叶片前缘形状对涡轮气动性能的影响

陈雷; 陈江; 赵石磊; 张慧

叶片前缘形状对涡轮气动性能的影响

1.
北京航空航天大学能源与动力工程学院, 北京 100191
2.
中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015

基金项目: 高技术研究发展计划(2008AA050503); 航空基金(2010ZB51023)

计量
- 文章访问数: 1704
- HTML浏览量: 192
- PDF量: 946
- 被引次数: 0
出版历程
- 收稿日期: 2012-05-12
- 刊出日期: 2013-04-28

Effect of blade leading edge on aerodynamic performance of turbine

1.
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

摘要: 采用Bezier曲线控制涡轮叶片前缘形状由圆弧形改为非圆弧形,用数值计算方法研究涡轮叶片前缘形状对其气动性能影响.首先以基元叶型为研究基础,数值模拟分析、比较不同基元叶型前缘形状在不同攻角下对涡轮叶栅性能影响.对于正常运行的攻角范围(-15°~+10°),由于非圆弧形前缘表面曲率半径增大较缓,减小了前缘表面流动的法向压力梯度,抑制过度膨胀,减小由摩擦力引起的能量耗散,损失减小,且非圆弧形曲率半径越大,提高性能效果相对越好.而在非设计工况的大攻角条件下,前缘曲率半径缓慢增大将导致叶型分离更严重,损失相对增加.其次以某5级低压涡轮作为验证实例,数值研究分析认为,非圆弧形前缘形状可改善叶片前缘流动特性,提高涡轮效率,但对于远离设计点的非设计工况,由于气流攻角的大幅度改变,会带来涡轮气动性能的负面影响.
- 叶片前缘 /
- 气动性能 /
- 基元叶型 /
- 低压涡轮 /
- 数值研究
Abstract: Geometry of turbine blade leading edge was altered from circular to non-circular by using the Bezier curves methods,based on which numerical analysis and comparison were made to illustrate how turbine cascade leading edges affected the aerodynamic performance under different attack angles.Within the normal operating range of attack angle (-15°~ +10°),the non-circular leading edge had a better performance as the gradual increase of the curvature radius of the non-circular leading edge reduced the normal pressure gradient of the leading edge,which further restrained the flow from excessively expanding and reduced the energy dissipation caused by the viscous stress,resulting in a decreased flow loss,and the bigger the curvature radius of the non-circular leading edge,the better the performance.Whereas under the large attack angle of the non-design condition,the gradual increase of the curvature radius would cause more severe cascade separation,which aggravated the loss,and it was exemplified by the case of a five-stage low pressure turbine.Numerical analysis has indicated that the non-circular leading edge can improve the flow features and increase the turbine efficiency.However,for the non-design condition estranging from the design point,the flow attack angle alters so substantially that it has negative effect on the turbine aerodynamic performance.
- blade leading edge /
- aerodynamic performance /
- cascade /
- low pressure turbine /
- numerical investigation

HTML

参考文献(15)

[1]	Zess G A,Thole K A.Computational design and experimental evaluation of using a leading edge fillet on a gas turbine vane [R].ASME Paper 2001-GT-0404,2001.
[2]	Mahmood G I,Gustafson R,Acharya S.Experimental investigation of flow structure and Nusselt number in a low speed linear blade passage with and without leading-edge fillets[J].ASME Journal of Heat Transfer,2005,127(5):499-512.
[3]	Sauer H,Muller R,Vogeler K. Reduction of secondary flow losses in turbine cascades by leading edge modifications at the endwall [R].ASME Paper 2000-GT-0473,2000.
[4]	Becz S,Majewski M S.Leading edge modification effects on turbine cascade endw all loss [R].ASME Paper 2003-GT-38898,2003.
[5]	孙大伟,乔渭阳.叶片前缘改型对涡轮叶栅二次流的影响[J].推进技术,2009,30(2):187-192. SUN Dawei,QIAO Weiyang.Effects of leading edge modification on secondary flow in turbine cascades [J].Journal of Propulsion Technology,2009,30(2):187-192.(in Chinese)
[6]	Smith D G,Bagshaw D,Ingram G,et al. Using profiled endwalls,blade lean and leading edge extensions to minimize secondary flow [R].ASME Paper 2008-GT-50811, 2008.
[7]	Walraevens R E,Cumpsty N A.Leading edge separation bubbles on turbomachine blades[J].Journal of Turbomachinery,1995,117(1):115-125.
[8]	Casartelli E,Saxer A P,Gyarmathy G.Numerical flow analysis in a subsonic vaned radial diffuser with leading edge redesign[J].Journal of Turbomachinery,1999,121(1):119-126.
[9]	Bak C,Fuglsang P.Modification of the NACA 63-415 leading edge for better aerodynamic performance[J].Journal of Solar Energy Engineering,2002,124(4):327-334.
[10]	Muller R,Sauer H,Vogeler K,et al.Influencing the secondary losses in compressor cascades by a leading edge bulb modification at the endwall [R].ASME Paper 2002-GT-30442,2002.
[11]	刘火星,李凌,蒋浩康,等.二维NACA65叶型前缘几何形状对气动性能的影响[J].工程热物理学报,2003,24(2):231-233. LIU Huoxing,LI Ling,JIANG Haokang,et al.Effect of leading edge geometry on separation bubble on a NACA65 compressor blade[J].Journal of Engineering Thermophysics,2003,24(2):231-233.(in Chinese)
[12]	陆宏志,徐立平.压气机叶片的带平台圆弧形前缘[J].推进技术,2003,24(6):532-536. LU Hongzhi,XU Liping.Circular leading edge with a flat for compressor bladed[J].Journal of Propulsion Technology,2003,24(6):532-536.(in Chinese)
[13]	Mengistu T,Ghaly W.Single and multipoint shape optimaization of gas turbine blade cascades [R].AIAA 2004-4446,2004.
[14]	靳军,刘波,南向谊,等. 超声速叶型前缘几何形状对叶栅气动性能的影响[J].航空动力学报,2007,22(4):660-665. JIN Jun,LIU Bo,NAN Xiangyi,et al.Influence effect of supersonic airfoil's leading edge geometric shape on aero-dynamical performance of cascade[J].Journal of Aerospace Power,2007,22(4):660-665.(in Chinese)
[15]	初雷哲,杜建一,黄典贵,等.离心压气机叶片前缘几何形状对性能的影响[J].工程热物理学报,2008,29(5):767-769. CHU Leizhe,DU Jianyi,HUANG Diangui,et al.Effect of the blade leading edge on the performance of a centrifugal compressor[J].Journal of Engineering Thermophysics,2008,29(5):767-769.(in Chinese)