U型槽对高负荷低压涡轮叶型攻角特性影响

张波; 李伟; 杜强; 黄恩亮; 卢新根; 朱俊强

U型槽对高负荷低压涡轮叶型攻角特性影响

张波^1,2,
李伟^1,2,
杜强^1,2,
黄恩亮^1,2,
卢新根²,
朱俊强²

1.
中国科学院研究生院,北京 100190
2.
中国科学院工程热物理研究所轻型动力重点实验室,北京 100190

基金项目: 国际科技合作项目(2010DFB70620); 国家自然科学基金(51176187)

计量
- 文章访问数: 1762
- HTML浏览量: 97
- PDF量: 618
- 被引次数: 0
出版历程
- 收稿日期: 2011-08-30
- 刊出日期: 2012-07-28

Effect of U-grooves on high-lift low pressure turbine profile's incidence characteristics

1.
Graduate University of Chinese Academy of Sciences,Beijing 100190,China
2.
Key Laboratory of Light-duty Gas-turbine,Institute of Engineering Thermophysics, Chinese Academy of Sciences,Beijing 100190,China

摘要

摘要: 以某高负荷低压涡轮叶型为研究对象,分析了该叶型在低雷诺数下的攻角特性,并应用了表面嵌壁式U形槽的被动控制方法来提高该叶型的攻角裕度.数值模拟的结果表明:相比较大的正攻角流动状况,叶型较大的负攻角并不会引起吸力面大的流动分离,从而减小了叶型损失;表面嵌壁式U型槽通过推迟分离、加速再附来减小分离泡甚至减小湍流湿面积,从而降低叶型损失;表面嵌壁式U型槽能否提高该叶型的攻角裕度与开槽位置和深度有关系,在±15°攻角范围内72%轴向弦长位置处开槽明显的降低了叶型损失而开槽深度为0.40mm时叶型损失最小.
- 低雷诺数 /
- 高负荷 /
- 攻角裕度 /
- 叶型损失 /
- 嵌壁式U型槽
Abstract: The high-lift low pressure turbine blade profile incidence characteristics under low Reynolds number were investigated.The modification used recessed U-grooves to improve the profiles’ incidence margin.The numerical simulations suggest that compared with high incidence flow condition,lower incidence does not induce large separation which appears on the suction surface of the profile and hence lessens profile loss.The recessed U-grooves delay the separation location,accelerate reattach location,decrease the turbulent wetted area,thereby the separation bubble is suppressed and the profile loss decreases.Whether or not the recessed U-grooves can improve the incidence margin is related to the depth and location of the U-grooves.With±15 incidence degrees,the U-grooves located in 72% axial chord length showed lower profile loss,and when the depth was 0.40mm the profile loss was the lowest.
- low Reynolds number /
- high-lift /
- incidence margin /
- profile loss /
- recessed U-grooves

HTML

参考文献(17)

[1]	Benner M W,Sjolander S A,Moustapha S H.Measurements of secondary flows downstream of a turbine cascade at off-design incidence .ASME GT 2004-53786,2004.
[2]	Benner M W,Sjolander S A,Moustapha S H.Measurements of secondary flows in turbine cascade at off-design incidence .ASME Turbo Expo,GT 97-382,1997.
[3]	Jouini D B M,Sjolander S A.Midspan flow-field measurements for two transonic linear turbine cascades at off-design conditions[J].Journal of Turbomachinery,2002,124(2):176-186.
[4]	Jouini D B M,Sjolander S A.Off-design performance of a single-stage transonic turbine .ASME GT 2000-0482,2000.
[5]	Perdichizzi A,Dossena V.Incidence angle and pitch-chord effects on secondary flows downstream of a turbine cascade[J].Journal of Turbomachinery,1993,115(3):383-391.
[6]	孙大伟,乔渭阳,许开富,等.不同攻角涡轮叶栅损失的影响[J].航空动力学报,2008,23(7):1232-1239. SUN Dawei,QIAO Weiyang,XU Kaifu,et al.Influence of different incidences on loss in turbine cascade[J].Journal of Aerospace Power,2008,23(7):1232-1239.(in Chinese)
[7]	陈绍文,陈浮,徐文远,等.变攻角下涡轮导向器二次流的实验研究[J].燃气涡轮试验与研究,2005,18(4):15-19. CHEN Shaowen,CHEN Fu,XU Wenyuan,et al.Experimental investigation of secondary flow with different incidences in an LP turbine guide vane[J].Gas Turbine Experimental and Research,2005,18(4):15-19.(in Chinese)
[8]	Curtis E M,Hodson H P,Banieghbal M R,et al.Development of blade profiles for low-pressure turbine applications[J].Journal of Turbomachinery,1997,119(3):531-538.
[9]	Jame P L,Paul I K,Richard B R.Low Reynolds number loss reduction on turbine blades with dimples and v-grooves .AIAA-2000-0738,2000.
[10]	ZHANG Xuefeng,Maria V,Hodson H P.Separation and transition control on an aft-loaded ultra-high-lift LP turbine blade at low Reynolds numbers:low-speed investigation .ASME Paper GT-2005-68892,2005.
[11]	蓝吉兵,谢永慧,张荻.低压高负荷燃气透平叶片边界层分离转捩数值模拟与流动控制[J].中国电机工程学报,2009,29(26):68-74. LAN Jibing,XIE Yonghui,ZHANG Di.Numerical simulation and control of separated transition flows in high-lift low-pressure gas turbine cascade[J].Proceedings of the CSEE,2009,29(26):68-74.(in Chinese)
[12]	Popovic I,Zhu J,Dai W,et al.Aerodynamics of a family of three highly loaded lower-pressure turbine airfoils:measured effects of Reynolds number and turbulence intensity in steady flow .ASME GT2006-91271,2006.
[13]	李伟,朱俊强,李刚,等.基于表面热膜的超高负荷低压涡轮叶栅附面层特性[J].航空动力学报.2011,26(1):115-121. LI Wei,ZHU Junqiang,LI Gang,et al.Experimental research for boundary layer behaviors on an ultra-high-lift low-pressure turbine profile based on surface hot-film[J].Journal of Aerospace Power,2011,26 (1):115-121.(in Chinese)
[14]	杜强,朱俊强,温殿中.高负荷低压涡轮边界层转捩预测及其机理分析[J].工程热物理学报,2010,31(5):761-764. DU Qiang,ZHU Junqiang,WEN Dianzhong.Boundary layer transition prediction and mechanism analysis of a high-loading LP turbine blade profile[J].Journal of Engineering Thermophysics,2010,31(5):761-764.(in Chinese)
[15]	Benner M W.The effects of leading edge geometry on profile and secondary losses in turbine cascades .Ottawa,Canada:Carleton University,2003.
[16]	Denton J D.Loss mechanisms in turbomachines[J].Jornal of Turbomachinery,1993,115(4):621-656.
[17]	Robarge T W,Stark A M,Min S K,et al.Design considerations for using indented surface treatments to control boundary layer separation .AIAA 2004-425,2004.