某涡轮静叶环形叶栅气动性能的试验研究
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摘要
针对SOFC燃料电池和微型蒸汽透平联合循环发电装置开发了涡轮静叶片,该叶片采用多个后加载型线堆叠而成,并在风洞试验台上测试其气动性能,研究了不同冲角和不同马赫数条件下的流动特征。同时,采用计算流体动力学的方法对试验模型在相同的边界条件下气动性能进行了数值研究。研究表明:马赫数在0.5～0.9的范围内,随着马赫数的增加,能量损失减小,同时出口气流角度也略有减少;正负冲角对带有后部加载特征的叶栅的气动性能影响较小。
This paper is to develop a turbine stator blade for power generation system with a SOFC and Micro-steam turbine combined cycle.The blade is stacked with a number of Aft-loading profiles,and the aerodynamic performance is tested in wind tunnel.The flow characteristics at different incidence angles and different Mach numbers are investigated.3 D numerical simulation of the experimental model is also conducted under the same boundary conditions.The results indicate that:the Mach number is in the range of 0.5～0.9,energy loss decreases as the Mach number increases,and the exit airflow angle decreases slightly.The positive or negative incidence angle has little influence on the aerodynamic performance of the Aft-loading cascade.
This paper is to develop a turbine stator blade for power generation system with a SOFC and Micro-steam turbine combined cycle.The blade is stacked with a number of Aft-loading profiles,and the aerodynamic performance is tested in wind tunnel.The flow characteristics at different incidence angles and different Mach numbers are investigated.3 D numerical simulation of the experimental model is also conducted under the same boundary conditions.The results indicate that:the Mach number is in the range of 0.5～0.9,energy loss decreases as the Mach number increases,and the exit airflow angle decreases slightly.The positive or negative incidence angle has little influence on the aerodynamic performance of the Aft-loading cascade.
引文
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[13] 高杰,郑群,岳国强,等.燃气轮机涡轮叶顶间隙气热技术研究进展[J].航空学报,2017,38(9):521019-1-521019-22.GAO Jie,ZHENG Qun,YUE Guo-qiang,et al.Research progress on turbine blade tip aerodynamics and heat transfer technology for gas turbine[J].Acta aeronautica et astronautica sinica,2017,38(9):521019-1-521019-22.
[14] 朱兰,张剑,卿雄杰.高压涡轮导向器扇形叶栅试验及改进设计验证[J].燃气涡轮试验与研究,2014,27(5):19-24.ZHU Lan,ZHANG Jian,QING Xiong-jie.Experiment and improved design verification on the sector cascade of high pressure turbine nozzle[J].Gas Turbine Experiment and Research,2014,27(5):19-24.
[15] 陈升,邱超,宋华芬.涡轮平面叶栅变几何试验研究[J].热能动力工程,2011,26(1):7-12.CHEN Sheng,QIU Chao,SONG Hua-fen.experimental study of a turbine planar cascade with variable geometry.[J].Journal of Engineering for Thermal Energy and Power,2011,26(1):7-12.
[2] 王玉璋,丰镇平,赵亚芳.极小展弦比后加载叶栅气动特性三维数值分析和实验[J].上海交通大学学报,2003,37(7);1031-1034.WANG Yu-zhang,FENG Zhen-ping,ZHAO Ya-fang.3D numerical simulation and experimental study on aerodynamic characteristics of ultra low-aspect ratio cascades of after-loaded type[J].Journal of Shanghai Jiaotong University,2003,37(7):1031-1034.
[3] 张华良,谭春青,陈海生.平面涡轮叶栅内旋涡结构的试验研究[J].机械工程学报,2010,46(12):155-160.ZHANG Hua-liang,TAN Chun-qing,CHEN Hai-sheng.Experimental investigation on vortex structures in linear turbine cascades[J].Journal of Mechanical Engineering,2010,46(12):155-160.
[4] 戴斌,刘庆龙,戴韧.进口气流冲角对环形叶栅端壁气膜冷却效率的影响[J].燃气轮机技术,2010,23(2):43-47.DAI Bin,LIU Qing-long,DAI Ren.The influence of incidence angle on the endwall film cooling effectiveness of the annular cascade[J].Gas Turbine Technology,2010,23(2):43-47.
[5] 周逊,王振峰,王祥锋.冲角变化对涡轮静叶栅流场的影响[J].实验流体力学,2009,23(4):11-14.ZHOU Xun,WANG Zhen-feng,WANG Xiang-feng.Effect of incidence on the flow field in turbine static cascade[J].Journal of Experiments in Fluid Mechanics,2009,23(4):11-14.
[6] 凌代军,王晖,马昌友.低雷诺数亚音速扩压平面叶栅试验[J].航空动力学报,2013,28(1):171-178.LING Dai-jun,WANG Hui,MA Chang-you.Subsonic compressor plane cascade experiment at low Reynolds Number[J].Journal of Aerospace Power,2013,28(1):171-178.
[7] 乔渭阳,曾军,曾文演.气膜孔喷气对涡轮气动性能影响的试验研究[J].推进技术,2007,28(1):14-19.QIAO Wei-yang,ZENG Jun,ZENG Wen-yan.Experimental studies for the aerodynamic loss in gas turbine with film cooling[J].Journal of Propulsion Technology,2007,28(1);14-19.
[8] 石玉文,顾忠华,韩万龙.大焓降静叶片设计思想的低速试验验证[J].汽轮机技术,2013,55(1):27-30.SHI Yu-wen,GU Zhong-hua,HAN Wan-long.Low-speed experimental verification on high-loading turbine blade design idea[J].Turbine Technology,2013,55(1);27-30.
[9] 梁晨,牛夕莹,林枫.某型涡轮动叶气动性能的实验研究[J].热能动力工程,2012,27(4):405-410.LIANG Chen,NIU Xi-ying,LIN Feng.Experimental study of the aerodynamic performance of the rotating blades of a turbine[J].Journal of Engineering for Thermal Energy and Power,2012,27(4):405-410.
[10] 曾军,向传国,程信华.跨声速涡轮叶栅三维流场的数值模拟[J].航空动力学报,2007,22(11):1915-1920.ZHENG Jun,XIANG Chuan-guo,CHENG Xin-hua.Numerical simulation of the three-dimensional flow field of transonic turbine cascade[J].Journal of Aerospace Power,2007,22(11):1915-1920.
[11] 杨其国,王祥峰,石玉文,等.高负荷涡轮叶栅气动性能试验[J].航空动力学报,2011,26(12):2722-2730.YANG Qi-guo,WANG Xiang-feng,SHI Yu-wen,et al.Experiment on aerodynamic performance of turbine static cascade with high aerodynamic loading[J].Journal of Aerospace Power,2011,26(12):2722-2730.
[12] 刘火星,周琨,邹正平.涡轮叶栅尾迹对二次流影响的试验研究[J].工程热物理学报,2009,30(3):397-401.LIU Huo-xing,ZHOU Kun,ZOU Zheng-ping.The investigation for influence of wake on secondary flow in a turbine cascade[J].Journal of Engineering Thermophysics,2009,30(3):397-401.
[13] 高杰,郑群,岳国强,等.燃气轮机涡轮叶顶间隙气热技术研究进展[J].航空学报,2017,38(9):521019-1-521019-22.GAO Jie,ZHENG Qun,YUE Guo-qiang,et al.Research progress on turbine blade tip aerodynamics and heat transfer technology for gas turbine[J].Acta aeronautica et astronautica sinica,2017,38(9):521019-1-521019-22.
[14] 朱兰,张剑,卿雄杰.高压涡轮导向器扇形叶栅试验及改进设计验证[J].燃气涡轮试验与研究,2014,27(5):19-24.ZHU Lan,ZHANG Jian,QING Xiong-jie.Experiment and improved design verification on the sector cascade of high pressure turbine nozzle[J].Gas Turbine Experiment and Research,2014,27(5):19-24.
[15] 陈升,邱超,宋华芬.涡轮平面叶栅变几何试验研究[J].热能动力工程,2011,26(1):7-12.CHEN Sheng,QIU Chao,SONG Hua-fen.experimental study of a turbine planar cascade with variable geometry.[J].Journal of Engineering for Thermal Energy and Power,2011,26(1):7-12.