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超声速气液两相清洗喷头计算

Calculation of supersonic gas-liquid two-phase cleaning nozzle
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摘要 为了建立高效可靠的喷射设备计算方法,辅助喷射喷头设计,对用于清洗机械零部件表面的某超声速气液两相清洗喷头进行计算,分析了其核心气动结构——Laval喷管中的流动情况。以空气与液相颗粒组成的两相流为研究对象,采用MacCormack预估—校正法在工程求解器EES中编写差分程序进行数值求解。计算了进口总压为0.5~4.5 MPa、液相流量为0.005~0.045 kg/s和液相颗粒直径为10~100μm时喷管中的流动情况。分析了进口总压、液相流量和颗粒直径对两相流动的影响,得出该清洗喷头中流动参数的变化规律、清洗喷头工作压力的调节规律和温度限制。 In order to establish an efficient and reliable injection equipment calculation method and auxiliary spray nozzle design.The supersonic gas-liquid two-phase cleaning nozzle used to clean the surface of mechanical parts was calculated,and the flow in the core aerodynamic structure,Laval nozzle,was analyzed.Taking the two-phase flow composed of air and liquid particles as the research object,the MacCormack prediction-correction method is used to write the differential program in the engineering equation solver EES for numerical solution.The flow in the nozzle was calculated when the total inlet pressure was 0.5~4.5 MPa,the liquid phase flow was 0.005~0.045 kg/s,and the liquid phase particle diameter was 10~100μm.The effects of total inlet pressure,liquid phase flow and particle diameter on the two-phase flow were analyzed.The variation of flow parameters in the cleaning nozzle,the regulation of the working pressure of the cleaning nozzle and the temperature limitation are obtained.
作者 田骏丹 徐让书 刘宗旺 TIAN Jun-dan;XU Rang-shu;LIU Zong-wang(School of Aero-engine,Shenyang Aerospace University,Shenyang 110136,China)
出处 《沈阳航空航天大学学报》 2020年第6期43-48,共6页 Journal of Shenyang Aerospace University
关键词 超声速 两相流 喷管 数值计算 清洗喷头 supersonic two-phase flow nozzle numerical simulation cleaning nozzle
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  • 1于勇,刘淑艳,张世军,张夏.固体火箭发动机喷管气固两相流动的数值模拟[J].航空动力学报,2009,24(4):931-937. 被引量:24
  • 2张家騄.中国现代声学与马大猷[J].声学学报,2005,30(6):481-486. 被引量:4
  • 3李东霞,徐旭,蔡国飙,张振鹏.火箭发动机气体-颗粒两相流双流体模型研究[J].固体火箭技术,2005,28(4):238-243. 被引量:15
  • 4Chang I S. One- and two phase nozzle flows[R]. AIAA-80- 0272,1980.
  • 5Golafshani M, Loh H T. Computation of two phase viscous flow in solid rocket motors using a flux-split Eulerian-Lagrangian technique[R]. AIAA 89 2785,1989,.
  • 6Wirzberger H, Yaniv S. Prediction of erosion in a solid rocket motor by alumina particles [R]. AIAA 2005- 4496.2005.
  • 7Cuffel R F,Back L H ,Massier P F. Transonic flow field in a supersonic nozzle with small throat radius of curvature [J]. AIAA Journal, 1969,17: 1364-1376.
  • 8Mehta R C, Jachandra T. A fast algorithm to slove viscous two -phase flow in an axisymmetric rocket nozzle[J] .Int J Numerical methods Fluids, 1998,26(5).
  • 9Coakly T J, Champeny J M. Numerical simulation of compressible turbulent two-phase flow[J]. MAA 85-1666.
  • 10Chang H T, Hourng L W, Chien L C. Application of flux-vector-splitting scheme to a dilute gas-particle JPL nozzle flow [J] . Int J Numerical Methods Fluids, 1996,22(10) .

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