固体火箭燃气超燃冲压发动机概念分析(Ⅰ)——全流道一体化设计  

Analysis of the conceptual solid rocket fuel gas scramjet engine(Ⅰ)——Integrated design of the full flow path

作　　者：刘洋[1] 高勇刚[1] 余晓京 霍东兴[3] 杨玉新[3] LIU Yang;GAO Yonggang;YU Xiaojing;HUO Dongxing;YANG Yuxin(National Key Laboratory of Combustion,Flow and Thermo-Structure Northwestern Polytechnical University,Xi＇an 710072,China;School of Power and Energy,Northwestern Polytechnical University,Xi＇an 710072,China;The 41st Institute of the Fourth Academy of the CASC,Xi＇an 710025,China)

机构地区：[1]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072 [2]西北工业大学动力与能源学院,西安710072 [3]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2018年第4期403-413,共11页Journal of Solid Rocket Technology

基　　金：航天创新基金项目

摘　　要：针对中心支板式固体火箭燃气超燃冲压发动机,从大气模型、进气道、燃烧室及尾喷管四个模块出发完成了其一体化流道设计。针对所设计的发动机设计点及非设计点,采用全流道一体化数值模拟的方法对发动机设计的合理性进行了验证。研究结果表明,发动机设计点及非设计点进气道均已启动,燃烧室及后体工作状态良好,验证了发动机设计的合理性;碳颗粒的燃烧效率限制了发动机整体的燃烧效率水平及发动机性能,发动机设计点整体的燃烧效率为49%,比冲仅有3674.61 m/s,提升碳颗粒的燃烧效率作为固体火箭燃气超燃冲压发动机性能提升的关键点;由于燃烧室长度可能较短,构型较为简单,这对于发动机的一体化设计是不利的,如果能合理布置燃烧室构型,则对固体火箭燃气超燃冲压发动机的二次补燃效率及发动机性能的提升有所帮助。For the center supported plate solid rocket fuel gas scramjet engine,the integrated flow path design was completed from the four modules of atmospheric model,intake,combustor and nozzle.Aiming at the design point and the non-design point of the engine,the rationality of the engine design was verified by the integrated numerical simulation of full flow path.The results show that the inlet of the engine design point and non-design point are all started. The designed combustor and the aft-airframe work well,which verifies the rationality of the engine design.The combustion efficiency of carbon particles limits the overall combustion efficiency and the performance of the engine.The overall combustion efficiency is 49% and the specific impulse is only 3674.61 m/s for the engine design point.The increase of carbon particles combustion efficiency is the key point for the performance improvement of the solid rocket fuel gas scramjet. The length of combustor may be shorter and the configuration is simple,which is unfavorable for the integrated design of the engine.If the combustor configuration can be reasonably arranged,it may be helpful for the improvement of secondary afterburning efficiency and engine performance of the solid rocket fuel gas scramjet.

关 键 词：固体火箭燃气超燃冲压发动机 一体化设计 支板火箭 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]