Adjoint method is an important tool for design refinement of multistage compressors. However, the radial static pressure distribution deviates during the optimization procedure and deteriorates the overall performance, producing final designs that are not well suited for realistic engineering applications. In previous development work on multistage turbomachinery blade optimization using adjoint method and thin shear-layer N-S equations, the entropy production is selected as the objective function with given mass flow rate and total pressure ratio as imposed constraints. The radial static pressure distribution at the interfaces between rows is introduced as a new constraint in the present paper. The approach is applied to the redesign of a five-stage axial compressor, and the results obtained with and without the constraint on the radial static pressure distribution at the interfaces between rows are discussed in detail. The results show that the redesign without radial static pressure distribution constraint (RSPDC) gives an optimal solution that shows deviations on radial static pressure distribution, especially at rotor exit tip region. On the other hand, the redesign with the RSPDC successfully keeps the radial static pressure distribution at the interfaces between rows and make sure that the optimization results are applicable in a practical engineering design.
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ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
June 15–19, 2015
Montreal, Quebec, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5665-9
PROCEEDINGS PAPER
Shape Optimization of Multi-Stage Axial Compressor Blades Using Adjoint Method With Static Pressure Constraint at Blade Row Interface
Jia Yu,
Jia Yu
Beijing Institute of Technology, Beijing, China
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Lucheng Ji,
Lucheng Ji
Beijing Institute of Technology, Beijing, China
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Weiwei Li,
Weiwei Li
Beijing Institute of Technology, Beijing, China
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Weilin Yi
Weilin Yi
Beijing Institute of Technology, Beijing, China
Search for other works by this author on:
Jia Yu
Beijing Institute of Technology, Beijing, China
Lucheng Ji
Beijing Institute of Technology, Beijing, China
Weiwei Li
Beijing Institute of Technology, Beijing, China
Weilin Yi
Beijing Institute of Technology, Beijing, China
Paper No:
GT2015-42232, V02CT45A004; 13 pages
Published Online:
August 12, 2015
Citation
Yu, J, Ji, L, Li, W, & Yi, W. "Shape Optimization of Multi-Stage Axial Compressor Blades Using Adjoint Method With Static Pressure Constraint at Blade Row Interface." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 2C: Turbomachinery. Montreal, Quebec, Canada. June 15–19, 2015. V02CT45A004. ASME. https://doi.org/10.1115/GT2015-42232
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