy-Duty Gas Turbine
作者：余文昶, 丁阳, 王旭阳, 陈永刚, 毕克, 刘志刚, 上官新刚, 黄道火, 肖峰, 李光, 王广, 柯汉章, 孙亚松, 王鑫
authors:Wenchang YU, Yang DING, Xuyang WANG, Yonggang CHEN, Ke BI, Zhigang LIU, Xingang SHANGGUAN, Daohuo HUANG, Feng XIAO, Guang LI, Guang WANG, Hanzhang KE, Yasong SUN, Xin WANG
关键词：燃气轮机,透平叶片,结构优化,涂层改进,冷却孔,流体计算,有限元计算,
keywords:gas turbine,turbine blade,structure optimization,coating improvement,cooling hole,fluid calculation,finite element calculation,
发表日期：2024-10-31
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- 3.61 MB
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