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CLC number: V43

On-line Access: 2017-01-24

Received: 2016-07-04

Revision Accepted: 2016-08-22

Crosschecked: 2017-01-05

Cited: 0

Clicked: 1653

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Zhong Lv

http://orcid.org/0000-0003-3741-3186

Zhi-xun Xia

http://orcid.org/0000-0002-2315-3005

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Journal of Zhejiang University SCIENCE A 2017 Vol.18 No.2 P.106-112

http://doi.org/10.1631/jzus.A1600489


Preliminary experimental study on solid-fuel rocket scramjet combustor


Author(s):  Zhong Lv, Zhi-xun Xia, Bing Liu, Li-ya Huang

Affiliation(s):  Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   zxxia@nudt.edu.cn

Key Words:  Solid fuel, Rocket scramjet, Dual combustor, Direct-connect experiment


Zhong Lv, Zhi-xun Xia, Bing Liu, Li-ya Huang. Preliminary experimental study on solid-fuel rocket scramjet combustor[J]. Journal of Zhejiang University Science A, 2017, 18(2): 106-112.

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author="Zhong Lv, Zhi-xun Xia, Bing Liu, Li-ya Huang",
journal="Journal of Zhejiang University Science A",
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A1 - Zhong Lv
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J0 - Journal of Zhejiang University Science A
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PB - Zhejiang University Press & Springer
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DOI - 10.1631/jzus.A1600489


Abstract: 
Liquid or gaseous fuel scramjet technology has made great progress, and there has been some research attention to solid-fuel scramjet. A new scramjet configuration using solid fuel as propellant, namely solid-fuel rocket scramjet, is tested experimentally. It consists of two combustors. One is a rocket combustor used as gas generator, and the other is a supersonic combustor used for secondary combustion. The experiment simulates a flight Mach number of 4 at high altitude (stagnation temperature and pressure are 1170 K and 1.16 MPa, respectively), and metalized solid fuel is used as propellant. The results reveal that fuel-rich gas from the gas generator can burn with air in the supersonic combustor. Preliminary evaluation results show that the combustion efficiency of the propellant is about 90%, and the total pressure recovery coefficient in the supersonic combustor is about 0.6. These results indicate that the configuration of solid-fuel rocket scramjet is feasible.

固体火箭超燃冲压发动机燃烧室初步实验研究

目的:通过发动机直连式实验,验证燃气发生器产生的富燃燃气可以在超声速气流中二次燃烧,进而证明固体火箭超燃冲压发动机方案的可行性,并初步评估固体火箭超燃冲压发动机燃烧室的工作性能。
创新点: 1. 提出固体火箭超燃冲压发动机构型方案,并开展固体火箭超燃冲压发动机燃烧室直连式实验研究;2. 验证了固体火箭超燃冲压发动机构型可行;3. 初步评估了固体火箭超燃冲压发动机燃烧室的工作性能。
方法:1. 通过直连式实验测定固体火箭超燃冲压发动机燃烧室的工作参数(图2、3和4);2. 通过实验现象(图8)和数据处理,确定燃气发生器产生的富燃燃气可以在超声速燃烧室中燃烧,进而确定固体火箭超燃冲压发动机方案的可行性;3. 初步确定发动机燃烧室的工作性能(公式(6)和(7))。
结论: 1. 燃气发生器中产生的富燃燃气可以在超声速燃烧室中燃烧,固体火箭超燃冲压发动机构型方案可行;2. 初步评估了固体火箭超燃冲压发动机燃烧室的工作性能,总压恢复系数约为0.6,燃烧效率约为90%;3.燃气发生器产生的部分一次燃气沉积于燃气发生器喉部,使燃气发生器的工作压力增加,进而引起富燃燃气质量流量的增加;4. 燃烧室中的总压损失主要集中在富燃燃气入口处,总压损失主要由射流引起的激波和燃气二次燃烧引起。

关键词:固体燃料;火箭超燃冲压发动机;双燃烧室;直连式实验

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