【摘要】 目的研究载人航天器舱内的气流组织性能 ,分析斜进风通风方式下舱内的通风换热 ,为通风换热的设计提供依据。方法由物理模型 ,引入合理假设 ,建立描述舱内流动和传热的数学模型 ,采用交错网格的SIMPLE算法 ,从进风角度、换热性能、温度、速度的均匀性及环境的舒适性等方面综合分析该通风方式的特点。结果斜进风方式不存在明显的短路问题 ,换热能力较好 ;舱内工作区速度、温度的均匀性和舒适性提高 ;投入能量得到了较好的利用 ;两侧壁换热虽失去对称性 ,但其换热能力并没有迥然差别 ;进风角度小于 45°时温度场、速度场的均匀性比进风角度大于 45°时要好一些 ,但由于V ·△T的值保持在一定水平 ,此时的换热能力与进风角度大于 45°时相比变化不大。结论二维斜进风通风方式气流组织性能较好 ,但流动的可控性较差 ;可以适当地设计通风方式和角度 ,增加流动的可控性 ,并使换热和均匀性同时优化 ;空间站载人舱可采用角度变动范围在 1 5°～ 75°之间的风向可调式小开口斜进风方式。更多还原

【Abstract】 Objective To investigate the ventilation organization in a square space with slot inlet and oblique inlet flow and to try afford some useful suggestion for the design of ventilation. Method Based on physical model, control equations depicting the ventilation and heat transfer in cabin were given. The inlet air direction, velocity, temperature, convective heat transfer capability and environment amenity were numerically simulated with staggered grid SIMPLE method. Result As far as the cases of oblique inlet flow direction were concerned, the research indicated that the heat transfer capability, the homogeneity, amenity and effectiveness of input energy were acceptable although the flow patterns were asymmetric. When the angle between the inlet flow direction and ceiling was smaller than 45 degree, there were better homogeneity of temperature and velocity fields. The heat transfer performance,was not sensitive to the inlet flow angle. Conclusion The 2D ventilation configuration with oblique inlet flow direction has good thermal performance but the control of flow pattern is not satisfactory. It is possible to improve the homogeneity of temperature and velocity, heat transfer capability and the control of flow pattern simultaneously by proper organization of V·△T. The research recommends independent inlet apertures with adjustable angle between 30～45 degree.更多还原