基于射流襟翼的涡轮平面叶栅流动控制实验

王蒲伟; 乔渭阳; 陈萍萍; 魏佐君

基于射流襟翼的涡轮平面叶栅流动控制实验

西北工业大学动力与能源学院,西安 710072

计量
- 文章访问数: 1696
- HTML浏览量: 2
- PDF量: 610
- 被引次数: 0
出版历程
- 收稿日期: 2011-08-25
- 刊出日期: 2012-07-28

Two-dimensional cascade test on flow control using jet-flap for turbine blades

School of Power and Energy, Northwestern Polytechnical University,Xi'an 710072,China

摘要

摘要: 实验研究了襟翼射流对涡轮叶栅流动的控制,实验测量了某型涡轮叶片压力面尾缘附近由直径为1mm的射流喷口喷射不同流量射流,对不同流动状态下涡轮叶栅流动的影响效果.结果表明:射流襟翼能够有效控制通道内的主流质量流量和流动方向;在进口雷诺数为71742,马赫数为0.048,湍流度为１％状态下,当射流流量达到主流质量流量的4%时,主流质量流量减少了13.32%,气流转折角增大了6.34%;随着射流流量的增大,叶型载荷系数有所降低,同时总压损失系数会增大.
- 射流襟翼 /
- 主流质量流量 /
- 变循环 /
- 气流转折角 /
- Zweifel载荷系数
Abstract: Control of jet-flap on turbine cascade flow was studied.An experiment was conducted to study the impacts of the jet-flap which were blown out by a row of jet holes which were in diameter of 1mm and were near to the trailing edge on the pressure surface of gas turbine blade.The experiment adopted different shapes of jet-flap with different mass flows under various flow conditions.The experiment results show that jet-flap can effectively control the mass flow and the turning angle.When Reynolds number is 71742,Mach number is 0.048,turbulence is 1%,and the jet flow reaches to 4% of the mass flow,the mainstream mass flow is reduced by 13.32%,and the turning angle is increased by 6.34%.Along with the increase of the jet flow,the loading coefficient decreases and the total pressure loss coefficient increases.
- jet-flap /
- mass flow /
- variable cycle /
- turning angle /
- Zweifel loading coefficient

HTML

参考文献(13)

[1]	方昌德.变循环发动机[J].燃气涡轮实验与研究,2004,17(3):1-5. FANG Changde.Variable cycle engines[J].Gas Turbine Experiment and Research,2004,17(3):1-5.(in Chinese)
[2]	朱之丽,李东.变几何涡轮发动机几何调节对性能的影响[J].航空动力学报,1999,14(1):35-38. ZHU Zhili,LI Dong.Influence of geometric variation on performance of VGE[J].Journal of Aerospace Power,1999,14(1):35-38.(in Chinese)
[3]	刘增文,王占学,黄红超,等.变循环发动机性能数值研究[J].航空动力学报,2010,25(6):1310-1315. LIU Zengwen,WANG Zhanxue,HUANG Hongchao,et al.Numerical simulation on performance of variable cycle engines[J].Journal of Aerospace Power,2010,25(6):1310-1315.(in Chinese)
[4]	Byerley A R,Störmer O,James W B.Using gurney flaps to control laminar separation on linear cascade blades .ASME Paper GT2002-30662,2002.
[5]	张军胜,乔渭阳,孙大伟.基于Gurney襟翼的低压涡轮叶栅流动控制实验[J].航空动力学报,2009,24(5):1129-1135. ZHANG Junsheng,QIAO Weiyang,SUN Dawei.Experiment on flow control using Gurney-flaps for a low-pressure turbine cascade[J].Journal of Aerospace Power,2009,24(5):1129-1135.(in Chinese)
[6]	张军胜.低雷诺数涡轮流动损失控制技术实验研究 .西安:西北工业大学,2009. ZHANG Junsheng.Experimental investigation of the flow loss control in the turbine with low Reynolds number .Xi'an:Northwestern Polytechnical University,2009.(in Chinese)
[7]	罗华玲,乔渭阳,许开富.射流襟翼-低压涡轮叶栅主动控制数值研究[J].航空动力学报,2008,23(2):347-354. LUO Hualing,QIAO Weiyang,XU Kaifu.Numerical study of active flow control using jet-flap for a low-pressure turbine cascade[J].Journal of Aerospace Power,2008,23(2):347-354.(in Chinese)
[8]	Stanley M N,Jobn F K.Two-dimensional cascade test of a jet-flap turbine rotor blade .NASA TM X-2183,1971.
[9]	高丽敏,王尚锦,刘波.涡轮叶栅尾缘冷气喷射对主流场干扰的物理模型的研究[J].航空动力学报,1999,14(4):405-408. GAO Limin,WANG Shangjin,LIU Bo.2-D model for influence of trailing edge ejection on aerodynamic performance of a turbine cascade[J].Journal of Aerospace Power,1999,14(4):405-408.(in Chinese)
[10]	McAuliffe B R,Sjolander S A.Active flow control using steady blowing for a low-pressure turbine cascade[J].ASME J. Turbomach.,2004,126(4):560-569.
[11]	乔渭阳,敬睿.叶轮机动态参数测试技术[M].北京:国防工业出版社,2004.
[12]	陈萍萍,乔渭阳,侯伟涛,等.基于流动控制技术的低稠度大负荷涡轮设计[J].航空动力学报,2010,25(11):2528-2538. CHEN Pingping,QIAO Weiyang,HOU Weitao,et al.Study on the high-loading turbine airfoil design based on the flow control[J].Journal of Aerospace Power,2010,25(11):2528-2538.(in Chinese)
[13]	Gier J,Franke M,Hubner N,et al.Designing LP turbines for optimized airfoil loading .ASME Paper GT 2008-51101,2008.