摘要
对TRRE发动机关键技术难点及技术途径进行了初步分析,对北京动力机械研究所原理样机研制进展进行了简要介绍,并结合原理样机流道设计与数值仿真研究获得的性能数据,开展了TRRE发动机推进性能探索研究,初步验证了TRRE发动机在兼具加速、巡航、机动等方面的性能优势。研究结果表明,在适当兼顾低马赫数大推力需求和Ma=6纯冲压工况高比冲需求的情况下,发动机在宽马赫数工作范围具有较大范围、灵活便捷的推力调节能力,可满足高低速通道平稳接力需求,表现出极具优势的加速、机动飞行和高马赫数巡航的适应性。
The key technical difficulties and performance of the TRRE were studied. A brief introduction was conducted on the progress of the principle prototype from the Beijing Power Machinery Institute. The performance data from the flow channel design of the principle prototype and numerical simulations were utilized to assess the propulsion performance of the TRRE engine,which primitively validated its comprehensive advantages on the acceleration,cruising,mobility and other aspects. The results show that the TRRE engine can reconcile the demands of high thrust at lower Mach numbers and high specific impulse at a Mach number of 6.0（pure scramjet mode）. In a wide Mach number operating range,the TRRE engine provides the relatively wide,flexible and convenient adjustment ability in the thrust. It can satisfy the smooth relay between the high and low speed channels,illustrating the advantageous adaptability in the acceleration,maneuver flight and high Mach number cruising.
作者
韦宝禧
凌文辉
冮强
魏祥庚
秦飞
何国强
WEI Bao-xi LING Wen-hui GANG Qiang WEI Xiang-geng QIN Fei HE Guo-qiang(Science and Technology on Scramjet Laboratory, Beijing Power Machinery Institute , Beijing 100074,China Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi＇an 710072, China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2017年第2期298-305,共8页
Journal of Propulsion Technology
关键词
临近空间及空天飞行器
组合发动机
性能分析
Near space and aerospace vehicle
Combined engine
Performance analysis
