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为了研究冷却剂温度分层的形成机理及其对流动和换热的影响,应用雷诺应力模型(RSM)对液体火箭发动机推力室再生冷却通道的流动与传热进行了三维数值模拟,冷却剂为气氢,考虑其物性随温度和压力的变化.所得结果表明:冷却剂在非流动方向会出现温度分层现象,随着冷却剂的不断受热,温度分层现象越明显,由于喉部二次流加强了冷却剂间的混合,在喉部区域温度分层被减弱,温度分层对冷却剂温升及压降影响较小,严重影响气壁温度的估算.
In order to study the formation mechanism of coolant temperature stratification and its influence on flow and heat transfer, a three-dimensional numerical simulation of the flow and heat transfer in the regenerative cooling passage of the thrust chamber of a liquid propellant rocket engine is carried out using Reynolds stress model (RSM). The coolant is Gas and hydrogen, taking into account its physical and chemical properties with temperature and pressure changes.The results show that: the coolant in the non-flow direction of the temperature stratification occurs, with the coolant continues to heat, the more obvious temperature stratification, the throat of the second The flow strengthens the intermixing of coolant, the temperature stratification in the throat area is weakened, and the temperature stratification has little effect on the temperature rise and pressure drop of the coolant, which seriously affects the estimation of the wall temperature.