| 航空发动机涡轮动叶设计平台的构建与验证 |
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| 引用本文： | 李磊,敖良波,王心美,岳珠峰.航空发动机涡轮动叶设计平台的构建与验证[J].航空发动机,2012,38(3):24-28. |
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| 作者姓名： | 李磊 敖良波 王心美 岳珠峰 |
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| 作者单位： | 西北工业大学工程力学系,西安710129 |
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| 基金项目： | 博士后基金（20100471634）、863计划（2009AA042418）资助 |
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| 摘 要： | 针对航空发动机涡轮叶片的设计流程,开发了涡轮动叶的设计平台。基于气动热力学方法建立了1维性能设计模块;并在研究平面叶栅造型设计方法的基础上,建立了2维气动分析模块,可以实现2维叶型气动性能的快速分析;在实心/冷却叶片参数化设计的基础上,引入多学科可行方法,建立了实心/冷却叶片设计和多学科优化模块。利用所开发的设计平台进行了某型冷却叶片的多学科设计优化,有效提高了该叶片的综合性能,验证了平台的有效性。
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| 关 键 词： | 航空发动机 涡轮叶片 设计平台 设计流程 多学科设计优化 |
Establishment and Verification of Aeroengine Turbine Rotor Blade Design Platform |
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| Authors: | LI Lei AO Liang-bo WANG Xin-mei YUE Zhu-feng |
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| Institution: | (Department of Engineering Mechanics, Northwestern Polytechnincal University, Xi＇an 710129, China) |
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| Abstract: | Aiming at design process of aeroengine turbine rotor blade, its platform was developed. One-dimensional performance design module was developed with aerothermodynamics. Based on planar cascade method, the two-dimensional aerodynamic design module which can predict the performance of the cascade quickly was built. The cooling blade and multi-disciplinary design optimization module were built with multi-disciplinary method based on the cooling blade parametric design. The multi-disciplinary design optimization of a cooling blade was obtained by the design platform, which effectively improve the blade integrated performance and validate the platform efficiency. |
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| Keywords: | aeroengine turbine blade design platform design process multi-disciplinary design optimization |
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