Uncertainty analysis of effects of real coupling deviations on aerodynamic performance of compressor cascades
-
摘要:
为研究真实耦合偏差对叶栅气动性能的影响，本研究基于矩的任意多项式混沌方法，将弦长偏差、最大厚度偏差与前缘半径偏差施加于一高负荷压气机叶栅进行研究。研究结果表明：与原型相比，负攻角工况下，总压损失系数增大的概率约为79.47%，静压系数减小的概率约为92.83%；正攻角工况下，总压损失系数增大的概率约为91.11%，静压系数减小的概率约为86.42%。不同工况下性能参数均对前缘半径偏差敏感性最高，结合损失源分析发现前缘损失占主导地位，因此在加工时需严格控制前缘加工精度。相较原型叶片，负攻角工况下，加入耦合偏差的叶栅角区分离程度变化明显，分离点、回流区域面积与回流区轴向长度明显增大；正攻角工况下，加入耦合偏差的叶栅角区分离程度不明显。
-
关键词:
- 耦合偏差 /
- 角区流动 /
- 基于矩的任意多项式混沌方法 /
- 不确定性量化 /
- 叶栅
Abstract:To investigate the effect of real coupling deviation on the aerodynamic performance of a blade cascade, chord length deviation, thickness deviation, and leading edge radius deviation were applied to a high load compressor blade cascade for research based on the arbitrary polynomial chaos method of moments. The research results showed that compared with the prototype, the probability of an increase in total pressure loss coefficient and a decrease in static pressure coefficient under negative angle of attack conditions was about 79.47% and 92.83%, respectively; under positive angle of attack conditions, the probability of an increase in total pressure loss coefficient was about 91.11%, and the probability of a decrease in static pressure coefficient was about 86.42%. The aerodynamic performance under different operating conditions was most sensitive to the deviation of the leading edge radius. Combined with the analysis of the loss source, it was found that the leading edge loss played a dominant role. Therefore, strict control of the leading edge machining accuracy was required during machining. Compared with the prototype blade, under negative attack angle conditions, the degree of separation in the blade angle region with added coupling error changed significantly, and the separation point, recirculation area, and axial length of the recirculation area increased significantly; under positive angle of attack conditions, the degree of separation in the blade angle region with added coupling error was not significant.
-
图 4 不同网格数下距尾缘下游0.5C位置处总压损失系数沿叶高分布图
Figure 4. Spanwise distribution of $\omega $ at 0.5C downstream of the trailing edge for different grids numbers
图 9 攻角为−2°下性能参数计算值与预测值对比
Figure 9. Comparison of calculation and predicted results when i=−2°
图 10 攻角为4°下性能参数计算值与预测值对比
Figure 10. Comparison of calculation and predicted results when i=4°
图 16 不同叶型几何对比及局部放大图
Figure 16. Geometric comparison and local enlargement of different cascade
图 19 周向平均总压损失系数沿叶高分布
Figure 19. Distribution of circumferential average total pressure loss coefficient along the blade span
图 21 攻角为−2°下0.1倍叶高和0.5倍叶高轴向速度云图
Figure 21. Axial velocity contour of 0.1 times and 0.5 times blade span at i=−2°
图 22 不同叶型几何对比及局部放大图
Figure 22. Geometric comparison and local enlargement of different cascade
图 25 周向平均总压损失系数沿叶高分布
Figure 25. Distribution of circumferential average total pressure loss coefficient along the blade span
图 27 攻角为4°下0.1倍叶高和0.5倍叶高轴向速度云图
Figure 27. Axial velocity contour of 0.1 times and0.5 times blade span at i=4°
表 1 原型叶栅设计参数
Table 1. Original cascade design parameters
参数 数值 叶高$h/{\text{mm}}$ 100 弦长C/mm 40 轴向弦长Ca/mm 36.2 进口几何角β1k/（°） 25 出口几何角β2k /（°） 80 叶距 s/mm 20 设计攻角i/（°） 0 
下载: 导出CSV
表 2 偏差统计特征值
Table 2. Deviation statistical characteristic value
mm 偏差类型 分布区间 平均值 标准差 弦长偏差 [−0.387, 0.298] − 0.03479 0.13692 最大厚度偏差 [−0.040, 0.081] 0.03937 0.02406 前缘半径偏差 [−0.021, 0.054] 0.02253 0.01533
下载: 导出CSV
表 3 测试集的R2与Er-RMSE分布
Table 3. Test set R2 and Er-RMSE distribution
输出变量 R2 Er-RMSE/% ω（i=−2°） 0.9975 0.0376 ${C_{\text{p}}}$（i=−2°） 0.9986 0.0118 ω（i=4°） 0.9997 0.0090 ${C_{\text{p}}}$（i=4°） 0.9995 0.0122
下载: 导出CSV
表 4 攻角为−2°下性能统计结果
Table 4. Performance statistics when i=−2°
统计量 设计值 μ σ （σ/μ）/% ω 0.2324 0.2337 0.001495 0.64 Cp 0.5226 0.5205 0.001485 0.29
下载: 导出CSV
表 5 攻角为4°下性能统计结果
Table 5. Performance statistics when i=4°
统计量 设计值 μ σ （σ/μ）/% ω 0.3273 0.3289 0.001049 0.32 Cp 0.4957 0.4943 0.001244 0.25
下载: 导出CSV
-
[1] 刘铠烨, 楚武利, 郭正涛, 等. 加工误差对超音速叶栅气动性能影响的不确定性分析 [J]. 航空动力学报, 2024, 39(12): 20220791. LIU Kaiye, CHU Wuli, GUO Zhengtao. Uncertaintyanalysis of effects of manufacturing errors on aerodynamic performance of supersonic cascades[J]. Journal of Aerospace Power, 2024, 39(12): 20220791. (in ChineseLIU Kaiye, CHU Wuli, GUO Zhengtao. Uncertaintyanalysis of effects of manufacturing errors on aerodynamic performance of supersonic cascades[J]. Journal of Aerospace Power, 2024, 39（12）: 20220791. (in Chinese) [2] 郭正涛, 楚武利, 晏松, 等. 加工误差对压气机叶栅气动性能及稳定性影响的数据挖掘[J]. 推进技术, 2022, 43(3): 200576. GUO Zhengtao, CHU Wuli, YAN Song, et al. Data mining on effects of manufacturing error on aerodynamic performance and stability of compressor cascade[J]. Journal of Propulsion Technology, 2022, 43(3): 200576. (in ChineseGUO Zhengtao, CHU Wuli, YAN Song, et al. Data mining on effects of manufacturing error on aerodynamic performance and stability of compressor cascade[J]. Journal of Propulsion Technology, 2022, 43(3): 200576. (in Chinese) [3] GARZON V E, DARMOFAL D L. Impact of geometric variability on axial compressor performance[J]. Journal of Turbomachinery, 2003, 125(4): 692-703. doi: 10.1115/1.1622715 [4] LANGE A, VOGELER K, GU¨MMER V, et al. Introduction of a parameter based compressor blade model for considering measured geometry uncertainties in numerical simulation: ASME Paper GT2009-59937 [R]. New York, US: ASME, 2010. [5] 高丽敏, 蔡宇桐, 曾瑞慧, 等. 叶片加工误差对压气机叶栅气动性能的影响[J]. 推进技术, 2017, 38(3): 525-531. GAO Limin, CAI Yutong, ZENG Ruihui, et al. Effects of blade machining error on compressor cascade aerodynamic performance[J]. Journal of Propulsion Technology, 2017, 38(3): 525-531(in Chinese).GAO Limin, CAI Yutong, ZENG Ruihui, et al. Effects of blade machining error on compressor cascade aerodynamic performance[J]. Journal of Propulsion Technology, 2017, 38(3): 525-531(in Chinese). [6] 郑似玉, 滕金芳, 羌晓青. 叶片加工超差对高压压气机性能影响和敏感性分析[J]. 机械工程学报, 2018, 54(2): 216-224. ZHENG Siyu, TENG Jinfang, QIANG Xiaoqing. Sensitivity analysis of manufacturing variability on high-pressure compressor performance[J]. Journal of Mechanical Engineering, 2018, 54(2): 216-224. (in Chinese doi: 10.3901/JME.2018.02.216ZHENG Siyu, TENG Jinfang, QIANG Xiaoqing. Sensitivity analysis of manufacturing variability on high-pressure compressor performance[J]. Journal of Mechanical Engineering, 2018, 54(2): 216-224. (in Chinese) doi: 10.3901/JME.2018.02.216 [7] 郑似玉, 滕金芳, 羌晓青. 轮廓度加工超差对压气机气动性能影响的数值研究[J]. 科学技术与工程, 2016, 16(29): 317-320. ZHENG Siyu, TENG Jinfang, QIANG Xiaoqing. Numerical investigation of profile variability on axial compressor flow field performance[J]. Science Technology and Engineering, 2016, 16(29): 317-320. (in ChineseZHENG Siyu, TENG Jinfang, QIANG Xiaoqing. Numerical investigation of profile variability on axial compressor flow field performance[J]. Science Technology and Engineering, 2016, 16(29): 317-320. (in Chinese) [8] 莫喻钦, 楚武利, 刘铠烨, 等. 位置度偏差对动叶气动性能影响的不确定性研究[J]. 航空动力学报, 2025, 40(4): 20230477. MO Yuqin, CHU Wuli, LIU Kaiye, et al. Uncer-tainty research of effects of position deviation on aerodynamic performance of rotor[J]. Journal of Aerospace Power, 2025, 40(4): 20230477. (in ChineseMO Yuqin, CHU Wuli, LIU Kaiye, et al. Uncer-tainty research of effects of position deviation on aerodynamic performance of rotor[J]. Journal of Aerospace Power, 2025, 40（4）: 20230477. (in Chinese) [9] SCHULZ H D, GALLUS H D. Experimental investigation of the three-dimensional flow in an annular compressor cascade[J]. Journal of Turbomachinery, 1988, 110(4): 467-478. doi: 10.1115/1.3262220 [10] 姬田园, 楚武利, 张皓光, 等. 基于数据驱动的扭转度偏差对压气机性能的影响[J]. 航空学报, 2024, 45(19): 629938. JI Tianyuan, CHU Wuli, ZHANG Haoguang, et al. Effect of data-driven twist deviation on compressor performance[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 629938. (in ChineseJI Tianyuan, CHU Wuli, ZHANG Haoguang, et al. Effect of data-driven twist deviation on compressor performance[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 629938. (in Chinese) [11] 姬田园, 楚武利, 张皓光, 等. 真实安装角偏差影响压气机性能的不确定性量化[J]. 航空动力学报, 2024, 39(10): 20220858. JI Tianyuan, CHU Wuli, ZHANG Haoguang, et al. Uncertainty quantification of real stagger angle deviation affecting compressor performance[J]. Journal of Aerospace Power, 2024, 39(10): 20220858. (in ChineseJI Tianyuan, CHU Wuli, ZHANG Haoguang, et al. Uncertainty quantification of real stagger angle deviation affecting compressor performance[J]. Journal of Aerospace Power, 2024, 39（10）: 20220858. (in Chinese) [12] 但玥, 高丽敏, 余华蔚, 等. 考虑偏峰统计特征的压气机叶栅前缘半径加工误差不确定性量化研究[J]. 航空学报, 2024, 45(19): 630366. DAN Yue, GAO Limin, YU Huawei, et al. Unce-rtainty quantification research considering the statistical characteristics of skewness and kurtosis in l-eading-edge radius machining error of compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 630366.(in ChineseDAN Yue, GAO Limin, YU Huawei, et al. Unce-rtainty quantification research considering the statistical characteristics of skewness and kurtosis in l-eading-edge radius machining error of compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45（19）: 630366.(in Chinese) [13] AHLFELD R, BELKOUCHI B, MONTOMOLI F. SAMBA: sparse approximation of moment-based arbitrary polynomial chaos[J]. Journal of Computational Physics, 2016, 320: 1-16. doi: 10.1016/j.jcp.2016.05.014 [14] AHLFELD R, MONTOMOLI F. A single formulation for uncertainty propagation in turbomachinery: SAMBA PC[J]. Journal of Turbomachinery, 2017, 139(11): 111007. doi: 10.1115/1.4037362 [15] 尤付浩, 李相君, 鲁庆, 等. 基于二次流控制规律的非轴对称端壁造型优化设计[J]. 航空动力学报, 2024, 39(2): 20220215. YOU Fuhao, LI Xiangjun, LU Qing, et al. Non-axisymmetric endwall based on secondary flow control law modeling optimization design[J]. Journal of Aerospace Power, 2024, 39(2): 20220215. (in ChineseYOU Fuhao, LI Xiangjun, LU Qing, et al. Non-axisymmetric endwall based on secondary flow control law modeling optimization design[J]. Journal of Aerospace Power, 2024, 39(2): 20220215. (in Chinese) [16] 郭正涛, 楚武利, 姬田园, 等. 端壁倒圆半径误差对高负荷静叶栅性能影响的不确定性分析[J]. 航空动力学报, 2021, 36(10): 2173-2185. GUO Zhengtao, CHU Wuli, JI Tianyuan, et al. Uncertainty analysis of effects of end wall fillet radius error on high-load stator cascade performance[J]. Journal of Aerospace Power, 2021, 36(10): 2173-2185. (in ChineseGUO Zhengtao, CHU Wuli, JI Tianyuan, et al. Uncertainty analysis of effects of end wall fillet radius error on high-load stator cascade performance[J]. Journal of Aerospace Power, 2021, 36(10): 2173-2185. (in Chinese) [17] 姬田园, 楚武利, 郭正涛, 等. 一种叶片截面几何特征参数的获取方法: CN115168986A[P]. 2022-10-11. [18] 中国航空工业总公司. 叶片叶型的标志、公差与叶身表面粗糙度: HB5647 [S]. 北京: 中国航空工业总公司, 1999: 15-25. [19] LANGE A, VOIGT M, VOGELER K, et al. Probabilistic CFD simulation of a high-pressure compressor stage taking manufacturing variability into account: ASME Paper GT2010-22484 [R] New York, US: ASME, 2010. [20] LANGE A, VOIGT M, VOGELER K, et al. Impact of manufacturing variability on multistage high-pressure compressor performance[J]. Journal of Engineering for Gas Turbines and Power, 2012, 134(11): 417-426. [21] 姬田园, 楚武利, 张振华, 等. 叶片厚度偏差对转子性能影响的不确定性分析[J]. 航空动力学报, 2024, 39(11): 20220203. JI Tianyuan, CHU Wuli, ZHANG Zhenhua, et al. Uncertainty analysis of impact of blade thickn-ess deviation on rotor performance[J]. Journal of Aerospace Power, 2024, 39(11): 20220203. (in ChineseJI Tianyuan, CHU Wuli, ZHANG Zhenhua, et al. Uncertainty analysis of impact of blade thickn-ess deviation on rotor performance[J]. Journal of Aerospace Power, 2024, 39（11）: 20220203. (in Chinese) [22] 高丽敏, 王浩浩, 黄维娜, 等. 压气机叶片加工偏差的不确定性效应研究进展[J]. 航空学报, 2024, 45(19): 630386. GAO Limin, WANG Haohao, HUANG Weina, et al. Research progress on uncertainty effect of compressor blade machining deviation[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 630386. (in ChineseGAO Limin, WANG Haohao, HUANG Weina, et al. Research progress on uncertainty effect of compressor blade machining deviation[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45（19）: 630386. (in Chinese) [23] 熊芬芬, 王瑞利, 吴晓军, 等. 不确定性量化方法及其应用[M]. 北京: 科学出版社, 2022. XIONG Fenfen, WANG Ruili, WU Xioajun, et al. Method and application of uncertainty quantification[M]. Beijing: Science Press, 2022. (in ChineseXIONG Fenfen, WANG Ruili, WU Xioajun, et al. Method and application of uncertainty quantification[M]. Beijing: Science Press, 2022. (in Chinese) [24] 熊芬芬, 陈江涛, 任成坤, 等. 不确定性传播的混沌多项式方法研究进展[J]. 中国舰船研究, 2021, 16(4): 19-36. XIONG Fenfen, CHEN Jiangtao, REN Chengkun, et al. Recent advances in polynomial chaos method for uncertainty propagation[J]. Chinese Journal of Ship Research, 2021, 16(4): 19-36. (in ChineseXIONG Fenfen, CHEN Jiangtao, REN Chengkun, et al. Recent advances in polynomial chaos method for uncertainty propagation[J]. Chinese Journal of Ship Research, 2021, 16(4): 19-36. (in Chinese) [25] 颜勇, 祝培源, 宋立明, 等. 基于非平稳高斯过程的叶栅加工误差不确定性量化[J]. 推进技术, 2017, 38(8): 1767-1775. YAN Yong, ZHU Peiyuan, SONG Liming, et al. Uncertainty quantification of cascade manufacturing error based non-stationary Gaussian process[J]. Journal of Propulsion Technology, 2017, 38(8): 1767-1775. (in ChineseYAN Yong, ZHU Peiyuan, SONG Liming, et al. Uncertainty quantification of cascade manufacturing error based non-stationary Gaussian process[J]. Journal of Propulsion Technology, 2017, 38(8): 1767-1775. (in Chinese) [26] 王浩浩, 高丽敏, 杨光, 等. 一种鲁棒的数据驱动不确定性量化方法及在压气机叶栅中的应用[J]. 航空学报, 2023, 44(17): 122-134. WANG Haohao, GAO Limin, YANG Guang, et al. Robust data-driven uncertainty quantification method and its application in compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 122-134. (in ChineseWANG Haohao, GAO Limin, YANG Guang, et al. Robust data-driven uncertainty quantification method and its application in compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 122-134. (in Chinese) [27] 熊芬芬. 工程概率不确定性分析方法[M]. 北京: 科学出版社, 2015. XIONG Fenfen. Analysis method of engineering probability uncertainty[M]. Beijing: Science Press, 2015. (in ChineseXIONG Fenfen. Analysis method of engineering probability uncertainty[M]. Beijing: Science Press, 2015. (in Chinese) [28] 楚武利, 何旭东, 杨吉博, 等. 叶片单一与耦合误差对轴流压气机性能的影响[J]. 航空动力学报, 2024, 39(11): 20220941. CHU Wuli, HE Xudong, YANG Jibo, et al. Eff-ects of blade single and coupling errors on axial flow compressor performance[J]. Journal of Aerospace Power, 2024, 39(11): 20220941. (in ChineseCHU Wuli, HE Xudong, YANG Jibo, et al. Eff-ects of blade single and coupling errors on axial flow compressor performance[J]. Journal of Aerospace Power, 2024, 39（11）: 20220941. (in Chinese) [29] GUO Zhengtao, CHU Wuli, ZHANG Haoguang. A data-driven non-intrusive polynomial chaos for performance impact of high subsonic compressor cascades with stagger angle and profile errors[J]. Aerospace Science and Technology, 2022, 129: 107802. doi: 10.1016/j.ast.2022.107802 [30] 郑似玉, 滕金芳, 羌晓青. 压气机叶片扭转度加工超差分析与研究[J]. 节能技术, 2017, 35(2): 99-102, 112. ZHENG Siyu, TENG Jinfang, QIANG Xiaoqing. Numerical research of twisted variability on axial compressor performance[J]. Energy Conservation Technology, 2017, 35(2): 99-102, 112. (in Chinese doi: 10.3969/j.issn.1002-6339.2017.02.001ZHENG Siyu, TENG Jinfang, QIANG Xiaoqing. Numerical research of twisted variability on axial compressor performance[J]. Energy Conservation Technology, 2017, 35(2): 99-102, 112. (in Chinese) doi: 10.3969/j.issn.1002-6339.2017.02.001 [31] CHU Wuli, LI Xiangjun, WU Yanhui, et al. Reduction of end wall loss in axial compressor by using non-axisymmetric profiled end wall: a new design approach based on end wall velocity modification[J]. Aerospace Science and Technology, 2016, 55: 76-91. doi: 10.1016/j.ast.2016.05.011 [32] LI Xiangjun, CHU Wuli, WU Yanhui. Numerical investigation of inlet boundary layer skew in axial-flow compressor cascade and the corresponding non-axisymmetric end wall profiling[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2014, 228(6): 638-656. doi: 10.1177/0957650914532264 [33] 陈懋章. 粘性流体动力学基础[M]. 北京: 高等教育出版社, 2002. CHEN Maozhang. Fundamentals of viscous fluid dynamics[M]. Beijing: Higher Education Press, 2002. (in ChineseCHEN Maozhang. Fundamentals of viscous fluid dynamics[M]. Beijing: Higher Education Press, 2002. (in Chinese) -
点击查看大图
计量
- 文章访问数: 484
- HTML浏览量: 381
- PDF量: 25
- 被引次数: 0