再生冷却推力室耦合传热数值模拟
Numerical study on coupled heat transfer of thrust chamber with regenerative cooling
-
摘要: 对大推力液体火箭发动机再生冷却推力室内部燃气、室壁和再生冷却剂进行了耦合传热数值计算。采用二维轴对称N-S方程描述推力室内部燃气的湍流流动与传热,对冷却剂流动采用简化的一维模型,通过室壁的偶合传热采用一维传热模型。N-S方程的求解采用贴体坐标系下的有限容积法,速度和压强的耦合采用可压缩的SIMPLE算法。湍流的模拟采用可压缩的标准k-ε模型,辐射传热采用热流模型计算。研究表明,本文方法可较好地模拟燃气的二维流动,同时能快速计算壁面热流密度、壁温和冷却套温升,计算结果对大推力发动机推力室的设计具有一定的指导意义。Abstract: Numerical study on coupled heat transfer of the hot gas,chamber wall and coolant was performed.The two-dimensional Navier-Stokes equations were adopted to describe the hot gas flow,while a reduced one-dimensional model was employed for the coolant flow and heat transfer,and one dimensional heat transfer model was used to calculate the coupling heat transfer through the wall.The N-S equations were discretized by the finite volume method in body-fitted coordinates and the coupling of pressure and velocity was implemented with the compressible form of SIMPLE algorithm.The compressible form of the standard k-ε turbulence model was adopted to simulate the hot gas flow.Radiation of gas stream was also considered and simulated with the FLUX model.Results show that the method adopted in this paper can simulate two dimensional gas flow field well.Moreover, the method can calculate the heat flux through the wall,wall temperature and the temperature increase of coolant quickly.The numerical results are expected to be helpful for the design,especially for cooling scheme design of rocket engines.
-
[1] 休译尔 D K,黄 D,格雷特 R E,等著.液体火箭发动机现代工程设计[M].朱宁昌,葛李虎,陈祖奎,等译.北京:中国宇航出版社,2004. [2] Wang T S,Luong V.Numerical analysis of the hot gasside and coolant side heat transfer for liquid rocket engine combustion[R].AIAA92-3151,1992. [3] Carlos H M,Fernando L,Antonio F C da Silva,Jose N H.Numerical solutions of flows in rocket engines with regenerative cooling[J].Numerical Heat Transfer,Part A,2004,45:699-717. [4] 牛禄,程惠尔,李明辉.高宽比和粗糙度对再生冷却通道流动的影响[J].上海交通大学学报,2002,36(11):1 612-1615.NIU Lu,CHENG Hui-er,LI Ming-hui.Effects of aspect ratio and wall roughness on flow in regenerative cooling channels[J].Journal of Shang Hai Jiao Tong University.2002,36(11):1612-1615. [5] 韩振兴,林文,张远君,等.液体火箭发动机铣槽推力室三维壁温分布计算[J].航空动力学报,1996,11(2):145-148.HAN Zhen-xing,LIN Wen,ZHANG Yuan-jun,etal.Computing of three-cimensional wall temperature field in liquid rocket thruster chamber[J].Journal of Aerospace Power,1996,11 (2):145-148. [6] 李军伟,刘宇.一种计算再生冷却推力室温度场的方法[J].航空动力学报,2004,19(4):550-556.LI Jun-wei,LIU Yu.Method of computing temperature field in regeneratively-cooled thrust chamber[J].Journal of Aerospace Power,2004,19(4):550-556. [7] 李军伟,刘宇.三维数值模拟再生冷却喷管的换热[J].推进技术,2005,26(2):111-115.LI Jun-wei,LIU Yu.Three dimension numerical simulation of heat transfer in regeneratively cooled nozzle[J].Journal of propulsion technology,2005,26(2):111-115. [8] Sarkar S,Balakrishnan L.Application of a Reynolds-stress turbulence model to the compressible shear layer[R].ICASE Report 90-18,NASA CR 182002,1990. [9] Kim S E,Choudhury D.A near-wall treatment using wall functions sensitized to pressure gradient[J].In ASME FED Vol.217,Separated and Complex Flows.ASME,1995. [10] Miller R W.Flow measurement engineering handbook,second edition[M].McGraw Hill,New York,1983. [11] 杨世铭,陶文铨.传热学(第三版)[M].北京:高等教育出版社,1998. [12] Bartz D R.A simple equation for rapid estimation of rocket nozzle convective heat transfer coefficients[J].Jet Propulsion,1957,37:49-51.
点击查看大图
计量
- 文章访问数: 1789
- HTML浏览量: 2
- PDF量: 457
- 被引次数: 0