通道深宽比对液体火箭发动机推力室再生冷却的影响  

Effect of aspect ratio on heat transfer and fluid flow in regenerative cooling channel of liquid rocket engine thrust chamber

作　　者：吴峰[1] 曾敏[1] 王秋旺[1] 孙纪国 

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 [2]北京航空动力研究所,北京100076

出　　处：《航空动力学报》2007年第1期114-118,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目(50323001)

摘　　要：应用湍流模型对液体推进剂火箭发动机再生冷却推力室通道的流动与传热进行了三维数值模拟,冷却工质为氢气,其密度、导热系数、动力粘度随着温度和压力而变化,冷却剂比热容及金属固体物性随着温度而变化.计算采用标准k-ε两方程湍流模型及气-固耦合算法.保持再生冷却通道个数及冷却工质进口流量不变,通过改变通道肋壁厚度来改变冷却通道深宽比,研究不同深宽比对推力室壁面再生冷却效果的影响规律.计算结果表明:增加通道深宽比对推力室壁面能够起到强化传热的作用,但同时也增加了冷却通道的进出口压差.这是由于冷却工质流速的增高,从而提高了推力室传热系数.随着深宽比不断增加,推力室再生冷却效果趋于饱和,而冷却工质进出口压降则不断上升.The turbulent fluid flow and heat transfer in a regenerative-cooling channel of liquid propellant rocket engine were numerically investigated by solving three-dimensional elliptical Navier-Stokes equations. The coolant was hydrogen, whose thermal properties such as thermal conductivity, density, dynamical viscidity, etc varied with both temperature and pressure. The specific heat of hydrogen and thermal properties of solid metal varied with temperature. The standard k-ε turbulence model and gas-solid coupled technique were adopted. An optimized calculation scheme was applied so as to find the best design for rocket combustion chamber. In the scheme, the cooling channel aspect ratio varied with the thickness of channel ribs while the channel number is fixed and coolant mass flow rate remains constant. The simulation results show that the heat transfer of rocket chamber will be enhanced when increasing the aspect ratio, but the pressure drop will increase simultaneously. The cooling effect of rocket thrust chamber will to be reach saturated as the aspect ratio becomes large enough.

关 键 词：航空、航天推进系统 液体推进剂火箭发动机 再生冷却通道 通道深宽比 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]