关键词: 第三流体, 冷却循环, 流动换热, 数值模拟

Abstract: Aiming at a kind of liquid oxygen kerosene rocket engine cooling system, in this paper, numerical calculation and simulation of the third fluid cooling circle was proceeded.Based on the computational fluid dynamics(CFD), using three-dimensional fluid-structure coupling algorithm, the flow and heat transfer characteristics of the cooling channels was calculated and analyzed.The results showed that when the mass flow of coolant raises by about 0.01kg/s, the wall temperature of thrust chamber and throat temperature decreases by about 9K and 15K respectively, while the outlet dryness of the coolant decreases by about 0.011.the influence of inlet temperature was affected by the coolant flow, when the flow is smaller, the influence of the inlet temperature can be ignored, while the flow is larger, the dryness of coolant raises by about 0.009 with the increasing of inlet temperature by 10K.The pressure loss of cooling channel raised by 54kPa with the growing of coolant flow by 0.01kg/s, and it decreased by about 24kPa with the raising of inlet-temperature by 10K.Therefore, the best range of coolant flow and inlet-temperature was obtained:12-14.4kg/s and 300-350K respectively.

Key words: third fluid, cooling circle, flow and heat transfer, numerical simulation