Statistics on aerodynamic sensitivities of blade geometric errors for transonic compressor rotor
-
摘要:
为了研究跨声速压气机转子的气动性能对不同类型几何误差的敏感性，以NASA Rotor 37为研究对象，采用非均匀有理B样条（NURBS）曲面及遗传算法实现三维叶型曲面重构。考虑了26个几何误差模型。采用拉丁超立方结合蒙特卡洛模拟生成了800个样本，通过定常CFD数值计算获得叶型气动特性及流场结构，采用Spearman秩相关及期望值分析不同工况下几何误差与气动性能之间的非线性关系。对不同工况下效率最敏感的几何误差模型进行了流动机理分析。统计分析结果表明：堵塞工况下，叶中前缘轮廓度对效率有最显著的消极影响，叶尖吸力面轮廓度对压比有最显著的消极影响。最高效率工况下，叶中吸力面轮廓度对效率和压比都有着最显著的消极影响。近失速工况下，叶尖前缘轮廓度对效率有最显著的消极影响，而叶中尾缘轮廓度对压比有着最显著的积极影响。
-
关键词:
- 几何误差 /
- 跨声速压气机转子 /
- 非均匀有理B样条（NURBS）曲面 /
- 气动敏感性 /
- 相关性分析
Abstract:In order to study the sensitivity of the aerodynamic performance of a transonic compressor rotor to different types of geometric errors, NASA Rotor 37 was selected as the research object. The non-uniform rational B-splines (NURBS) surface algorithm and genetic algorithm were used to parameterize the three-dimensional blade surface. A total of 26 geometric errors, including the sweeping error and skewing error, were considered and extracted for the 3D rotor blade. 800 samples were generated by uniform Latin hypercube sampling in association with Monte Carlo algorithm. The loss characteristic and flow structure of Rotor 37 were obtained by steady CFD numerical simulation. Spearman rank correlation and expectation curve analysis were used to investigate the nonlinear relationship between geometric deviations and aerodynamic parameters at two typical working conditions. The flow mechanism analysis was carried out on the most sensitive geometric error model of efficiency under different working conditions. Results indicated that leading-edge profile factor of midspan had the greatest negative effects on rotor efficiency; while suction profile factor near shroud was most negatively correlated with pressure ratio at choke point. As for peak efficiency point, suction profile factor of midspan had the most obvious negative influence on rotor efficiency and pressure ratio. Regarding to near stall point, suction profile factor of midspan had great negative correlation with rotor efficiency. Trailing-edge profile factor of midspan was great positively correlated with pressure ratio.
-
图 1 单通道网格及叶顶间隙蝶形拓扑示意图
Figure 1. Schematic diagram of single-channel grid set and the butterfly topology at tip clearance
图 3 叶片几何离散点参数化流程图
Figure 3. Flow chart of blade geometry discrete points parameterization
图 4 NURBS曲面重构过程及重构前后叶片对比
Figure 4. Process of NURBS surface reconstruction and comparison between reconstructed blade and original one
图 14 Spearman秩相关系数柱状图（堵塞工况）
Figure 14. Spearman rank correlation coefficient histogram （choke）
图 15 Spearman秩相关系数柱状图（最高效率工况）
Figure 15. Spearman rank correlation coefficient histogram （peak efficiency）
图 16 Spearman秩相关系数柱状图（近失速工况）
Figure 16. Spearman rank correlation coefficient histogram （near stall）
图 17 性能参数- Flp,h样本分布（堵塞工况）
Figure 17. Performance parameters-Flp,h sample distribution （choke）
图 18 压比、效率随26个几何误差变化期望值曲线（堵塞工况）
Figure 18. Expectation curve of variation of π and η with 26 geometric deviations （choke）
图 19 压比、效率随26个几何误差变化期望值曲线（最高效率工况）
Figure 19. Expectation curve of variation of π and η with 26 geometric deviations （peak efficiency）
图 20 压比、效率随26个几何误差变化期望值曲线（近失速工况）
Figure 20. Expectation curve of variation of π and η with 26 geometric deviations （near stall）
图 23 叶中流场平均马赫数云图（堵塞工况）
Figure 23. Mean Mach number contour of midspan flow field （choke）
图 24 弦向叶表静压系数分布（最高效率工况）
Figure 24. Cp distribution of chordwise blade surface（peak efficiency）
图 25 叶表动能损失厚度分布（最高效率工况）
Figure 25. Kinetic energy loss thickness distribution （peak efficiency）
图 26 叶中流场平均马赫数云图（最高效率工况）
Figure 26. Mean Mach number contour of midspan flow field（peak efficiency）
图 27 弦向叶表静压系数分布（近失速工况）
Figure 27. Cp distribution of chordwise blade surface （near stall）
表 1 NASA Rotor 37的主要设计参数
Table 1. Main design parameters of NASA Rotor 37
参数 数值 叶片数 36 转速/（r/min） 17188 叶尖速度/（m/s） 454.14 展弦比 1.19 进口轮毂比 0.7 叶顶间隙/mm 0.356 
下载: 导出CSV
表 2 网格无关性分析
Table 2. Grid independence analysis
参数 网格1 网格2 网格3 网格数 517656 1032493 1485763 压比 2.019 2.027 2.029 等熵效率/% 86.95 87.52 87.59 流量/（kg/s） 20.55 20.79 20.82
下载: 导出CSV
-
[1] KLAPPROTH J. Approximate relative-total-pressure losses of an infinite cascade of supersonic blades with finite leading-edge thickness[J]. NACA RM E9L21, 1950. [2] BAMMERT K,SANDSTEDE H. Influences of manufacturing tolerances and surface roughness of blades on the performance of turbines[J]. Journal of Engineering for Power,1976,98(1): 29-36. doi: 10.1115/1.3446107 [3] GOODHAND M, MILLER R, LUNG H W. The sensitivity of 2D compressor incidence range to In-service geometric variation[R]. Copenhagen, Denmark: ASME Turbo Expo: Turbine Technical Conference and Exposition, 2012. [4] 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) [5] 高丽敏,蔡宇桐,郝燕平,等. 加工误差对压气机叶片气动性能影响试验研究[J]. 推进技术,2017,38(8): 1761-1766.GAO Limin,CAI Yutong,HAO Yanping,et al. Experimental investigation on aerodynamic performance of compressor blade considering manufacturing error[J]. Journal of Propulsion Technology,2017,38(8): 1761-1766. (in Chinese) [6] 陈为雄,王掩刚,马峰,等. 超声速来流基元叶型前缘加工误差气动敏感性分析[J]. 推进技术,2019,40(10): 2235-2242.CHEN Weixiong,WANG Yangang,MA Feng,et al. Aerodynamic sensitivity analysis of manufacturing errors for leading edge of supersonic elementary blade profile[J]. Journal of Propulsion Technology,2019,40(10): 2235-2242. (in Chinese) [7] WANG Hao,WU Yadong,WANG Yangang,et al. Evolution of the flow instabilities in an axial compressor rotor with large tip clearance: an experimental and URANS study[J]. Aerospace Science and Technology,2020,96: 105557.1-105557.13. [8] ZHOU Kai,ZHOU Chao. Unsteady effects of vortex interaction on tip leakage vortex breakdown and its loss mechanism[J]. Aerospace Science and Technology,2018,82/83: 363-371. doi: 10.1016/j.ast.2018.09.019 [9] LI Jichao,GENG Shaojuan,DU Juan,et al. Circumferentially propagating characteristic dominated by unsteady tip leakage flow in axial flow compressors[J]. Aerospace Science and Technology,2019,85: 529-543. doi: 10.1016/j.ast.2018.11.058 [10] YANG B,GU C G. The effects of radially distorted incident flow on performance of axial-flow fans with forward-skewed blades[J]. Journal of Turbomachinery,2013,135(1): 011039.1-011039.12. [11] ZENGER F,HEROLD G,BECKER S. Acoustic characterization of forward- and backward-skewed axial fans under increased inflow turbulence[J]. AIAA Journal,2017,55(4): 1241-1250. doi: 10.2514/1.J055383 [12] HE Chen,MA Yunfei,LIU Xiaohua,et al. Aerodynamic instabilities of swept airfoil design in transonic axial-flow compressors[J]. AIAA Journal,2018,56(5): 1878-1893. doi: 10.2514/1.J056053 [13] DI Zhang,MA Jiaobin,QI Jing. Numerical study of unsteady flow and exciting force for swept turbomachinery blades[J]. Thermal Science,2016,20(Suppl.3): 669-676. [14] ROBERTS W B,ARMIN A,KASSASEYA G,et al. The effect of variable chord length on transonic axial rotor performance[J]. Journal of Turbomachinery,2002,124(3): 351-357. doi: 10.1115/1.1459734 [15] GIEBMANNS A, SCHNELL R, STEINERT W, et al. Analyzing and optimizing geometrically degraded transonic fan blades by means of 2D and 3D simulations and cascade measurements[R]. Copenhagen, Denmark: ASME Turbo Expo: Power for Land, Sea and Air, 2012. [16] ANANTHAKRISHNAN K,GOVARDHAN M. Influence of fillet shapes on secondary flow field in a transonic axial flow turbine stage[J]. Aerospace Science and Technology,2018,82/83: 425-437. doi: 10.1016/j.ast.2018.08.040 [17] REID L, MOORE R. Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor[R]. NASA-TP-1337, 1978. [18] SUDER K L. Experimental investigation of the flow field in a transonic, axial flow compressor with respect to the development of blockage and loss[D]. Cleveland, US: Case Western Reserve University, 1996. [19] MOHSEN M,OWIS F M,HASHIM A A. The impact of tandem rotor blades on the performance of transonic axial compressors[J]. Aerospace Science and Technology,2017,67: 237-248. doi: 10.1016/j.ast.2017.04.019 [20] ZHENG S Y, TENG J F, WU Y, et al. Impact of nonuniform stagger angle distribution on high-pressure compressor rotor performance[R]. ASME Paper GT2018-76067, 2018. [21] 程超,吴宝海,郑海,等. 叶片加工误差对压气机性能的影响[J]. 航空学报,2020,41(2): 28-38.CHENG Chao,WU Baohai,ZHENG Hai,et al. Effect of blade machining errors on compressor performance[J]. Acta Aeronautica et Astronautica Sinica,2020,41(2): 28-38. (in Chinese) [22] 耿少娟,张小玉,丁林超,等. 转子叶片加工误差对1.5级跨声速压气机气动性能的影响[J]. 推进技术,2021,42(1): 139-148.GENG Shaojuan,ZHANG Xiaoyu,DING Linchao,et al. Effects of rotor blade manufacturing variability on 1.5 stage transonic compressor aerodynamic performance[J]. Journal of Propulsion Technology,2021,42(1): 139-148. (in Chinese) [23] SPALART P, ALLMARAS S. A one-equation turbulence model for aerodynamic flows[R]. AIAA-1992-439, 1992. [24] LU Hanan,YANG Zhe,PAN Tianyu,et al. Non-uniform stator loss reduction design strategy in a transonic axial-flow compressor stage under inflow distortion[J]. Aerospace Science and Technology,2019,92: 347-362. doi: 10.1016/j.ast.2019.06.015 [25] SONG Liming,GUO Zhendong,LI Jun,et al. Research on metamodel-based global design optimization and data mining methods[J]. Journal of Engineering for Gas Turbines and Power,2016,138(9): 092604.1-092604.14. [26] KUMAR J,ABIRAMI S. Aspect-based opinion ranking framework for product reviews using a Spearman’s rank correlation coefficient method[J]. Information Sciences,2018,460/461: 23-41. doi: 10.1016/j.ins.2018.05.003 [27] JEONG J,HUSSAIN F. On the identification of a vortex[J]. Journal of Fluid Mechanics,1995,285: 69-94. doi: 10.1017/S0022112095000462 [28] INOUE M,KUROUMARU M. Structure of tip clearance flow in an isolated axial compressor rotor[J]. Journal of Turbomachinery,1989,111(3): 250-256. doi: 10.1115/1.3262263 -
点击查看大图
计量
- 文章访问数: 492
- HTML浏览量: 216
- PDF量: 65
- 被引次数: 0