Flow control mechanism of diffuser cascade corner-suction surface profiling design
-
摘要: 通过数值模拟,分别针对扩压叶栅的设计工况与角区失速工况进行叶身/端壁融合与吸力面优化造型设计,分析其流场结构与性能的变化,并探究两种优化造型对压气机性能改善的机理。优化结果表明:在设计工况下,优化造型吸力面凹陷,使得吸力面附面层厚度变薄,最大端壁融合位置靠近尾缘,角区低能流体在压力梯度的作用下转移并减少,分离结构得到明显控制,损失降低;在角区失速工况下,优化造型吸力面凸起,最大端壁融合位置靠近前缘,使得前缘分离结构显著减弱,当流体在进入吸力面前缘时提前附着,前缘分离区减小甚至消失,损失降低。根据两种造型流场结构特点与控制机理,可构造出在多工况下具有显著作用的叶身-端壁融合造型。Abstract: Through numerical simulation, the optimal profiling under the design point and near stall point were compared, allowing for analyzing the flow field structure and compressor performance changes and exploring the mechanism of the two kinds of optimized profiling to improve the compressor performance. The optimization results showed that the suction surface of the optimal profiling under the design point was sunken, which reduced obviously the thickness of the boundary layer on the suction surface; and blend blade and end wall was close to the trailing edge, which reduced the low energy fluid in the corner zone and produced transfer under the impact of the pressure gradient. For the optimal profiling under the near stall point, the blend blade and end wall was close to the leading edge and the suction surface was convex, which promoted the fluid adhesion in advance when fluid entered the leading edge, and the leading edge separation area decreased sharply or even disappeared. The optimal profiling adapted to all working conditions can be constructed based on the two profiling controlling mechanisms and structure features, yielding extremely positive effect on many working conditions.
-
[1] LIU Baojie,AN Guangfeng,YU Xianjun,et al.Experimental investigation of the effect of rotor tip gaps on 3D separating flows inside the stator of a highly loaded compressor stage[J].Experimental Thermal and Fluid Science,2016,75:96-107. [2] FEI Teng,JI Lucheng,YI Weilin,et al.Investigation of the dihedral angle effect on the boundary layer development using special-shaped expansion pipes[R].ASME Paper 2018-GT-76383,2018. [3] TAYLOR J V,MILLER R J.Competing 3D mechanisms in compressor flows[R].ASME Paper 2015-GT-43322,2015. [4] LEI V M,SPAKOVSZKY Z S,GREITZER E M.A criterion for axial compressor hub-corner stall[J].Journal of Turbomachinery,2008,130(3):1-10. [5] 李相君,楚武利,张皓光.高负荷轴流压气机叶栅二次流动与损失关联性探讨[J].推进技术,2014,35(7):914-925. LI Xiangjun,CHU Wuli,ZHANG Haoguang.Investi gation on relation between secondary flow and loss on a high loaded axial-flow compressor cascade[J].Journal of Propulsion Technology,2014,35(7):914-925.(in Chinese) [6] DEBRUGE L L.The aerodynamic significance of fillet geometry in turbocompressor blade rows[J].Journal of Engineering for Power,1980,102(4):984-993. [7] BAGSHAW D A,INGRAM G L,GREGORY-SMITH D G.The design of three-dimensional turbine blades combined with profiled endwalls[J].Power and Energy,2008,222:93-102. [8] 彭学敏,季路成,伊卫林,等.高负荷压气机叶栅的叶身/端壁融合研究[J].工程热物理学报,2014,35(2):242-246. PENG Xuemin,JI Lucheng,YI Weilin,et al.Study on blended blade and endwall technique applied to high-load compressor cascades[J].Journal of Engineering Thermophysics,2014,35(2):242-246.(in Chinese) [9] SMITH L H,YEH H.Sweep and dihedral effect in axial-flow turbomachinery[J].Journal of Basic Engineering,1963,85(3):401-414. [10] BREUGELMANS F A H,CARELS Y,DEMUTH M.Influence of dihedral on the secondary flow in a two-dimensional compressor cascade[J].Journal of Engineering for Gas Turbines and Power,1984,106(3):578-584. [11] SASAKI T,BREUGELMANS F.Comparison of sweep and dihedral effects on compressor cascade performance[J].Journal of Turbomachinery,1998,120(3):454-463. [12] 季路成,程荣辉,邵卫卫,等.最大负荷设计之:角区分离预测与控制[J].工程热物理学报,2007,28(2):219-222. JI Lucheng,CHENG Ronghui,SHAO Weiwei,et al.Prediction and control of corner separation for in maximizing blade loading[J].Journal of Engineering Thermophysics,2007,28(2):219-222.(in Chinese) [13] GMMER V,WENGER U,KAU H P.Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors[J].Journal of Turbomachinery,2001,123(1):40-48. [14] 季路成,伊卫林,田勇,等.一种叶轮机械叶片与端壁融合设计方法:CN201010623606.2[P].2011-06-15. [15] LI Jiabin,JI Lucheng,YI Weilin.The use of blended blade and end wall in compressor cascade[R].ASME Paper 2018-GT-76048,2018. [16] LI Jiabin,JI Lucheng,YI Weilin.Experimental and numerical investigation on the aerodynamic performance of a compressor cascade using blended blade and end wall[R].ASME Paper 2017-GT-63879,2017. [17] REUTTER O,POTTMANN S.H,HERGT A,et al.Endwall contouring and fillet design for reducing losses and homogenizing the outflow of a compressor cascade.[R].ASME Paper 2014-GT-25277,2014. [18] 李相君.高负荷轴流压气机端区流动机制及被动控制[D].西安:西北工业大学,2018.
点击查看大图
计量
- 文章访问数: 79
- HTML浏览量: 1
- PDF量: 124
- 被引次数: 0