An improved steady inverse method for turbomachinery aerodynamic design
发表时间：2019-03-12
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- 论文类型：
- 期刊论文
- 第一作者：
- Yang, J.
- 通讯作者：
- Liu, Y (reprint author), Dalian Univ Technol, Sch Energy & Power Engn, Dalian, Peoples R China.
- 合写作者：
- Liu, Y.,Wang, X.,Wu, H.
- 发表时间：
- 2017-05-04
- 发表刊物：
- INVERSE PROBLEMS IN SCIENCE AND ENGINEERING
- 收录刊物：
- SCIE、EI
- 文献类型：
- J
- 卷号：
- 25
- 期号：
- 5
- 页面范围：
- 633-651
- ISSN号：
- 1741-5977
- 关键字：
- Inverse method; turbomachinery; design; pressure loading; computational fluid dynamics
- 摘要：
- An improved inverse method for turbomachinery design is developed in this paper. A strict 'no-slip' boundary condition is imposed during the flow time marching process, and a virtual movement velocity is computed based on characteristics boundary conditions according to the difference of specified and calculated pressure loading, then the camber line of the blade is moved accordingly. A new 'inverse' time step calculation method is proposed to make the value of the 'inverse' time step case-independent, and a coupled non-uniform rational B-spline (NURBS) smoothing technique is used to improve the robustness of the solver, also guarantee the manufacturability of the obtained blade. Two-dimensional test cases, including compressor and turbine cascades, are adopted to validate the method. Then, the method is extended to three dimensions, and a high-loaded rotor of a fan stage is redesigned by the method in a stage environment. The final results indicate a fairly large performance gain, which demonstrates the effectiveness of the improved method.
- 是否译文：
- 否
