Abstract
A novel parametric control method for the compressor blade, the full-blade surface parametric method, is proposed in this paper. Compared with the traditional parametric method, the method has good surface smoothness and construction convenience while maintaining low-dimensional characteristics, and compared with the semi-blade surface parametric method, the proposed method has a larger degree of geometric deformation freedom and can account for changes in both the suction surface and pressure surface. Compared with the semi-blade surface parametric method, the method only has four more control parameters for each blade, so it does not significantly increase the optimization time. The effectiveness of this novel parametric control method has been verified in the aerodynamic optimization field of compressors by an optimization case of Stage35 (a single-stage transonic axial compressor) under multi-operating conditions. The optimization case has brought the following results: the adiabatic efficiency of the optimized blade at design speed is 1.4% higher than that of the original one and the surge margin 2.9% higher, while at off-design speed, the adiabatic efficiency is improved by 0.6% and the surge margin by 1.3%.
Highlights
In recent decades, there have been many important developments in compressor aerodynamic optimization design methods
Combined with the verified computational fluid dynamics (CFD) numerical method, Stage35 is aerodynamically optimized under multi-operating conditions, and an optimized solution is obtained within a relatively acceptable engineering time cost. This result verifies the superiority of the optimization method based on the full-blade surface parametric method in exploring an acceptable approach for multistage compressors with constraints and multi-objective optimization
To verify the effectiveness of the full-blade surface parametric method in solving the HEB problem of the aerodynamic optimization of compressors, a global optimization engineering task was built on a commercial supercomputing platform, which contains three parts: the full-blade surface parametric method, improved artificial bee colony (IABC) algorithm and CFD flow field calculation program and the general single-stage axial flow transonic compressor
Summary
Key Laboratory of Light-Duty Gas-Turbine, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
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