Traditionally, 3D aerodynamic shape design with the aid of optimization algorithm in an analysis mode has provided a rational and direct search through design space, but it is usually too time-consuming. Further improvement to reduce design cycle is probably a necessary concern in turbomachinery community. Due to less computational cost, adjoint method has received considerable attention in recent years. This paper focuses on continuous adjoint method, and couples with thin shear-layer N-S equations to formulate an efficient sensitivity analysis model for multi-stage turbomachinery blades in the specified objective function. This model includes adjoint equations/boundary conditions, and the sensitivity of objective function to design variable vector. Integrating a 3D blade perturbation parameterization and the simple steepest decent method, a frame of a gradient-based aerodynamic shape design system is constructed. Numerical implementation to solve flow equations and adjoint equations is very similar, and once they are converged respectively, the sensitivity can be calculated by complex method and mesh perturbation efficiently. Thus, a fast Automatic-CFD-Design tool is developed, including three sub-solvers to solve flow equations, adjoint equations and calculate sensitivity respectively. Flow surface design of a 1-1/2 compressor stage in the specified target pressure distribution is used to validate the present approach. Flow field design of NASA transonic compressor stage 35 aiming to increase efficiency and remain mass flow rate and pressure ratio unchanged is taken.
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ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
June 11–15, 2012
Copenhagen, Denmark
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4474-8
PROCEEDINGS PAPER
Multi-Stage Turbomachinery Blades Optimization Design Using Adjoint Method and Thin Shear-Layer N-S Equations
Lucheng Ji,
Lucheng Ji
Beijing Institute of Technology, Beijing, China
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Weiwei Li,
Weiwei Li
Chinese Academy of Sciences, Beijing, China
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Yong Tian,
Yong Tian
Chinese Academy of Sciences, Beijing, China
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Weilin Yi,
Weilin Yi
Beijing Institute of Technology, Beijing, China
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Jiang Chen
Jiang Chen
Beihang University, Beijing, China
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Lucheng Ji
Beijing Institute of Technology, Beijing, China
Weiwei Li
Chinese Academy of Sciences, Beijing, China
Yong Tian
Chinese Academy of Sciences, Beijing, China
Weilin Yi
Beijing Institute of Technology, Beijing, China
Jiang Chen
Beihang University, Beijing, China
Paper No:
GT2012-68537, pp. 1991-2000; 10 pages
Published Online:
July 9, 2013
Citation
Ji, L, Li, W, Tian, Y, Yi, W, & Chen, J. "Multi-Stage Turbomachinery Blades Optimization Design Using Adjoint Method and Thin Shear-Layer N-S Equations." Proceedings of the ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. Volume 8: Turbomachinery, Parts A, B, and C. Copenhagen, Denmark. June 11–15, 2012. pp. 1991-2000. ASME. https://doi.org/10.1115/GT2012-68537
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