| 过渡态带隔热涂层的燃气涡轮叶片热状态计算方法研究 |
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| 引用本文： | 徐磊,杨燕生.过渡态带隔热涂层的燃气涡轮叶片热状态计算方法研究[J].航空发动机,2010,36(1):20-23. |
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| 作者姓名： | 徐磊 杨燕生 |
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| 作者单位： | 中国燃气涡轮研究院,四川江油,621703 |
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| 摘 要： | 过渡态条件下热端部件热状态计算在评估发动机性能、强度寿命及内部间隙等方面占有十分重要的地位。参考了俄罗斯关于过渡态涂层叶片的1种计算方法,但对其中的数学处理作了更广泛的集成和推广,使得该方法能更充分地考虑过渡态变化过程的复杂性以及换热边界条件的适时变化等问题;以该方法编制了带涂层热端部件的工程计算程序,将计算结果与国外数据进行了对比,吻合较好。
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| 关 键 词： | 燃烧室 中低热值 燃气轮机 改进设计 WP6发动机 |
Calculation Method of Transient Thermal Behavior for Turbine Blade with Thermal Barrier Coating |
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| Authors: | XU Lei YANG Yan-sheng |
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| Institution: | (China Gas Turbine Establishment, Jiangyou 610500, Sichuan, China) |
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| Abstract: | RF031 gas turbine is derived from WP6 by removing 3 stages compressor and changing fuel from kerosene to low/middle calorific fuel. The improved concept and validation results of improved combustor were presented based on WP6 combustor. The combustion stabilization was achieved with low/middle calorific fuel （10467kJ/m^3） The various performance of the combustor could basically meet the general requirements and the preliminary goal of the RF031. |
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| Keywords: | combustor low/middle calorific gas turbine improved design WP6 aeroengine |
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