热辐射影响下的尾喷管气膜冷却特性研究

With the increase of gas temperature and radiation participation medium in gas，thermal radiation has become a prominent factor in the design of tail nozzle. In order to explore the influence of thermal radiation and structural parameters on the cooling characteristics of the tail nozzle air film， an axisymmetric tail nozzle simplification model was established， and the influence of radiation on the cooling of the tail nozzle was explored by numerical simulation. It was found that the cooling effect of the wall was reduced by thermal radiation，and the thermal radiation effect was related to the cooling structure. When the aperture of the air film increased from 2 mm to 3 mm and 4 mm，the radiant heat flux increased by 13% and 6%，respectively，and when the inclination angle of the air film aperture increased from 15° to 30° and 45°， respectively， the radiant heat flux was basically unchanged. When the main components changed from pure air to 10% carbon dioxide and 20% carbon dioxide，the radiant heat flux increased by 17% and 21%， respectively. In practical applications， the content of carbon dioxide and other radiant gasses in the mainstream components should be reduced as much as possible.