| 基于UG/GRIP的涡轮叶片辅助造型方法 |
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| 引用本文： | 严俊峰,焦烨.基于UG/GRIP的涡轮叶片辅助造型方法[J].火箭推进,2008,34(5). |
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| 作者姓名： | 严俊峰 焦烨 |
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| 作者单位： | 1. 西安航天动力研究所,陕西,西安,710100
2. 西安邮电学院,陕西,西安,710061 |
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| 摘 要： | 运用多项式原理和UG／GRIP技术对冲击式涡轮静子叶片进行造型设计，获得了一种先进的涡轮参数化设计方法，从而能够及时、直观地考察叶片的气动特性。同时可采用交互方式对涡轮设计参数进行修改，增强了涡轮计算机辅助设计系统的交互设计能力．有利于提高涡轮设计质量。
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| 关 键 词： | 涡轮 五次多项式 UG／GRIP |
Method of aided modeling for turbine blade based on UG/GRIP |
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| Yan Junfeng,Jiao Ye.Method of aided modeling for turbine blade based on UG/GRIP[J].Journal of Rocket Propulsion,2008,34(5). |
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| Authors: | Yan Junfeng Jiao Ye |
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| Institution: | Yan Junfeng1,Jiao Ye2 (1 Xi\'an Aerospace Propulsion Institute,Xi\'an 710100,China,2 Xi\'an University of Post , Telecommunications,Xi\'an 710061,China) |
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| Abstract: | Based on the principle of polynomial and UG/GRIP technology, in this paper, an advanced method of parametric design for impulse turbine stator is established. This method will assist designers to check the aerodynamic characteristics of the turbine immediately and directly. At the same time, the parameters can be modified in the manner of interactive operation. It will strengthen the interactive design function of the CAD system, which is useful for improving the design quality of turbines. |
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| Keywords: | UG/GRIP |
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