Multi-component coupling optimization for stability improvement of transonic centrifugal compressor
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摘要:
基于最优拉丁超立方采样、多项式代理模型、傅里叶幅值敏感性试验、梯度变异混合优化算法构建了跨声速离心压气机耦合优化方法，实现了自循环机匣处理扩稳的同时不降低等熵效率的目标。耦合优化后压气机气动性能全面提升，设计点和近失速点的等熵效率分别提高2.79%、1.82%，且峰值效率略高于实壁机匣压气机。耦合优化扩稳增效的机理是：自循环机匣抽吸流量增大，更多低能流体被移除；叶轮入口攻角改善，流动分离风险减小；前缘激波与叶尖泄漏涡干涉被抑制，叶轮下游低能流体减少，周向均匀性增强；机匣回流槽入射角增大，叶轮入口径向畸变被削弱；叶轮叶片尾缘安装角及扩压器有叶段尾缘半径的增大弥补了等熵效率损失；叶轮叶片前缘后掠角减小弥补了堵塞流量。
Abstract:Based on the optimal Latin hypercube sampling, polynomial surrogate model, Fourier amplitude sensitivity test, and gradient mutation hybrid optimization algorithm, a coupling optimization method of transonic centrifugal compressors was constructed, and the goal of self-recirculation casing treatment stability improvement without loss of isentropic efficiency was achieved. After the coupling optimization, the aerodynamic performance of the compressor was comprehensively improved. The isentropic efficiency of the design point and near-stall point increased by 2.79% and 1.82%, respectively, and the peak efficiency was slightly higher than the solid compressor. According to the mechanisms of coupling optimization for stabilization and efficiency enhancement: the recirculation flow of self-recirculation casing treatment was increased, and more low-energy fluid was removed; the flow incidence angle of impeller was improved, and the risk of flow separation was reduced; the interaction of leading edge shock wave and the tip leakage vortex was suppressed, the low-energy fluid downstream the impeller was reduced, and the circumferential uniformity of the flow was enhanced; the injection angle of upstream slot of the casing treatment was increased, and the radial distortion of the impeller inlet was weakened; the increases of both the blade angle of the impeller trailing edge and the radius of the diffuser blade trailing edge made up for the isentropic efficiency loss; the reduction of the back sweep of the impeller blade leading edge made up for the choke flow.
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图 6 自循环机匣设计空间全局敏感性分析
Figure 6. Global sensitivity analysis of design space for self-recirculation casing
图 7 叶轮与扩压器关键参数对压气机气动性能的影响
Figure 7. Influences of key parameters of impeller and diffuser on compressor’s aerodynamic performances
图 8 实壁机匣、基准自循环机匣、耦合优化压气机性能曲线对比
Figure 8. Comparison of performance curves among solid casing, baseline self-recirculation casing and coupling optimization compressors
图 9 优化前后叶轮90%叶高相对马赫数云图
Figure 9. Relative Mach number at 90% span of the impeller before and after optimization
图 10 优化前后叶轮90%叶高叶片表面静压分布
Figure 10. Static pressure on blade surface at 90% span of the impeller before and after optimization
图 11 优化前后自循环机匣回流量
Figure 11. Recirculation flow of self-recirculation casing before and after optimization
图 12 优化前后压气机子午速度分布及局部流线图
Figure 12. Meridional velocity and local streamlines of the compressor before and after optimization
图 13 优化前后叶轮90%叶高相对马赫数
Figure 13. Relative Mach number at 90% span of the impeller before and after optimization
图 14 优化前后压气机90%叶高熵分布
Figure 14. Entropy distribution at 90% span of the impeller before and after optimization
图 15 优化前后扩压器90%叶高熵分布
Figure 15. Entropy distribution at 90% span of the diffuser before and after optimization
图 16 优化前后压气机子午面相对马赫数分布
Figure 16. Relative Mach number distribution on meridian plane of the compressor before and after optimization
表 1 离心压气机主要设计参数
Table 1. Key design parameters of the centrifugal compressor
设计参数 数值 设计转速/（r/min） 94500 设计流量/（kg/s） 0.86 设计总压比 5.923 机器马赫数 1.7 叶轮主/分流叶片数 9/9 叶轮叶顶间隙/mm 0.5 叶轮出口直径/mm 118 扩压器叶片数 12 扩压器出口直径/mm
（含有叶与无叶段）200 
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表 2 不同转速下最大相对误差
Table 2. Maximum relative errors under different rotating speeds
转速 等熵效率
最大误差/%总压比
最大误差/%100%设计转速 1.3 5.4 90%设计转速 1.2 1.9 80%设计转速 0.7 0.7
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表 3 基准自循环机匣几何参数范围
Table 3. Value ranges of geometry parameters of the baseline self-recirculation casing
几何参数 下限值 基准值 上限值 空腔高度x1/mm 26 29.39 38 回流槽轴向位置x2/mm −75 −65.32 −55 回流槽入射角x3/（°） 120 135 160 回流槽径向位置x4/mm 45 53.05 61 空腔径向位置x5/mm 59 58.11 64 抽吸槽轴向位置x6/mm −36 −30.83 −25 抽吸槽宽度x7/mm 1 2.5 4 空腔长度x8/mm 85 94.5 104 空腔上倾斜角x9/（°） 0 1.5 3 空腔下倾斜角x10/（°） 0 1.5 3 抽吸槽角度x11/（°） 90 110 132
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表 4 不同代理模型方均根误差
Table 4. Root mean square error of different surrogate models
模型 方均根误差 堵塞
流量设计点
等熵效率设计点
总压比近失速点
等熵效率近失速点
总压比高斯过程回归 0.062 0.066 0.065 0.145 0.100 径向基神经网络 0.045 0.055 0.052 0.103 0.090 4阶多项式线性
回归模型0.046 0.063 0.039 0.071 0.096
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表 5 压气机耦合优化设计变量基准值及变化范围
Table 5. Baseline values and variation ranges of design variables for compressor coupling optimization
耦合优化设计变量 下限值 基准值 上限值 叶轮叶片前缘后掠角/（°） 1 5 5 叶轮叶片尾缘叶顶安装角/（°） 43 44.8 46 叶轮叶片尾缘叶根安装角/（°） 53.7 55.2 56.2 扩压器有叶段尾缘半径/mm 79 79 82 机匣回流槽入射角/（°） 135 135 160 机匣抽吸槽轴向位置/mm −36 −30.8 −25 机匣抽吸槽宽度/mm 1 2.5 4
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表 6 压气机优化前后主要性能指标
Table 6. Key performance indicators of compressor before and after optimization
性能指标 基准机匣 耦合优化 增量/% 设计点等熵效率/% 73.61 75.72 2.79 设计点总压比 5.923 6.183 4.21 近失速点等熵效率/% 71.75 73.08 1.82 近失速点总压比 6.255 6.417 2.52 稳定工况范围/% 20.87 22.92 2.05
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表 7 压气机优化前后设计变量对比
Table 7. Comparison of design variables of the compressor before and after optimization
设计变量 基准
机匣耦合
优化叶轮叶片前缘后掠角/（°） 5 2.31 叶轮叶片尾缘叶顶安装角/（°） 44.8 44.81 叶轮叶片尾缘叶根安装角/（°） 55.2 55.75 扩压器有叶段尾缘半径/mm 79 81.3 机匣回流槽入射角/（°） 135 160 机匣抽吸槽轴向位置/mm −30.8 −31.6 机匣抽吸槽宽度/mm 2.50 2.49
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