| 涡轮典型部件冷热态尺寸换算方法 |
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| 引用本文： | 牛冬生,陈伟.涡轮典型部件冷热态尺寸换算方法[J].航空动力学报,2006,21(1):190-194. |
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| 作者姓名： | 牛冬生 陈伟 |
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| 作者单位： | 南京航空航天大学,能源与动力学院,江苏,南京,210016 |
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| 摘 要： | 涡轮叶尖间隙影响着发动机的性能,涡轮典型部件的冷热态尺寸换算是间隙设计的重要内容.介绍了应用优化设计将涡轮典型部件热态尺寸换算到冷态尺寸的方法,应用此方法对某型涡轮叶片进行分析,比较了优化算法与简化算法的结果,表明优化算法的结果是合理的,此方法是可行的.同时将其应用于某涡轮盘的冷、热态尺寸换算,从而成功地解决了涡轮典型部件冷、热态尺寸换算问题.
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| 关 键 词： | 航空、航天推进系统 涡轮 尺寸换算 优化设计 |
| 文章编号： | 1000-8055(2006)01-0190-05 |
| 收稿时间： | 4/1/2005 12:00:00 AM |
| 修稿时间： | 2005年4月1日 |
Dimension Conversion from Hot State to Cold State of the Turbine Components |
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| NIU Dong-sheng and CHEN Wei.Dimension Conversion from Hot State to Cold State of the Turbine Components[J].Journal of Aerospace Power,2006,21(1):190-194. |
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| Authors: | NIU Dong-sheng and CHEN Wei |
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| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | Tip clearance of the turbine plays an important role on the aeroengine performance.Dimension conversion from hot state to cold state of the turbine components is an important content of tip clearance research.In this paper,dimension conversion method using design optimization was introduced.Based on this method,a blade was analyzed.Compared with simplified method,the result is reasonable and feasible.A turbine disc was also successfully calculated with the design optimization method.Thus,the problem of dimension conversion was solved. |
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| Keywords: | aerospace propulsion system turbine dimension conversion design optimization |
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