固体火箭燃气超燃冲压发动机燃烧组织技术研究

推进技术 ›› 2019, Vol. 40 ›› Issue (1): 140-150.

固体火箭燃气超燃冲压发动机燃烧组织技术研究

高勇刚¹,刘洋¹,余晓京²,霍东兴³,杨玉新³

西北工业大学燃烧、流动和热结构国家级重点实验室，陕西西安 710072,西北工业大学燃烧、流动和热结构国家级重点实验室，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西安航天动力技术研究所，陕西西安 710025,西安航天动力技术研究所，陕西西安 710025

发布日期:2021-08-15
作者简介:高勇刚，硕士生，研究领域为固体火箭燃气超燃冲压发动机。 E-mail: 1078493053@qq.com 通讯作者:刘洋，博士，副教授，研究领域为航空宇航推进理论与工程。 E-mail: liuyang802@nwpu.edu.cn。
基金资助:
国家自然科学基金( 51506178)

Research on Combustion Organization Technology of the Solid Rocket Fuel Gas Scramjet

National Key Laboratory of Combustion，Flow and Thermo-Structure，Northwestern Polytechnical University， Xi’an 710072，China,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,Xi’an Aerospace Power Technology Research Institute，Xi’an 710025，China and Xi’an Aerospace Power Technology Research Institute，Xi’an 710025，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究一次火箭室压、一次燃烧产物组分、不同燃烧室构型对于固体火箭燃气超燃冲压发动机性能的影响，采用全流道一体化数值模拟的计算方法，研究了纯气相一次燃烧产物的火箭室压、不同碳颗粒比例的一次燃烧产物、 40%的碳颗粒含量的一次燃烧组分下分流道以及波瓣结构两种混合增强方式三种因素对于中心支板式固体火箭燃气超燃冲压发动机补燃室流动燃烧以及发动机性能的影响。结果表明:一次火箭室压增大的同时，由于一次火箭喷管面积比相应地随之增大，一次火箭喷管出口射流的平均压强并未增加，避免了壅塞现象的产生，同时随着一次火箭室压的增加，发动机的推力以及比冲均呈上升趋势；碳颗粒的含量越少，发动机的性能越高，发动机的性能对于推进剂的要求较高；两种混合增强方式对于补燃效率的提高意义明显，合理设计混合增强装置有助于发动机性能的提高。

关键词: 固体火箭；超燃冲压发动机；支板火箭；碳颗粒燃烧；增强掺混；燃烧效率；数值模拟

Abstract: In order to study the effects of primary rocket pressure，primary combustion product compositionand different combustor configurations on the performance of solid rocket fuel gas scramjet，the calculation meth. od of integrated numerical simulation of full flow path was used to study the effect of the three factors of pure gas-phase primary products with different rocket pressure，primary combustion products with different proportion of carbon particle，40% of the carbon content of the primary combustion component with two kinds of hybrid en.hancement modes of staggered structure and shunt on the flow combustion of engine combustor and the perfor.mance of the center supported plate solid rocket fuel gas scramjet. The results show that the average pressure ofprimary rocket nozzle exit does not increase due to the increase of the area ratio of primary rocket nozzle when pri.mary rocket pressure increases，avoiding the occurrence of congestion. Meanwhile，the engine thrust and specificimpulse increase with the increase of primary rocket pressure. The lower content of carbon particle，the higherperformance of the engine is. The engine performance highly requires for propellant. The two kinds of hybrid en. hancement methods have obvious significance for the improvement of combustion efficiency. The design of reason.able hybrid enhancement device is very helpful to the improvement of engine performance.

Key words: Solid rocket；Scramjet engine；Plate rocket；Carbon particle combustion；Enhanced mix. ing；Combustion efficiency；Numerical simulation

高勇刚,刘洋,余晓京,霍东兴,杨玉新. 固体火箭燃气超燃冲压发动机燃烧组织技术研究[J]. 推进技术, 2019, 40(1): 140-150.

GAO Yong-gang¹,LIU Yang¹,YU Xiao-jing²,HUO Dong-xing³,YANG Yu-xin³. Research on Combustion Organization Technology of the Solid Rocket Fuel Gas Scramjet[J]. Journal of Propulsion Technology, 2019, 40(1): 140-150.

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