Full 3D relative stream surface iterative solution of the multistage transonic turbine in liquid rocket engines
-
摘要: 为了研究液体火箭发动机涡轮内流场,发展了一种基于相对流面理论和流线曲率法的多级跨声速叶轮机械流场计算方法.首先使用流线曲率法求解流面内的流场,再采用全三维流面迭代的方法得到三维流场.计算过程中通过临界流量的对比确定跨声速流道内的喉部位置,采用混合平面法将动、静叶间的非定常流动转化为定常流动.激波和黏性等损失通过相应的损失模型进行计算.对于多级流道内不同的超声速/亚声速流动状态则采用穷举法计算所有可能情况并用出口参数筛选最接近真实情况的结果.该方法准确地计算出了多级跨声速涡轮流场中的流动参数分布和性能参数,为进一步改进涡轮设计、提高涡轮性能提供了理论依据.Abstract: A three dimension transonic flow field solver for a multistage turbine in liquid rocket engine was developed based on relative stream surface theory and streamline curvature approach. The stream surfaces were calculated with the streamline curvature approach and the full three dimension flow field was solved by stream surface iterations. The throat was located by comparison of critical mass flux. The interaction between vanes and blades was dealt with the idea of mixing plane. Loss models were adopted to calculate the influence of shock wave and viscosity. The supersonic/subsonic flow conditions in different stages were filtered by comparison of exit parameters. The solver gave accurate flow parameter distribution and performance parameters of transonic multistage turbine, thus provides a theoretical basis for improving the design and performance of liquid rocket engine turbine.
-
[1] Denton J D.An improved time-marching method for turbomachinery flow calculation[J].Journal of Engineering for Power, 1983, 105:514-521 [2] Denton J D.Calculation of three dimensional flow through any type of turbomachine[R].AGARD, Lecture Series 140, 1985 [3] Hah C A.A navier-stokes analysis of 3d turbulent flows inside turbine blade rows[J].Journal of Engeering for Power, 1984(106):421-429 [4] Dawes W N.Development of a three-dimensional navier-stokes solver for application to all types of turbomachinery[R].ASME.Paper No.88-GT-70, 1988 [5] Wu Chunghua.A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial-, radial-, and mixed-flow types[R].NACA, TN-2604, 1952 [6] Boyer K M, O-Brien W F.Application of an improved streamline curvature approach to a modern, two-stage transonic fan:comparison with data and cfd[R].ASME Turbo Expo 2002.GT2002-30383, 2002 [7] 华鑫, 乔渭阳, 卢蕊.基于流线曲率法的航空轴流涡轮损失模型研究[J].机械设计与制造, 2005(12):12-14 Hua Xin, Qiao Weiyang, Lu Rui, et al.A study on different loss models in axial-flow turbines based on the methed of streamline-curvature[J].Machinery Design & Manufacture, 2005(12):12- 14(in Chinese) [8] Denton J D, Dawes W N.Computational fluid dynamics for turbomachinery design[J].Journal of Mechanical Engineering Science, 1998, 213(107): 107-124 [9] 汪庆桓, 吴文权, 朱根兴, 等.轴流式压气机两类流面迭代三元完全解[J].工程热物理学报, 1983, 4(4): 336-346 Wang Qinghuan, Wu Wenquan, Zhu Genxing, et al.Solution of three-dimensional compressible flow in an axial-flow compressor stator by the use of s1 and s2 relative surfaces[J].Journal of Engineering Thermophysics, 1983, 4(4): 336-346(in Chinese) [10] 马冬英, 梁国柱.基于S1, S2流面理论的液体火箭发动机涡轮内部流场计算[J].推进技术, 2008, 29(4): 401-406 Ma Dongying, Liang Guozhu.Calculation of the internal now for turbine of liquid rocket engine based on the theory of S1, S2 stream surface[J].Journal of Propulsion Technology, 2008, 29(4): 401-406(in Chinese) [11] Bloch G S.Flow losses in supersonic compressor cascades[D].Blacksburg, Virgina: Virginia Polytechnic Institute and State University, 1996
点击查看大图
计量
- 文章访问数: 1332
- HTML全文浏览量: 107
- PDF下载量: 519
- 被引次数: 0