重型燃气轮机透平一级动叶冷却结构优化与评估
TK14; [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...
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| Published in | 发电技术 Vol. 45; no. 5; pp. 838 - 846 |
|---|---|
| Main Authors | , , , , , , , , , , , , , |
| Format | Journal Article |
| Language | Chinese |
| Published |
中国华电集团有限公司上海分公司,上海市 浦东新区 200126%华电电力科学研究院有限公司,浙江省 杭州市 310030%上海奉贤燃机发电有限公司,上海市 奉贤区 201404
01.10.2024
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| Subjects | |
| Online Access | Get full text |
| ISSN | 2096-4528 |
| DOI | 10.12096/j.2096-4528.pgt.24101 |
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| Abstract | TK14; [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. |
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| AbstractList | TK14; [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_FL | [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. |
| Author | 上官新刚 陈永刚 王鑫 王旭阳 肖峰 柯汉章 李光 丁阳 黄道火 王广 毕克 刘志刚 孙亚松 余文昶 |
| AuthorAffiliation | 中国华电集团有限公司上海分公司,上海市 浦东新区 200126%华电电力科学研究院有限公司,浙江省 杭州市 310030%上海奉贤燃机发电有限公司,上海市 奉贤区 201404 |
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| Author_FL | SUN Yasong WANG Guang WANG Xin BI Ke SHANGGUAN Xingang LIU Zhigang LI Guang CHEN Yonggang HUANG Daohuo KE Hanzhang DING Yang WANG Xuyang XIAO Feng YU Wenchang |
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| Keywords | gas turbine finite element calculation 燃气轮机 冷却孔 涂层改进 流体计算 structure optimization cooling hole coating improvement fluid calculation 有限元计算 turbine blade 结构优化 透平叶片 |
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| Title | 重型燃气轮机透平一级动叶冷却结构优化与评估 |
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