Optimal Design of Centrifugal Compressor Impeller under Uncertain Aerodynamic Boundary Condition
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摘要: 以某小型离心压气机为研究对象，基于非嵌入式概率配置点法和数值分析研究气动边界不确定性对离心压气机气动性能的影响规律，量化转速波动不确定对离心压气机压比的影响程度；提出一种基于不确定分析方法、代理模型、多目标优化算法的离心压气机气动稳健设计方法，为离心压气机及其他叶轮机械设计及应用提供重要参考。研究结果表明，优化后叶轮压比增大4.1%，压比方差降低13.52%，叶轮气动稳健性增强。Abstract: Taking a small centrifugal compressor as the object, based on the non-intrusive probability collocation method and numerical analysis, the influence rule of the aerodynamic boundary uncertainty on the aerodynamic performance of the centrifugal compressor is studied, and the influence of the uncertainty of the rotational speed fluctuation on the centrifugal compressor pressure ratio is quantified. An aerodynamic robust design method for centrifugal compressor based on the uncertain analysis method, the surrogate model and the multi-objective optimization algorithm is proposed, which provides an important reference for the design and application of centrifugal compressor and other impeller machinery. The results show that the impeller pressure ratio increases by 4.1% and the pressure ratio variance decreases by 13.52% after optimization. The aerodynamic robustness is enhanced.
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表 1 不同工况下叶轮实验值与计算值的比较
类型 工况 实验值 计算值 误差/% LSCC 设计点 压比 1.141 1.143 0.18 效率 0.922 0.949 2.9 非设计点 压比 1.169 1.170 0.08 效率 0.931 0.958 2.9 Krain 设计点 压比 4.133 4.297 3.96 效率 0.850 0.852 0.23 非设计点 压比 4.054 4.223 4.17 效率 0.845 0.853 0.94 
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表 2 2阶和3阶配置点与对应权重
2阶 3阶 转速/(r·min-1) 权重 转速/(r·min-1) 权重 130 324 0.166 667 128 697 0.045 876 135 000 0.666 667 132 997 0.454 121 139 677 0.166 667 137 003 0.454 121 141 303 0.045 876
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表 3 拉丁超立方试验设计变量与响应值
方案 β1b β2b δu tclr π σπ2 1 38.6 46.4 57.2 0.3 1.828 4 0.003 8 2 26.2 56.0 60.9 0.3 1.979 2 0.005 1 29 33.8 54.0 54.1 0.2 2.030 2 0.004 5 30 21.4 63.6 57.8 0.2 2.169 4 0.005 8
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表 4 不确定性优化后离心叶轮性能参数对比
参数 π σπ2 η/% Δπ/% Δσπ2/% Δη/% 初始 1.980 7 0.005 4 80.2 A 1.996 7 0.004 3 83.8 0.81 -20.37 4.49 B 2.062 0.004 7 82.1 4.1 -13.52 1.2 C 2.097 0.004 9 82.0 5.87 -8.52 2.29 注:η为效率均值
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