等直段直径对固体燃料超燃冲压发动机燃烧室性能的影响

推进技术 ›› 2015, Vol. 36 ›› Issue (6): 884-892.

等直段直径对固体燃料超燃冲压发动机燃烧室性能的影响

陶　欢,魏志军,迟鸿伟,孙巍伟,王宁飞

北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081,北京理工大学宇航学院，北京 100081

发布日期:2021-08-15
作者简介:陶　欢(1987—)，女，博士生，研究领域为固体燃料超燃冲压发动机。E-mail:taohuan@bit.edu.cn 通讯作者:魏志军(1971—)，男，博士，教授，研究领域为航空宇航推进理论与工程。
基金资助:
国家自然科学基金(51276020)。

Effects of Diameter of Cylindrical Section on Flowfield Characteristics of Solid Fuel Scramjet Combustor

School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China,School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China and School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究燃烧室内等直段直径的尺寸对固体燃料超燃冲压发动机燃烧室性能及流场特性的影响，基于国外研究者完成的固体燃料超燃冲压发动机的实验数据，对不同等直段直径燃烧室工作过程进行数值模拟。采用基于压力的二阶迎风差分数值方法，物理模型为轴对称结构，燃烧模型采用有限速率/涡耗散模型(Finite-Rate/ Eddy-Dissipation)，湍流模型采用SST k-ω模型。PMMA燃料进口边界由用户自定义函数的方式给定，分析不同等直段直径下超燃冲压发动机燃烧室内流场特性及其性能变化。数值模拟结果显示:随着等直段直径的增大，燃烧室可由壅塞状态转变为超声速流动状态，增大至某一数值(约为16.5mm)附近时，燃烧室出口可以达到完全膨胀状态。同时，燃烧室的燃烧效率逐渐增大，出口处燃烧效率由62.45%增大至72.74%。总压损失也逐渐增大，出口处最大值可达52%，而燃烧室推力逐渐减小。

关键词: 固体燃料超燃冲压发动机；数值模拟；流场特性；燃烧效率；总压损失；燃烧室推力

Abstract: In order to investigate the effects of the diameter of cylindrical section on the solid fuel scramjet combustor performance and the flowfield characteristics，based on a solid fuel scramjet experimental data，the numerical investigations concerning about the characteristics of the flow field in the solid fuel scramjet and the combustor performance are carried out when the diameter of the cylindrical section is changed. A second-order-upwind difference scheme and the pressure based solver were used for simulating the dynamic flow associated with an axis symmetric physical model. The combustion model in the numerical simulations was Finite-Rate/ Eddy-Dissipation and the turbulence model was the SST k-ω model. The boundary of PMMA solid fuel was defined as the user defined function way. The numerical simulation results indicate that with the increasing of the diameter of the cylindrical section，until the cylindrical section is open，the combustor will not be choked and the mainstream in the combustor becomes supersonic. In certain size of the cylindrical section diameter (about dcyl=16.5mm)，the outlet of the combustor is optimum-expansion. Generally，as the diameter of the cylindrical section increases，the combustion efficiency increases from 62.45% to 72.74% at outlet，while the total pressure loss also increases，which gets an maximum value of 52% at outlet in certain model，and the combustor thrust decreases.

Key words: Solid fuel scramjet；Numerical simulation；Flow field characteristics；Combustion efficiency；Total pressure loss；Combustor thrust

陶　欢,魏志军,迟鸿伟,孙巍伟,王宁飞. 等直段直径对固体燃料超燃冲压发动机燃烧室性能的影响[J]. 推进技术, 2015, 36(6): 884-892.

TAO Huan,WEI Zhi-jun,CHI Hong-wei,SUN Wei-wei,WANG Ning-fei. Effects of Diameter of Cylindrical Section on Flowfield Characteristics of Solid Fuel Scramjet Combustor[J]. Journal of Propulsion Technology, 2015, 36(6): 884-892.

参考文献

[1] 马岩, 赵庆华, 刘建全. 固体燃料的超声速燃烧研究进展[J]. 飞航导弹, 2009, (10):59-63.
[2] 刘萝威. 一种新型高密度燃料在高速气流中的点火性能[J]. 飞航导弹, 1997, (10).
[3] Witt M A. Investigation into the Feasibility of Using Solid Fuel Ramjets for High Supersonic/Low Hypersonic Tactical Missiles [R]. ADA214737.
[4] Angus W J. An Investigation into the Performance Characteristics of a Solid Fuel Scramjet Propulsion Device [R]. ADA246486.
[5] Ben-Yakar A, Natan B, Gany A. Investigation of a Solid Fuel Scramjet Combustor [J]. Journal of Propulsion and Power, 1998, 14(4): 447-455.
[6] Ben-Yakar A, Gany A. Experimental Study of a Solid Fuel Scramjet[R]. AIAA 94-2815.
[7] Jarymowycz T A, Yang V, Kuo K. Numerical Study of Solid Fuel Combustion under Supersonic Crossflows [J]. Journal of Propulsion and Power, 1992, 8(2): 346-353.
[8] Ben-Arosh R, Natan B, Spiegler E, et al. Mixing of Supersonic Airflow with Fuel Added Along the Wall in a Sudden Expansion Chamber [R]. AIAA 97-3241.
[9] Ben-Arosh R, Natan B, Spiegler E, et al. Fuel-Air Mixing in Solid Fuel Scramjet Combustors [J]. International Journal of Turbo and Jet Engines, 1998, 15: 223-234.
[10] Ben-Arosh R, Natan B, Spiegler E, et al. The Reacting Flowfield within a Supersonic Combustion Solid Fuel Ramjet [R]. AIAA 97-3119.
[11] Ben-Arosh R, Natan B, Spiegler E, et al. Theoretical Study of a Solid Fuel Scramjet Combustor [J]. Acta Astronautica, 1999, 45(3): 155–166.
[12] Sun Bo, Wu Xiaosong, Xia Qiang, et al. Numerical Analysis of Solid Fuel Scramjet Combustors [R]. CISE 2009-5363946.
[13] Shimon S and Gany A. Testing Metalized Solid Fuel Scramjet Combustion [R]. ISABE 2007-1176.
[14] 杨向明, 刘伟凯, 陈林泉, 等. 固体燃料超燃冲压发动机原理性试验研究[J].固体火箭技术, 2012, 3: 319-324.
[15] Gruber M R, Baurle R A, Mathur T, et al. Fundamental Studies of Cavity-Based Flameholder Concepts for Supersonic Combustors [J]. Journal of Propulsion and Power, 2001, 17(1):146-153.
[16] Tsai Tzunghang, Li Maojeng, Shih Iyou, et al. Experimental and Numerical Study of Autoignition and Pilot Ignition of PMMA Plates in a Cone Calorimeter [J]. Combustion and Flame, 2001, 124(3):466-480.
[17] 潘余, 王振国, 刘卫东. 超燃冲压发动机燃烧效率测量方法简介[J].实验流体力学, 2007, 21(2): 68-73.(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2014-04-21；修订日期:2014-06-12。基金项目:国家自然科学基金(51276020)。作者简介:陶欢(1987—),女,博士生,研究领域为固体燃料超燃冲压发动机。E-mail:taohuan@bit.edu.cn 通讯作者:魏志军(1971—),男,博士,教授,研究领域为航空宇航推进理论与工程。E-mail:wzj@bit.edu.cn