To further improve the efficiency of turbomachinery, an advanced aerodynamic optimization system has been developed for the turbomachinery blade optimization design. The system includes parametric modeling, evaluation system, and optimization strategy modules. The nonuniform rational B-spline technique is successfully used for parametric modeling of different blade shapes. An in-house viscous flow code, which combines the lower-upper symmetric-Gauss-Seidel Gaussian elimination (LU-SGS-GE) implicit scheme and the modified fourth-order monotone upstream-centered schemes for conservation laws total variation diminishing (MUSCL TVD) scheme, has been developed for flow field evaluation, which can be replaced by other computational fluid dynamics codes. The optimization strategy is defined by different cases in the system. Parallel optimization technique was used to accelerate the optimization processes. Three test cases were optimized to improve the efficiency by using the system. These cases are the annular turbine cascades with a subsonic turbine blade, a transonic turbine blade, and a subsonic turbine stage. Reasonably high efficiency and performance were confirmed by comparing the analytical results with those of the previous ones. The advanced aerodynamic optimization system can be an efficient and robust design tool to achieve good blade optimization designs in a reasonable time.
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April 2008
Research Papers
Advanced Aerodynamic Optimization System for Turbomachinery
Bo Chen,
Bo Chen
Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering,
e-mail: b-chen04@mails.tsinghua.edu.cn
Tsinghua University
, Beijing 100084, People’s Republic of China
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Xin Yuan
Xin Yuan
Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering,
Tsinghua University
, Beijing 100084, People’s Republic of China
Search for other works by this author on:
Bo Chen
Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering,
Tsinghua University
, Beijing 100084, People’s Republic of Chinae-mail: b-chen04@mails.tsinghua.edu.cn
Xin Yuan
Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering,
Tsinghua University
, Beijing 100084, People’s Republic of ChinaJ. Turbomach. Apr 2008, 130(2): 021005 (12 pages)
Published Online: February 12, 2008
Article history
Received:
November 7, 2006
Revised:
March 15, 2007
Published:
February 12, 2008
Citation
Chen, B., and Yuan, X. (February 12, 2008). "Advanced Aerodynamic Optimization System for Turbomachinery." ASME. J. Turbomach. April 2008; 130(2): 021005. https://doi.org/10.1115/1.2776953
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