某大涵道比风扇轮毂型线数值计算
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摘要
为了改善风扇叶根的二次流动,基于某原型方案,采用数值模拟方法研究了轮毂型线对大涵道比民用发动机风扇流场的影响。研究结果表明:凹形轮毂型线对风扇根部流动的影响主要体现在从下凹位置开始的加速流动作用。靠近风扇尾缘是较优的轮毂下凹最深位置,对根部流动存在2种改善作用,即流路收缩带来的加速流动作用,在提高风扇根部出口子午速度的同时,提高了10%叶高附近吸力面表面流体速度,抑制该叶高靠近尾缘处流体回流;由于轮毂下凹最深位置靠近尾缘,轮毂型线在靠近风扇出口时可以维持在凹曲线形式,减弱风扇角区吸力面表面回流。轮毂下凹深度对风扇内涵的压比和效率呈现单调影响。改进后的轮毂型线计算结果与原型方案相比,风扇吸力面极限流线改善,全流量范围内风扇内涵效率提升。
In order to improve the secondary flow of fan blade root, the effect of hub-shape contouring on the flow field of a high bypass ratio civil engine fan was studied by using numerical simulation method based on the prototype plan. The results show that the effect of concave hub-shape contouring on the flow of fan blade root is mainly reflected in accelerating flow, starting from the concave position.The most deep concave position of hub is near to the fan trailing edge, which has improvement effect in two aspects, the accelerating flow,caused by the flow path contraction, enhances both the meridian velocity at fan root exit and the suction-surface flow velocity near to the 10% of blade height location, and therefore restrains the fluid recirculation near to the trailing edge of the blade height. Since the most deep concave position of hub is near to the fan trailing edge, the hub-shape contouring remains concaved near to the fan exit, and the suctionsurface recirculation in fan angular region is reduced. The depth of hub concave influences the pressure ratio and efficiency of the fan core monotonously. Compared with the prototype plan, the suction surface limiting stream line of fan is improved, and the core efficiency of fan in full flow range is enhanced.
In order to improve the secondary flow of fan blade root, the effect of hub-shape contouring on the flow field of a high bypass ratio civil engine fan was studied by using numerical simulation method based on the prototype plan. The results show that the effect of concave hub-shape contouring on the flow of fan blade root is mainly reflected in accelerating flow, starting from the concave position.The most deep concave position of hub is near to the fan trailing edge, which has improvement effect in two aspects, the accelerating flow,caused by the flow path contraction, enhances both the meridian velocity at fan root exit and the suction-surface flow velocity near to the 10% of blade height location, and therefore restrains the fluid recirculation near to the trailing edge of the blade height. Since the most deep concave position of hub is near to the fan trailing edge, the hub-shape contouring remains concaved near to the fan exit, and the suctionsurface recirculation in fan angular region is reduced. The depth of hub concave influences the pressure ratio and efficiency of the fan core monotonously. Compared with the prototype plan, the suction surface limiting stream line of fan is improved, and the core efficiency of fan in full flow range is enhanced.
引文
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[13]肖文富,申晓霞,屈霁云.轮毂造型抑制角区失速的数值研究[J].硅谷,2010(7):116-118.XIAO Wenfu,SHEN Xiaoxia,QU Jiyun.Numerical simulation of inhibitory corner for stall hub-shape contouring[J].Silicon Valley,2010(7):116-118.(in Chinese)
[14]张恒铭,黄秀全.跨音速压气机轮毂型线优化设计[J].航空计算技术,2013,43(1):25-27.ZHANG Hengming,HUANG Xiuquan.Optimization of hub-shape contouring of a transonic axial compressor[J].Aeronautical Computing Technique.2013,43(1):25-27.(in Chinese)
[15]李志平,李秋实,吴渺.单级风扇/压气机双波浪结构轮毂造型方法:中国104791294A[P].2015-07-22.LI Zhiping,LI Qiushi,WU Miao.Hub-shape contouring method of double wave structure for single-stage fan/compressor:China104791294A[P].2015-07-22.(in Chinese)
[2]Khalid S A,Khalsa A S,Waitz I A,et al.Endwall blockage in axial compressors[J].ASME Journal of Turbomachinery,1999,121(3):499-509.
[3]Roque Corral,Fernando Gisbert.Profiled endwall design using an adjoint navier stokes solver[R].ASME 2006-GT-90650.
[4]Lu J,Chu W,Wu Y.Effects of endwall profiling on axial flow compressor stage[R].ASME 2009-GT-59418.
[5]张龙新,周逊,吴帆,等.凹型轴对称端壁造型在大安装角扩压叶栅中的应用研究[J].推进技术,2016,37(10):1869-1874.ZHANG Longxin,ZHOU Xun,WU Fan,et a1.Application study of concave axisymmetric endwall molding in a compressor cascade with high stagger angle[J].Journal of Propulsion,2016,37(10):1869-1874.(in Chinese)
[6]Hoeger M.Rotary turbomachine having a transonic compressor stage:US Patent 6017186[P].2000-01-25.
[7]Hoeger M,Sievers N,Lawerenz M.On the performance of compressor blades with contoured endwalls[R].The 4th European Conf.on Turbomach,2001.
[8]Hoeger M,Cardamone P,Fottner L.Influence of endwall contouring on the transonic flow in a compressor blade[R].ASME 2002-GT-30440.
[9]Oliver R,Stefan H P,Alexander H,et al.Endwall contouring and fillet design for reducing losses and homogenizing the outflow of a compressor cascade[R].ASME 2014-GT-25277.
[10]徐全勇,侯安平,李绍斌,等.轮毂曲线对跨声速压气机转子性能的影响[J].工程热物理学报,2009,30(5):761-764.XU Quanyong,HOU Anping,LI Shaobin,et al.Influences of hub design on rotor performance in transonic compressor[J].Journal of Enginerring Thermophysics,2009,30(5):761-764.(in Chinese)
[11]杨春,李秋实,袁巍,等.轮毂修型对压气机静子角区堵塞的影响[J].航空动力学报,2009,24(10):2333-2337.YANG Chun,LI Qiushi,YUAN Wei,et al.Effect of hub-shape contouring on the corner blockage of compressor stator cascade[J].Journal of Aerospace Power,2009,24(10):2333-2337.(in Chinese)
[12]李秋实,杨春,肖文富,等.端壁造型抑制角区失速的数值研究[J].自然科学进展,2009,19(5):537-543.LI Qiushi,YANG Chun,XIAO Wenfu,et al.Numerical simulation of inhibitory corner stall for endwall profiling[J].Progress in Natural Science,2009,19(5):537-543.(in Chinese)
[13]肖文富,申晓霞,屈霁云.轮毂造型抑制角区失速的数值研究[J].硅谷,2010(7):116-118.XIAO Wenfu,SHEN Xiaoxia,QU Jiyun.Numerical simulation of inhibitory corner for stall hub-shape contouring[J].Silicon Valley,2010(7):116-118.(in Chinese)
[14]张恒铭,黄秀全.跨音速压气机轮毂型线优化设计[J].航空计算技术,2013,43(1):25-27.ZHANG Hengming,HUANG Xiuquan.Optimization of hub-shape contouring of a transonic axial compressor[J].Aeronautical Computing Technique.2013,43(1):25-27.(in Chinese)
[15]李志平,李秋实,吴渺.单级风扇/压气机双波浪结构轮毂造型方法:中国104791294A[P].2015-07-22.LI Zhiping,LI Qiushi,WU Miao.Hub-shape contouring method of double wave structure for single-stage fan/compressor:China104791294A[P].2015-07-22.(in Chinese)