平面扩压叶栅最佳弯叶片生成线与叶栅折转角的关系

凌敬; 杜鑫; 王松涛; 王仲奇

doi:10.13224/j.cnki.jasp.2015.04.014

平面扩压叶栅最佳弯叶片生成线与叶栅折转角的关系

doi: 10.13224/j.cnki.jasp.2015.04.014

哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001

详细信息

作者简介:
凌敬(1986-),男,河北唐山人,博士生,主要从事叶轮机械气动热力学研究.

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2013-11-06
- 刊出日期: 2015-04-28

Relationship between optimum curved blade generate line and blade camber angle in linear compressor cascade

School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 用优化的方法研究了扩压叶栅最佳弯叶片生成线与叶栅折转角之间的关系,在8个不同叶栅折转角下优化弯叶片生成线的弯角和弯高.积叠线是由两段贝塞尔曲线和一段直线组成,在这种积叠线形式下,相同弯角下弯叶片损失随弯高增大不断减小,弯叶片的最佳弯高为0.5.在相同的叶栅折转角下弯叶片损失随弯角增大先减小后增大,存在最佳弯角使弯叶片总损失最小.随着叶栅折转角增大,弯叶片收益增大.最佳弯角随着叶栅折转角的增加有增大的趋势.在给定计算条件下,最佳弯角与叶栅折转角之间呈类似线性变化规律.
- 弯叶片优化 /
- 平面扩压叶栅 /
- 最佳弯角 /
- 最佳弯高 /
- 叶栅折转角
Abstract: The relationship between the optimum curved blade generate line and blade camber angle in linear compressor cascade was researched by optimization method. Curved angle and curved height of curved blade generate line were optimized at eight different blade camber angles. The stack line was composed of two Bezier curves and a straight line, cascade loss decreases with the increasing curved height at the same curved angle, and the optimum curved height of the curved blade is 0.5. As for an optimum curved angle, at which curved blade total loss is minimal, curved blade loss decreases with increasing curved angle when curved angle is less than curved angle, and loss grows with increasing optimum curved angle when curved angle is larger than optimum curved angle. The benefits of the curved blade improve with increasing blade camber angle. Optimum curved angle increases along with the increasing blade camber angle. The relationship of optimum curved angle and blade camber angle presents a similar linear type.
- optimization of curved blade /
- linear compressor cascade /
- optimum curved angle /
- optimum curved height /
- blade camber angle

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参考文献(18)

[1]	Breugelmans F A E, Carels Y, Demuth M, et al.Influence of dihedral on the secondary flow in a two dimensional compressor cascade[J].Journal of Engineering for Gas Turbine and Power, 1984, 106(3):578-584.
[2]	Breugelmans F A E.Influence of incidence angle on the secondary flow in compressor cascade with different dihedral distribution[R].ISABE Paper 85-7078, 1985.
[3]	Sasaki T, Breugelmans F A E.Comparison of sweep and dihedral effects on compressor cascade performance[J].Journal of Turbomachinery, 1998, 120(2):454-464.
[4]	Fischer A, Riess W, Seume J R.Performance of strongly bowed stators in a 4-stage high speed compressor[R].ASME Paper GT2003-38392, 2003.
[5]	Gallimore S J, Bolger J J, Cumpsty N A, et al.The use of sweep and dihedral in multistage axial flow compressor blading:Part 1 university research and methods development[R].ASME Paper GT-2002-30328, 2002.
[6]	Gallimore S J, Bolger J J, Cumpsty N A, et al.The use of sweep and dihedral in multistage axial flow compressor blading:Part 2 low and high speed designs and test verification[R].ASME Paper GT-2002-30329, 2002.
[7]	钟兢军, 王苇, 苏杰先, 等.稠度对弯曲叶片压气机叶栅特性的影响[J].航空动力学报, 1997, 12(2):163-166. ZHONG Jingjun, WANG Wei, SU Jiexian, et al.Effects of solidity on characteristics of compressor cascade with curved-blade[J].Journal of Aerospace Power, 1997, 12(2):163-166.(in Chinese)
[8]	Wang Z Q, Lai S K, Xu W Y.Aerodynamic calculation of turbine stator cascades with curvilinear leaned blades and some experimental results[R].Baugalore, India:Symposium Paper of 5th ISABE, 1981.
[9]	苏杰先, 王仲奇.叶片的弯扭联合气动成型理论、实验、设计及其应用[J].动力工程, 1992, 12(6):1-6. SU Jiexian, WANG Zhongqi.Profiling of simultaneously vaulted and twisted blades:theory, experiment, design and application[J].Power Engineering, 1992, 12(6):1-6.(in Chinese)
[10]	张永军.扩压叶栅采用弯叶片控制流场结构与改善气动性能的研究[D].哈尔滨:哈尔滨工业大学, 2007. ZHANG Yongjun.Investigation of bowed blade controlling flow field structure and improving aerodynamic performance indiffussion cascade[D].Harbin:Harbin Institute of Technology, 2007.(in Chinese)
[11]	张华良.采用叶片弯/掠及附面层抽吸控制扩压叶栅内涡结构的研究[D].哈尔滨:哈尔滨工业大学, 2007. ZHANG Hualiang.Investigation on application of dihedral/swept blade and boundary layer suction to control vortex configuration in compressor cascades[D].Harbin:Harbin Institute of Technology, 2007.(in Chinese)
[12]	Xing X Q, Zhou S, Zhao X L.Probing into the connotation of sweep aerodynamics of transonic fans and compressors[R].ASME Paper 2001-GT-0352, 2001.
[13]	单鹏, 桂幸民, 周盛, 等.高负荷后掠风扇设计若干基本问题[J].工程热物理学报, 1999, 20(5):576-579. SHAN Peng, GUI Xingmin, ZHOU Sheng, et al.Fundamental considerations on high loading backward swept fan design[J].Journal of Engineering Thermophysics, 1999, 20(5):576-579.(in Chinese)
[14]	邢秀清, 单鹏, 周盛.风扇转子前缘曲线相对掠对性能的影响[J].航空动力学报, 2000, 15(1):39-43. XING Xiuqing, SHAN Peng, ZHOU Sheng.Effects of swept leading edge on performance of fans[J].Journal of Aerospace Power, 2005, 15(1):39-43.(in Chinese)
[15]	Koller U, Monig R, Kustes B, et al.Development of advanced compressor airfoils for heavy-duty gas turbines:Part Ⅰ design and optimization[J].Journal of Turbomachinery, 2000, 122(6):397-405.
[16]	周正贵.高亚声速压气机叶片优化设计[J].推进技术, 2004, 25(1):58-61. ZHOU Zhenggui.Optimization of high subsonic axial compressor blades[J].Journal of Propulsion Technology, 2004, 25(1):58-61.(in Chinese)
[17]	Chung J, Shim J K, Lee D.Shape optimization of high-speed axial compressor blades using 3D N-S flow physics[R].ASME Paper 2001-GT-0594, 2001.
[18]	金东海, 陈佳, 桂幸民.压气机叶栅多点气动优化设计[J].推进技术, 2007, 28(4):367-372. JIN Donghai, CHEN Jia, GUI Xingmin, et al.Multi-point aerodynamic design optimization for compressor cascade airfoils[J].Journal of Propulsion Technology, 2007, 28(4):367-372.(in Chinese)