液氧/煤油发动机喷管内型面对尾焰特性影响  

Impact of the Inner Nozzle Surface on Plume Characteristics of LO_2/Kerosene Engine

作　　者：蔡红华[1] 聂万胜[1] 郑刚[1] 

机构地区：[1]中国人民解放军装备学院航天装备系,北京101416

出　　处：《导弹与航天运载技术》2015年第5期35-38,共4页Missiles and Space Vehicles

基　　金：国家自然科学基金(91441123)

摘　　要：通过数值模拟研究了3种不同喷管内型面发动机的尾焰特性,将计算结果与某试验液氧/煤油发动机进行比较,分析喷管内型面对尾焰速度场、温度场和湍动能分布的影响。结果表明,采用数值仿真方法可以有效模拟出发动机尾焰的马赫盘和连续激波等基本结构、特性;相比于钟形喷管,锥形喷管和内型面为直线的喷管由于喷管扩张段内燃气存在非轴向流动,造成大量能量损失的同时引起了斜激波的产生,导致喷管出口膨胀更加剧烈、尾焰中连续激波更加明显。Numerical simulations were carried out to analyze plume characteristics of three engines of different inner nozzle surface,the calculated results were compared to a test LO2/kerosene engine, the impact of inner nozzle surface on chamber pressure and velocity field, temperature field, turbulent kinetic energy distribution of plume were analyzed. The results show that the basic structure and characteristic of the engine plume such as Mach disk and continuous shock can be simulated effectively. Compared to the bell nozzle, because of the presence of non-axial movement of gas in nozzle expansion section, the conical nozzle and the linear nozzle made the oblique shock wave generation as time as there was a lot of energy loss. As a result, the expansion out of nozzle was more intense and the continuous shock in plume was more obvious.

关 键 词：液氧/煤油发动机 喷管内型面 尾焰 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程] V43