带不同形状吸力面小翼的压气机叶栅变间隙实验研究
|
摘要
为了控制和降低压气机中由叶尖间隙引起的泄漏损失,对加装不同形状的吸力面小翼变间隙流场进行了实验研究。通过五孔探针测量叶栅出口流场,详细分析了不同间隙下吸力面叶尖小翼对压气机叶栅出口流场结构、气动损失和通流能力的影响。结果表明:与常规叶栅相比,附加吸力面小翼的叶栅泄漏涡涡核向远离叶片吸力面移动,且强度明显减弱,泄漏涡的起始点转移到吸力面小翼的最大厚度轴向位置处。不同形状的吸力面小翼在大间隙高度下对叶栅损失的影响较为明显,其中SW25方案叶栅在3%h间隙高度下效果最佳,可使叶栅出口总压损失降低15.38%。研究的三种不同形状的吸力面小翼仅在小间隙高度下改善了叶尖泄漏涡造成的叶栅出口气流角的过偏转/欠偏转现象。
In order to control and reduce leakage loss in the compressor caused by the tip clearance,detailed experiments have been carried out on variable tip clearance flow with different shapes of suction-side winglets. And the outlet flow fields of the cascade were obtained by the five-hole probe,the effects of suction-side winglets on outlet flow field structure,aerodynamic loss and the flow capacity of the cascade were detailed analyzed under different gaps. The results show that compared with conventional cascades,leakage vortex core of the suction side winglet cascades moves away from the blade suction surface,and the intensity is significantly reduced,the starting point of leakage vortex moves to the maximum thickness of the axial location. Effects of suction-side winglets with different shapes in large tip height on cascade loss are more obvious,and the SW25 scheme cascade under 3% clearance height is best,which can reduce cascade outlet total pressure loss by15.38%. The underturning and overturning of outlet flow angle induced by leakage vortex are reduced only in smaller tip height.
In order to control and reduce leakage loss in the compressor caused by the tip clearance,detailed experiments have been carried out on variable tip clearance flow with different shapes of suction-side winglets. And the outlet flow fields of the cascade were obtained by the five-hole probe,the effects of suction-side winglets on outlet flow field structure,aerodynamic loss and the flow capacity of the cascade were detailed analyzed under different gaps. The results show that compared with conventional cascades,leakage vortex core of the suction side winglet cascades moves away from the blade suction surface,and the intensity is significantly reduced,the starting point of leakage vortex moves to the maximum thickness of the axial location. Effects of suction-side winglets with different shapes in large tip height on cascade loss are more obvious,and the SW25 scheme cascade under 3% clearance height is best,which can reduce cascade outlet total pressure loss by15.38%. The underturning and overturning of outlet flow angle induced by leakage vortex are reduced only in smaller tip height.
引文
[1]Denton J D.Loss Mechanisms in Turbomachines[J].Journal of Turbomachinery,1993,115(4):621-656.
[2]钟兢军.弯曲叶片控制扩压叶栅二次流动的实验研究[D].哈尔滨:哈尔滨工业大学,1996.
[3]Houghton T,Day I.Enhancing the Stability of Subsonic Compressors Using Casing Grooves[J].Journal of Turbomachinery,2011,133(2).
[4]李继超.轴流压气机叶顶喷气扩稳技术—机理及智能调控[D].北京:中国科学院研究生院,2012.
[5]Gourdain N,Leboeuf F.Unsteady Simulation of an Axial Compressor Stage with Casing and Blade Passive Treatments[J].Journal of Turbomachinery,2009,131(2).
[6]全建军.风力机叶尖加小翼动力放大特性实验研究[D].呼和浩特:内蒙古工业大学,2006.
[7]崔承根.不同叶梢结构的螺旋桨研究动态[J].船舶,1997,(2):20-23.
[8]韩丰波,魏秀玲,袁小龙.飞机翼梢小翼及其应用[C].长春:吉林省第八届科学技术学术年会,2014.
[9]Patel K V.Research on a High Work Axial Gas Generator Turbine[R].SAE Technical,No.800618,1980.
[10]Dey D,Camci C.Tip Desensitization of an Axial Turbine Rotor Using Tip Platform Extensions[C].USA:ASME Turbo Expo 2001:Power for Land,Sea and Air,2001.
[11]王大磊,邵伏永,郭昊雁,等.翼梢小翼对涡轮间隙泄漏流动影响的数值研究[J].推进技术,2014,35(3):341-346.(WANG Da-lei,SHAO Fu-yong,GUO Hao-yan,et al.Study of Tip Winglets on Leakage Flow in a Transonic Turbine Stage[J].Journal of Propulsion Technology,2014,35(3):341-346.)
[12]魏曼,钟兢军.具有叶尖小翼的涡轮叶栅间隙流动的实验研究[J].推进技术,2015,36(12):1825-1832.(WEI Man,ZHONG Jing-jun.Experimental Investigation on Tip Clearance Flow of a Turbine Cascade with Tip Winglet[J].Journal of Propulsion Technology,2015,36(12):1825-1832.)
[13]钟兢军,魏曼,陆华伟.压力面小翼对涡轮叶栅不同间隙下流场影响的实验[J].航空动力学报,2016,(1):84-91.
[14]韩少冰,钟兢军,陆华伟.不同宽度吸力面小翼控制压气机叶栅间隙流动的实验研究[J].推进技术,2016,37(3):471-478.(HAN Shao-bing,ZHONG Jing-jun,LU Hua-wei.Experimental Investigation of Compressor Cascade Tip Leakage Flow Control Using Suction-Side Winglet with Different Widths[J].Journal of Propulsion Technology,2016,37(3):471-478.)
[15]韩少冰,钟兢军.具有叶尖小翼的压气机叶栅间隙流动分析[J].工程热物理学报,2012,33(9):1492-1496.
[16]史磊,刘波,那振喆,等.吸附式压气机叶栅端壁流场油流实验研究及数值分析[J].推进技术,2015,36(2):217-225.(SHI Lei,LIU Bo,NA Zhenzhe,et al.Oil Flow Visualization and Numerical Calculation on End-Wall of Aspirated Compressor Cascade[J].Journal of Propulsion Technology,2015,36(2):217-225.)
[2]钟兢军.弯曲叶片控制扩压叶栅二次流动的实验研究[D].哈尔滨:哈尔滨工业大学,1996.
[3]Houghton T,Day I.Enhancing the Stability of Subsonic Compressors Using Casing Grooves[J].Journal of Turbomachinery,2011,133(2).
[4]李继超.轴流压气机叶顶喷气扩稳技术—机理及智能调控[D].北京:中国科学院研究生院,2012.
[5]Gourdain N,Leboeuf F.Unsteady Simulation of an Axial Compressor Stage with Casing and Blade Passive Treatments[J].Journal of Turbomachinery,2009,131(2).
[6]全建军.风力机叶尖加小翼动力放大特性实验研究[D].呼和浩特:内蒙古工业大学,2006.
[7]崔承根.不同叶梢结构的螺旋桨研究动态[J].船舶,1997,(2):20-23.
[8]韩丰波,魏秀玲,袁小龙.飞机翼梢小翼及其应用[C].长春:吉林省第八届科学技术学术年会,2014.
[9]Patel K V.Research on a High Work Axial Gas Generator Turbine[R].SAE Technical,No.800618,1980.
[10]Dey D,Camci C.Tip Desensitization of an Axial Turbine Rotor Using Tip Platform Extensions[C].USA:ASME Turbo Expo 2001:Power for Land,Sea and Air,2001.
[11]王大磊,邵伏永,郭昊雁,等.翼梢小翼对涡轮间隙泄漏流动影响的数值研究[J].推进技术,2014,35(3):341-346.(WANG Da-lei,SHAO Fu-yong,GUO Hao-yan,et al.Study of Tip Winglets on Leakage Flow in a Transonic Turbine Stage[J].Journal of Propulsion Technology,2014,35(3):341-346.)
[12]魏曼,钟兢军.具有叶尖小翼的涡轮叶栅间隙流动的实验研究[J].推进技术,2015,36(12):1825-1832.(WEI Man,ZHONG Jing-jun.Experimental Investigation on Tip Clearance Flow of a Turbine Cascade with Tip Winglet[J].Journal of Propulsion Technology,2015,36(12):1825-1832.)
[13]钟兢军,魏曼,陆华伟.压力面小翼对涡轮叶栅不同间隙下流场影响的实验[J].航空动力学报,2016,(1):84-91.
[14]韩少冰,钟兢军,陆华伟.不同宽度吸力面小翼控制压气机叶栅间隙流动的实验研究[J].推进技术,2016,37(3):471-478.(HAN Shao-bing,ZHONG Jing-jun,LU Hua-wei.Experimental Investigation of Compressor Cascade Tip Leakage Flow Control Using Suction-Side Winglet with Different Widths[J].Journal of Propulsion Technology,2016,37(3):471-478.)
[15]韩少冰,钟兢军.具有叶尖小翼的压气机叶栅间隙流动分析[J].工程热物理学报,2012,33(9):1492-1496.
[16]史磊,刘波,那振喆,等.吸附式压气机叶栅端壁流场油流实验研究及数值分析[J].推进技术,2015,36(2):217-225.(SHI Lei,LIU Bo,NA Zhenzhe,et al.Oil Flow Visualization and Numerical Calculation on End-Wall of Aspirated Compressor Cascade[J].Journal of Propulsion Technology,2015,36(2):217-225.)