固体燃料空气涡轮火箭发动机方案和技术研究

推进技术 ›› 2017, Vol. 38 ›› Issue (2): 249-256.

固体燃料空气涡轮火箭发动机方案和技术研究

刘洋¹,李江¹,刘诗昌¹,杨绪钊²,王伟³,蒲晓航⁴,祝珊¹

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,西北工业大学燃烧、流动和热结构国家级重点实验室，陕西西安 710072,北京航天伺服技术研究所，北京 100076,四川航天系统工程所，四川成都 610100,中国运载火箭技术研究院战术武器事业部，北京 100076,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

发布日期:2021-08-15
作者简介:刘洋，男，副教授，博士，研究领域为航空宇航推进理论与工程。

Scheme and Technology Investigation on Solid Propellant Air Turbo Rocket

Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Beijing Aerospace Servo Technology Research Institute，Beijing 100076，China,Sichuan Aerospace System Engineering Institution，Chengdu 610100，China,China Academy of Launch Vehicle Technology Tactical Weapons Division，Beijing 100076，China and Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 针对固体燃料空气涡轮火箭发动机(SP-ATR)的工作特点，提出了双燃气发生器的加力工作模式，并根据总体性能要求确定了部件的工作参数。主要采用数值模拟和实验研究相结合的手段，分别针对压气机和涡轮部件开展了气动设计和增压装置集成，获得了工作特性，并完成了增压系统工作特性的冷流实验验证。开展了考虑涡轮后低温旋流条件下多股气流的高效掺混燃烧研究，通过研究涡轮转速、空气入射角度、补燃室富燃燃气流量和富燃燃气射流位置对燃烧效率的影响，确定了原理样机和关键部件的恰当形式和布局方式。最终开展了原理样机的地面热试实验，验证了双燃气发生器的SP-ATR发动机的工作原理，热试实验结果表明燃气涡轮增压装置工作可靠，性能满足设计要求，其中压气机压比达到了3.3，转速为82kr/min，补燃室燃烧效率为85.21%。

关键词: 固体燃料空气涡轮火箭发动机；压气机；涡轮；燃气涡轮增压装置

Abstract: Based on the operation characteristics of Solid Propellant Air Turbo Rocket (SP-ATR)，new operation mode to realize the afterburning of SP-ATR based on the two independent gas generators was proposed. Series of study were carried out mainly by the numerical and experimental methods focusing on the aerodynamic design of compressor and turbine and the integration of turbocharger，through which the characteristics map of turbocharger was calculated by numerical simulation and performance verified by the cold flow experiments. The studies on mixed combustion between the low temperature and swirling gas by driving the turbine and air and fuel rich gas were carried out，in which the influences on combustion efficiency by different factors were studied，such as rotation speed of turbine，jet angle of the inlet air，the flux of fuel rich gas in the afterburner，jet position of fuel rich gas，and so on，that determined principle prototype and the scheme and layout form of the key components. Finally，the hot firing experiments were carried out，through which the SP-ATR based on two independent gas generators operation principle was examined，the turbocharger was tested to be safe and reliable and the performance of turbocharger could meet the design requirement，that the compressor pressure ratio was 3.3，the rotation speed was 82kr/min，and the combustion efficiency was 85.21%.

Key words: Solid Propellant Air Turbo Rocket (SP-ATR)，Compressor，Turbine，Turbocharger

刘洋,李江,刘诗昌,杨绪钊,王伟,蒲晓航,祝珊. 固体燃料空气涡轮火箭发动机方案和技术研究[J]. 推进技术, 2017, 38(2): 249-256.

LIU Yang¹,LI Jiang¹,LIU Shi-chang¹,YANG Xu-zhaO²,WANG Wei³,PU Xiao-hang⁴,ZHU Shan¹. Scheme and Technology Investigation on Solid Propellant Air Turbo Rocket[J]. Journal of Propulsion Technology, 2017, 38(2): 249-256.

参考文献

[1] Thomas M E, Bossard J A, Ostrander M J. Addressing Emerging Tactical Missile Propulsion Challenges with the Solid Propellant Air Turbo Rocket[R]. AIAA 2000-3399.
[2] Bossard J A, Thomas M E. Customized Turbomachinery for Solid-Propellant Air Turbo Rockets[R]. AIAA 97-3258.
[3] 屠秋野, 陈玉春, 苏三买, 等. 固体推进剂吸气式涡轮火箭发动机的建模及特征研究[J]. 固体火箭技术, 2006, 29(5): 317-345.
[4] 赵巍. 临近空间高速动力装置—空气涡轮火箭发动机(上)[J]. 工程热物理纵横, 2012, 6(9): 4-5.
[5] 潘宏亮, 周鹏. 空气涡轮液体火箭发动机建模与仿真研究[J]. 西北工业大学学报, 2009, 27(4): 492-498.
[6] Lilley J S. Experimental Evaluation of an Air Turbo Ramjet[R]. AIAA 94-3386.
[7] 莫然. 涡轮增压固体冲压发动机建模与性能分析[D]. 西安:西北工业大学硕士学位论文, 2010.
[8] 潘宏亮, 林彬彬, 刘洋. 加力式空气涡轮火箭发动机特性研究[J]. 固体火箭技术, 2010, 33(6): 650-655.
[9] 杨飒. 涡轮增压固冲发动机技术研究[D]. 西安:西北工业大学博士学位论文, 2012.
[10] 刘洋, 蒲晓航, 李江, 等. 固体燃料ATR涡轮/压气机匹配方法研究[J]. 推进技术, 2015, 36(3): 378-384. (LIU Yang, PU Xiao-hang, LI Jiang, et al. Research on Matching Method of Turbine/Compressor in Solid Propellant Air Turbo Rocket[J]. Journal of Propulsion Technology, 2015, 36(3): 378-384.)
[11] Yang Liu, Jiang Li, Guo-qiang He, et al. Design and Performance Analysis of Compressor in Solid Propellant Air Turbo Rocket (SPATR)[J]. Applied Mechanics and Material, 2014, 574: 190-196.
[12] 杨昀, 燃气涡轮增压固冲发动机压气机—涡轮方案设计及性能仿真[D]. 陕西:西北工业大学硕士学位论文, 2013.
[13] 李江, 刘诗昌, 刘洋, 等. 固体碳氢推进剂ATR二次燃烧特性实验研究[J]. 推进技术, 2013, 34(9): 1284-1289. (LI Jiang, LIU Shi-chang, LIU Yang, et al. Investigation on Experimental Method for Solid Hydrocarbon Propellant ATR Afterburning Characteristics[J]. Journal of Propulsion Technology, 2013, 34(9): 1284-1289.)
[14] 林彬彬. 涡轮增压固体冲压发动机掺混燃烧技术研究[D]. 陕西:西北工业大学硕士学位论文, 2011.
[15] 李江, 王伟, 刘洋, 等. 固体燃气涡轮火箭发动机燃烧组织优化研究[J]. 固体火箭技术, 2013, 36 (4): 462-466.
[16] 刘诗昌. 固体燃气涡轮火箭发动机地面试验原理研究[D]. 陕西:西北工业大学硕士学位论文, 2011.　　收稿日期:2016-10-05；修订日期:2016-10-25。作者简介:刘洋,男,副教授,博士,研究领域为航空宇航推进理论与工程。E-mail: liuyang802@nwpu.edu.cn(编辑:张荣莉)