Numerical analysis of effect of gas-solid coupled design on oblique impeller performances
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摘要: 为了获得在设计工况下性能最佳的叶型,提出一种三维单向气-固耦合迭代设计方法。对三维气动设计得到的热态叶型(记为RT)进行单向气-固耦合计算,获得设计点流场特性和热态叶型变形量。采用基于面积平均的三维插值造型方法,分别获得进行机匣处理和不进行机匣处理的冷态叶轮(分别记为RC和RC-tip)。对冷热态叶轮流场的数值分析结果表明:与热态叶轮相比,冷态叶轮在设计转速下堵塞点流量提高1.93%;冷态叶轮的叶片最小负荷下降约30%;在低转速下,冷态叶轮的性能曲线优于热态叶轮;说明通过该设计流程得到的冷态叶轮在叶片负荷和流通能力等方面实现了优化。Abstract: A one-way three dimensional gas-solid coupled design method was proposed to obtain the optimized performance blade profile at the design point. The original thermal state blade profile (denoted as RT) designed by the aerodynamics was used for calculating the flow field characteristics and deformation through one way coupled method. Then two revised cold state blade profiles with and without casing treatment (denoted as RC and RC-tip) through an area-averaged 3D interpolation modeling method were obtained. Results indicated that the flow rate of RC-tip impeller at choke point improved 1.93% under designed speed. The minimum blade loading also dropped by 30%. At low speed, performance of RC-tip was obviously better than that of RT, proving that the coupled design method optimized the blade loading and flow capacity of oblique impeller.
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[1] MUSGRAVE D S,PLEHN N J.Mixed-flow compressor stage design and test results with a pressure ratio of 3:1[J].Journal of Turbomachinery,1987,109(4):513-519. [2] ELMENDORF W,KURZ H,GALLUS H E.Design and experimental investigation of a mixed-flow supersonic compressor stage[R].ASME Paper 95-GT-0379,1995. [3] 高星,刘宝杰.高比转速斜流叶轮流场分析[J].航空动力学报,2008,23(5):889-894.GAO Xing,LIU Baojie.Analysis of flow in a high specific speed mixed flow compressor[J].Journal of Aerospace Power,2008,23(5):889-894.(in Chinese) [4] 任众,刘振侠,黄健.斜流压气机扩压器设计和流场的数值模拟研究[J].航空计算技术,2011,41(4):35-44.REN Zhong,LIU Zhenxia,HUANG Jian.Design and numerical investigation of mixed-flow compressor diffuser[J].Aeronautical Computing Technique,2011,41(4):35-44.(in Chinese) [5] 张大义,洪杰,马艳红.高结构效率的斜流压气机结构设计[J].航空动力学报,2013,28(4):866-871.ZHANG Dayi,HONG Jie,MA Yanhong.Novel structural design of mixed-flow compressor with high structural efficiency[J].Journal of Aerospace Power,2013,28(4):866-871.(in Chinese) [6] EISENLOHR G,BENFER F E.Aerodynamic design and investigation of a mixed flow compressor[R].Advisory Group for Aerospace Research and Development,AGARD-CP468,1993. [7] MONIG R,ELMENDOR F W.Design and rotor performance of a 5:1 mixed-flow supersonic compressor[J].Journal of Turbomachinery,1993,155(3):565-572. [8] 陶胜,周正贵,严欣.三维环境下离心-斜流压气机二维叶型优化设计[J].航空动力学报,2014,29(12):2965-2972.TAO Sheng,ZHOU Zhengxin,YAN Xin.Optimization design of centrifugal/oblique flow compressor two dimensional blade profiles in three dimensional environment[J].Journal of Aerospace Power,2014,29(12):2965-2972.(in Chinese) [9] 张小伟,王延荣,张潇.涡轮机械叶片的流固耦合数值计算方法[J].航空动力学报,2009,24(7):1622-1626.ZHANG Xiaowei,WANG Yanrong,ZHANG Xiao.Numerical method for fluid-structure interaction in turbomachinery bladings[J].Journal of Aerospace Power,2009,24(7):1622-1626.(in Chinese) [10] 王征,吴虎,史亚锋.基于CFD_CSD技术的压气机叶片流固耦合及颤振分析[J].航空动力学报,2011,26(5):1077-1084.WANG Zheng,WU Hu,SHI Yafeng.Fluid-structure interaction and flutter analysis ofcompressor blade based on CFD_CSD[J].Journal of Aerospace Power,2011,26(5):1077-1084.(in Chinese) [11] HAMID H,LAN W,Micheal C.Effect of blade deformation on the performance of a high flow coefficiency mixed flow impeller[J].Journal of Turbomachinery,2013,137(12):1005-1009. [12] WIESNER F J.A review of slip factors for centrifugal impellers[J].Journal of Engineering for Power,1967,89(4):558-572. [13] TTEODOR W,BACKSTROM V.A Unified correlation for slip factor in centrifugal impellers[J].Journal of Turbomachinery,2005,128(1):1-10. [14] PAUER R,MULLER N.Impeller design for radial and mixed-flow compressors[R].ASME Paper IMECE2004-61926,2004. [15] QIU Xuwen,MALLIKARACHCHI C,ANDERSON M.A new slip factor model for axial and radial impellers[R].ASME Paper GT2007-27064,2007. [16] 袁春.斜流叶轮的气动设计和叶片造型[D].西安:西北工业大学,2002.YUAN Chun.Aerodynamics design of diagonal impeller and the blades design[D].Xian:Northwestern Polytechnical University,2002.(in Chinese) [17] 王琦,单鹏.径流及斜流压气机任意曲面叶型长短叶片的造型设计方法[J].航空动力学报,2006,21(4):747-753.WANG Qi,SHAN Peng.Design of radial flow and mixed flow compressor rotor splitter-blades[J].Journal of Aerospace Power,2006,21(4):747-753.(in Chinese) [18] 冀国锋,桂幸民.轴流/离心压气机叶片通用任意中弧造型设计方法[J].航空动力学报,2009,24(1):150-156.JI Guofeng,GUI Xingmin.A blading design method for axial/centrifugal compressor air foils using arbitrary camber lines[J].Journal of Aerospace Power,2009,24(1):150-156.(in Chinese) [19] 樊小莉,刘云飞,郭然.轴流压气机转子叶片的流固耦合分析[J].工程热物理学报,2012,33(2):218-221.FAN Xiaoli,LIU Yunfei,GUO Ran.The research and application on coupled fluid-structure simulation of compressor rotor[J].Journal of Engineering Thermophysics,2012,33(2):218-221.(in Chinese)
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