加工误差对多级压气机性能影响的不确定性分析

孟德君; 史文斌; 张皓光; 施磊; 徐朋飞; 王丁喜

doi:10.13224/j.cnki.jasp.20240553

加工误差对多级压气机性能影响的不确定性分析

doi: 10.13224/j.cnki.jasp.20240553

孟德君^{1, 2,},
史文斌^2,*, ,,
张皓光³,
施磊²,
徐朋飞²,
王丁喜³

1.
西北工业大学国家卓越工程师学院，西安 710129
2.
中国航发沈阳发动机研究所，沈阳 110015
3.
西北工业大学动力与能源学院，西安 710129

基金项目: 国家重大科技专项（J2019-Ⅰ-0011）

详细信息

作者简介:
孟德君（1979-），男，研究员，硕士，主要从事压气机设计技术研究。E-mail：762406405@qq.com

通讯作者:
史文斌（1983-），男，高级工程师，硕士，主要从事压气机性能设计。E-mail：zhuowbin@163.com

中图分类号: V231.3
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出版历程
- 收稿日期: 2024-08-07
- 网络出版日期: 2025-03-13

Uncertainty analysis on the impact of manufacturing errors on the performance of multi-stage compressors

MENG Dejun^{1, 2
,},
SHI Wenbin^{2,*
, ,},
ZHANG Haoguang³,
SHI Lei²,
XU Pengfei²,
WANG Dingxi³

1.
National Elite Institute of Engineering，Northwestern Polytechnical University，Xi’an 710129，China
2.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
3.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China

摘要

摘要:
为了评估叶片真实加工误差对多级轴流压气机气动性能的影响，通过引入稀疏非嵌入式多项式混沌方法改进了全局Kriging，随后以较低的训练成本训练了加工误差-压气机工作性能及喘振裕度代理模型，最终获得了加工误差对多级压气机工作性能及喘振裕度的耦合影响规律，并基于Sobol灵敏度分析得到了对压气机性能及喘振裕度影响程度较大的压气机级及几何误差类型。研究结果表明：在加工误差影响下，压气机工作点流量变化的均值及标准差分别为−0.47%和0.064%；工作点效率变化的均值及标准差分别为−0.314%和0.031%。第一级转子的前缘半径对工作点的性能影响显著，对流量和效率方差的贡献率分别为44.83%和47.06%。各级转子安装角误差对工作点的质量流量的总影响较大，方差贡献率合计为52.77%。压气机综合喘振裕度变化量均值及标准差分别为−0.19%和0.146%，综合喘振裕度对转子安装角误差最为敏感，各级转子安装角误差的贡献率总和超过95%。
- 真实加工误差 /
- 多级轴流压气机 /
- 不确定性量化 /
- 喘振裕度 /
- 灵敏度分析
Abstract:
To assess the coupled impact of real blade manufacturing errors on the performance of multi-stage axial compressors, the global Kriging model was improved by introducing the sparse non-intrusive polynomial chaos method. Subsequently, the surrogate model describing the relationship between manufacturing error and compressor’s aerodynamics was trained at a lower training cost. Finally, the quantitative impacts of manufacturing errors on the operational performance and stability margin of a multi-stage compressor were obtained. Moreover, based on Sobol sensitivity analysis, the geometric errors of the compressor stages with the greatest impact on performance and stability margin were identified. The research results indicated that under the impact of manufacturing errors, the mean and standard deviations of the mass flow rate variation at the compressor operating point were −0.47% and 0.064%, respectively. The mean and standard deviations of the efficiency variation at the operating point were −0.314% and 0.031%, respectively. The leading-edge radius error of the first-stage rotor significantly impacted the performance of the operating point, with contributions of 44.83% and 47.06% to the variance of mass flow rate and efficiency respectively. The cumulative contribution of stagger angle errors of each rotor to the mass flow rate at the operating point was significant, with a total contribution rate of 52.77%. The mean and standard deviations of the comprehensive stability margin variation were −0.19% and 0.146%, respectively. The comprehensive stability margin was most sensitive to rotor’s stagger angle errors, with a cumulative contribution exceeding 95% from all rotor stages.
- real machining errors /
- multi-stage compressors /
- uncertainty quantification /
- surge margin /
- sensitivity analysis

HTML

图 1 多级压气机部分计算域

Figure 1. Computational partial domain of multistage compressor

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图 2 对目标几何拟合的优化过程

Figure 2. Optimization process of target geometry fitting

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图 3 转子叶片各截面的参数化建模方案示意图

Figure 3. Schematic diagram of parametric modeling scheme for each section of rotor blades

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图 4 原型叶型截面与拟合结果的对比

Figure 4. Comparison between fitting result and nominal blade

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图 5 第一级转子展向平均加工误差的概率统计分布和Q-Q图

Figure 5. Probability density and Q-Q plots for spanwise-averaged manufacturing errors of first stage rotor

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图 6 二维情况下LHS方法和QMCS方法的采样对比

Figure 6. Comparison between sampling results of LHS and QMCS methods in two-dimensional cases

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图 7 加工误差对多级轴流压气机性能影响的不确定性分析流程图

Figure 7. Flowchart of uncertainty analysis for the impact of manufacturing error parameters on the compressor performance

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图 8 稀疏PC-Kriging对测试集的预测效果

Figure 8. Prediction performance of sparse PC-Kriging on test set

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图 9 工作点气动性能变化统计直方图

Figure 9. Statistical histogram of aerodynamic performance variations at operating point

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图 10 工作点气动性能的Sobol灵敏度计算结果

Figure 10. Sobol sensitivity indices of aerodynamic performance at operating point

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图 11 R1前缘半径误差分别处于公差带上下边界时的R1叶尖（98%叶高）工作点相对马赫数云图

Figure 11. Relative Mach number contour at blade tip （98% span） of R1 at operating point when R1’s leading-edge error equals to tolerance boundaries

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图 12 压气机喘振裕度变化统计直方图

Figure 12. Statistical histogram of variations in compressor surge margin

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图 13 喘振裕度的Sobol灵敏度计算结果

Figure 13. Sobol sensitivity indices of surge margin

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图 14 工作点和近喘点流量的Sobol灵敏度计算结果

Figure 14. Sobol sensitivity indices of mass flow rate at operating and near-surge point

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图 15 工作点和近喘点压比的Sobol灵敏度计算结果

Figure 15. Sobol sensitivity indices of total pressure ratio at operating and near-surge point

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图 16 R1前缘半径误差分别处于公差带上下边界时的R1叶尖（98%叶高）近喘点相对马赫数云图

Figure 16. Relative Mach number contour at blade tip （98% span） of R1 at near-surge point when R1’s leading-edge error equals to tolerance boundaries

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图 17 R1前缘半径误差分别处于公差带上下边界时的后面级叶尖近喘点相对马赫数云图

Figure 17. Relative Mach number contour at blade tip of backward stages at near-surge point when R1’s leading-edge error equals to tolerance boundaries

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