Simulation on effect of throat contraction ratio and strake stagger angle on flow field and aerodynamic performance of scrampressor
doi: 10.13224/j.cnki.jasp.2017.05.020
Simulation on effect of throat contraction ratio and strake stagger angle on flow field and aerodynamic performance of scrampressor
-
摘要: The design methods of typical supersonic aircraft intakes and shock wave compression technology have been applied to ram-rotor, an attractive compression system. A ram-rotor is of a typical structure including the compression ramp, the throat and the subsonic diffuser; a scrampressor is similar to ram-rotor, the only difference is that scrampressor has no subsonic diffuser. The work was the continuation of the preparatory work. In order to further study the effect of throat contraction ratio and strake stagger angle on the flow field and performance of a scrampressor, the flow field of a scrampressor with a three-dimensional flow path was numerically simulated with different throat contraction ratios and strake stagger angles. Simulated results indicated that the optional aerodynamic performance of a scrampressor could be achieved with an adiabatic efficiency of 0.8413 a total pressure recovery coefficient of 0.8446, a total pressure ratio of 7.14 and a static pressure ratio of 5.17 for a throat contraction ratio of 0.6 and a strake stagger angle of 12°. It was therefore concluded that an appropriate decrease in throat contraction ratio and an increase in strake stagger angle could help the comprehensive improvement of a scrampressor in performance.Abstract: The design methods of typical supersonic aircraft intakes and shock wave compression technology have been applied to ram-rotor, an attractive compression system. A ram-rotor is of a typical structure including the compression ramp, the throat and the subsonic diffuser; a scrampressor is similar to ram-rotor, the only difference is that scrampressor has no subsonic diffuser. The work was the continuation of the preparatory work. In order to further study the effect of throat contraction ratio and strake stagger angle on the flow field and performance of a scrampressor, the flow field of a scrampressor with a three-dimensional flow path was numerically simulated with different throat contraction ratios and strake stagger angles. Simulated results indicated that the optional aerodynamic performance of a scrampressor could be achieved with an adiabatic efficiency of 0.8413 a total pressure recovery coefficient of 0.8446, a total pressure ratio of 7.14 and a static pressure ratio of 5.17 for a throat contraction ratio of 0.6 and a strake stagger angle of 12°. It was therefore concluded that an appropriate decrease in throat contraction ratio and an increase in strake stagger angle could help the comprehensive improvement of a scrampressor in performance.
-
Key words:
- scrampressor /
- flow field /
- aerodynamic performance /
- throat contraction ratio /
- strake stagger angle
-
[1] Denton J D.The calculation of three dimensional vicous flow through multistage turbomachines[J].Journal of Turbomachinery,1992,114(1):18-26. [2] He L.An Euler solution for unsteady flows around oscillating blades[J].Journal of Turbomachinery,1990,112(4):714-722. [3] He L,Ning W.Efficient approach for analysis of unsteady viscous flows in turbomachines [J].AIAA Journal,1998,36(11):2005-2012. [4] Hall K C,Thomas J P,Clark W S.Computation of unsteady nonlinear flows in cascades using a harmonic balance technique\[R\].Grenoble:The 9th International Symposium on Unsteady Aerodynamics,Aeroacoustics,and Aeroelasticity of Turbomachines,2000. [5] Gopinath A,Jameson A.Time spectral method for periodic unsteady computations over two-and three-dimensional bdies\[R\].AIAA-2005-1220,2005. [6] 张健.跨声速多级轴流压气机三维流场及气动性能数值模拟研究[D].四川 绵阳:中国空气动力研究与发展中心,2014.ZHANG Jian.Research on numerical simulation of 3D flow field and aerodynamic performance of transonic multistage axial compressor [D].Mianyang Sichuan:China Aerodynamic Research and Development Center,2014.(in Chinese) [7] 王雷,刘波.非线性谐波法在对转压气机中的校验分析[J].航空动力学报,2012,27(7):1448-1455.WANG Lei,LIU Bo.Validation of nonlinear harmonic method in dual-stage counter-rotating compressor [J].Journal of Aerospace Power,2012,27(7):1448-1455.(in Chinese) [8] 刘波,王雷,黄建.非线性谐波法在双级对转压气机中的进一步校验[J].航空动力学报,2013,28(6):1333-1341.LIU Bo,WANG Lei,HUANG Jian.Further validation of nonlinear harmonic method in dual-stage counter-rotating compressor [J].Journal of Aerospace Power,2013,28(6): 1333-1341.(in Chinese) [9] 马灿,苏欣荣,袁新.用于非定常流动的谐波平衡方法研究[J].工程热物理学报,2015,36(4):739-743.MA Can,SU Xinrong,YUAN Xin.Research on harmonic balance method for unsteady flow simulation [J].Journal of Engineering Thermophysics,2015,36(4):739-743.(in Chinese) [10] 杜鹏程.叶轮机转静非定常流动建模技术研究[D].北京: 北京航空航天大学,2015.DU Pengcheng.Investigation of the modeling methodologies for the rotor-stator unsteady flow interactions in turbomachinery [D].Beingjing: Beijing University of Aeronautics and Astronautics,2015.(in Chinese) [11] Biesinger T,Cornelius C,Rube C,et al.Unsteady CFD methods in a commercial solver for turbomachinery applications [R].ASME Paper GT2010-22762,2010. [12] NUMECA International.User manual fineTM/turbo v9.0 flow integated environment[R].Brussels:NUMECA International,2013. [13] Gerolymos G A,Michon G J,Neubauer J.Analysis and application of chorochronic periodicity in turbomachinery rotor/stator interaction computations [J].Journal of Propulsion and Power,2002,18(6):1139-1152. [14] Erdos J I,Alzner E,McNally W,Numerical solution of periodic transonic flow through a fan stage [J].AIAA Journal,1977,15(11):1559-1568. [15] 牟斌,肖中云,周铸,等.直升机旋翼悬停流场的粘性数值模拟[J].空气动力学学报,2009,27(5):582-585.MOU Bin,XIAO Zhongyun,ZHOU Zhu,et al.Numerical simulation of viscous flow-fields around helicopter rotor [J].Journal of Aerodynamic,2009,27(5):582-585.(in Chinese) [16] 肖中云.旋翼流场数值模拟方法研究[D].四川 绵阳:中国空气动力研究与发展中心,2007.XIAO Zhongyun.Investigation of computation modeling techiques for rotor flow fields[D].Mianyang Sichuan: China Aerodynamic Research and Development Center,2007.(in Chinese) [17] Reid L,Moore R D.Performance of a single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 1.82 [R].NASA TP-1338,1978. [18] 薛亮,韩万金,黄家骅,等.单级压气机气动优化设计[J].推进技术,2009,30(4):419-424.XUE Liang,HAN Wanjin,HUANG Jiahua,et al.Aerodynamic optimization design of a single stage compressor [J].Journal of Propulsion Technology,2009,30(4):419-424.(in Chinese)
点击查看大图
计量
- 文章访问数: 832
- HTML浏览量: 2
- PDF量: 7
- 被引次数: 0