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Research Papers

Advanced Aerodynamic Optimization System for Turbomachinery

[+] Author and Article Information
Bo Chen1

Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, Tsinghua University, Beijing 100084, People’s Republic of Chinab-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 China

1

Corresponding author.

J. Turbomach 130(2), 021005 (Feb 12, 2008) (12 pages) doi:10.1115/1.2776953 History: Received November 07, 2006; Revised March 15, 2007; Published February 12, 2008

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.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Subsonic turbine blade profile represented with NURBS

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Figure 2

Transonic turbine blade profile represented with NURBS

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Figure 3

Compressor blade profile represented with NURBS

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Figure 4

Fan blade profile represented with NURBS

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Figure 5

Stacking line represented using NURBS for blade deformation: (a) lean of the blade, (b) sweep of the blade, and (c) twist of the blade

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Figure 6

3D blade deformation system

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Figure 7

Integration among NURBS, ISIGHT , and CFD codes

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Figure 8

Stacking line before and after optimization: (a) original and (b) after optimization

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Figure 9

Yamamoto’s 3D blade surface

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Figure 10

Total pressure loss coefficient contours before optimization: (a) exit section, (b) end wall, and (c) tip

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Figure 11

Total pressure loss coefficient contours after optimization: (a) exit section, (b) end wall, and (c) tip

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Figure 12

Exit total pressure loss distributions

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Figure 13

Comparison of static pressure coefficients

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Figure 14

The evaluating history of the GA strategy

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Figure 15

VKI-LS-59 3D blade surface: (a) original and (b) after optimization

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Figure 16

Bottom profile comparison

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Figure 17

Middle profile comparison

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Figure 18

Top profile comparison

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Figure 19

Exit total pressure loss distributions

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Figure 20

Mach number contours at the blade middle span: (a) original blade and (b) optimal blade

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Figure 21

Isentropic Mach number along the blade

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Figure 22

The evaluating history of the ASA strategy

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Figure 23

Comparison of static pressure distributions

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