高速飞行器发动机舱内元组件热环境研究

为满足高速飞行器发动机舱内元组件热防护及热管理的需要,就热环境问题提出了严格准确的定义;然后基于此定义与准则关系式建立了一套估算高速飞行器发动机舱内元组件热环境的传热模型。利用建立的稳态热平衡方程,通过迭代求解得到某高速飞行器发动机舱内元组件在典型飞行工况下的一维热环境。对典型飞行工况下不同参数进行了系列研究。结果表明:舱内元组件的热环境随着冷却气流流量的减少而恶化,当冷却气流质量流量从1.0 kg/s减少至0.5 kg/s时,冷却气流出口温度增加了0.185 4无量纲温度。舱内元组件自身发热量对冷却气流的温升有较大影响;且冷却气流流量越小,温升越大。当冷却气流质量流量为1.0 kg/s时,元组件自身发热量导致了0.139无量纲温升,而当冷却气流质量流量为0.5 kg/s时,元组件自身发热量导致了0.294 9无量纲温升。

Investigation on thermal environment of components in high speed aircraft nacelle

In order to meet the demand of the thermal protection and thermal management for components in high speed aircraft nacelle, an accurate definition of thermal environment was proposed, then based on the definition and empirical formula the heat transfer model for estimating thermal environment of components in high speed aircraft nacelle was set up. The one dimensional steady thermal environment of components in the high speed aircraft nacelle under typical fly condition was obtained by iterative computating the equation of steady state heat balance. A series of studies with different parameters under typical fly condition were carried out. The results show that, the thermal environment of components in nacelle deteriorates with the reducing mass flowrate of coolant air, the outlet temperature of coolant air increases 0.1854, when the mass flowrate of coolant air varies from 1.0 to 0.5. The temperature rise of coolant air is influenced by the heat release rate of components in nacelle, and the temperature rise increases with the decrease of the mass flowrate of coolant air. The heat release rate of components in nacelle leads to 0.139 temperature rise when the mass flowrate of coolant air is 1.0. And the heat release rate of components in nacelle leads to 117.94K temperature rise when the mass flowrate of coolant air is 0.2949.