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

作　　者：张宏伟[1] 陶文铨[1] 何雅玲[1] 丰镇平[1] 

机构地区：[1]西安交通大学动力工程多相流国家重点实验室,陕西西安710049

出　　处：《航空动力学报》2006年第5期930-936,共7页Journal of Aerospace Power

基　　金：国家自然科学基金的资助(50476046)

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。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 diseretized 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 κ-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 ean 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.

关 键 词：航空 航天推进系统 火箭发动机 再生冷却 耦合传热 数值模拟 湍流 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]