固体燃料ATR涡轮/压气机匹配方法研究 *

推进技术 ›› 2015, Vol. 36 ›› Issue (3): 378-384.

固体燃料ATR涡轮/压气机匹配方法研究 *

刘洋,蒲晓航,李江,王伟,刘诗昌

西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072

发布日期:2021-08-15
作者简介:刘洋(1979—)，男，博士，副教授，研究领域为航空宇航推进理论与工程。

Research on Matching Method of Turbine/Compressor in 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,Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory，Northwestern Polytechnical University，Xi’an 710072，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： 为了获得固体燃料空气涡轮火箭发动机(SP-ATR)中涡轮和压气机的匹配工作特性，建立了涡轮和压气机的工作特性模型，根据SP-ATR转速、功率和背压平衡的工作特点，分别基于涡轮和压气机的工作环境先后采用两种不同的方法完成了二者的匹配。对比两种匹配方法得出结论:(1)基于涡轮的匹配方法与转速稳定过程一致，可确定特定飞行环境中发动机的转速；(2)基于压气机的匹配方法需要条件更少、适用范围更广，可用于特定转速调控方案下驱涡燃气流量的确定。两种匹配方法的计算结果相对AxSTREAM仿真结果的最大误差为10.75%，两种匹配方法的计算结果相差不超过8%。将建立的匹配方法应用于HARM弹自主爬升飞行过程，得到SP-ATR驱涡燃气流量的定量调控规律。

关键词: 匹配方法；固体燃料空气涡轮火箭；涡轮；压气机

Abstract: In order to obtain the cooperative operating characteristics of turbine and compressor in Solid Propellant Air Turbo Rocket (SP-ATR)，turbine and compressor operating characteristics models were built up firstly，and then，following the matching criteria of rotating and power and backpressure balance，two different matching methods were carried out according to each component working conditions. The comparison results show that:(1)The matching method based on turbine is consistent with the actual stabilizing process of rotor，which can be used to calculate the rotating speed of SP-ATR in a certain condition.(2)The matching method based on compressor needs fewer requirements and has broader application range. It can be used to calculate the gas mass flow according to the control scheme of rotating speed. The maximum error between the matching results of two methods and the simulation result of AxSTREAM is 10.75%，and the error between two matching methods is less than 8%. At last，the matching method was used for the missile HARM’s autonomous climbing flight，and the quantitative variation of turbo-driving gas mass flow in SP-ATR was obtained.

Key words: Matching method；Solid propellant air turbo rocket；Turbine；Compressor

刘洋,蒲晓航,李江,王伟,刘诗昌. 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,WANG Wei,LIU Shi-chang. Research on Matching Method of Turbine/Compressor in Solid Propellant Air Turbo Rocket[J]. Journal of Propulsion Technology, 2015, 36(3): 378-384.

参考文献

[1] 陈湘, 陈玉春, 屠秋野, 等. 空气涡轮火箭发动机的性能研究[J]. 导弹与制导学报, 2009, 29(2): 162～165.
[2] 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.
[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] 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. Investigation on Experimental Method for Solid Hydrocarbon Propellant ATR Afterburning Characteristics[J]. Journal of Propulsion Technology, 2013, 34(9): 1284-1289.)
[6] Bossard J A, Thomas M E. The Influence of Turbomachinery Characteristics on Air Turbo Rocket Engine Operation[R]. AIAA 2000-3308.
[7] John A Bossard, Matthew E Thomas. Customized Turbomachinery for Solid-Propellant Air Turbo Rockets [R]. AIAA 97-3257.
[8] Hongliang Pan, Peng Zhou. Performance Analysis of Liquid Air Turborocket[R]. AIAA 2008-70.
[9] 陈湘, 陈玉春, 屠秋野, 等. 固体推进剂空气涡轮火箭发动机的非设计点性能研究[J]. 固体火箭技术, 2008, 31(5): 445-448.
[10] Sullerey R K, Pradeep A M, Mayank Kedia. Performance Comparison of Air Turborocket Engine with Different Fuel System[R]. AIAA 2003-4417.
[11] Thomas M E. Monorotor Turbomachinery for Air-Turborocket Propulsion[R]. AIAA 95-2804.
[12] 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.
[13] Joshua A Clough, Mark J Lewis. Component Matching for the Air Turbo Rocket[R]. AIAA 2004-3648.
[14] 赵寅生. 鱼雷涡轮机原理[M]. 西安:西北工业大学出版社, 2001.
[15] 朱梅林. 涡轮增压器原理[M]. 北京:国防工业出版社, 1982.
[16] 西安交通大学. 离心压缩机原理[M]. 北京:机械工业出版社, 1980.
[17] 杨飒. 涡轮增压固冲发动机技术研究[D]. 西安:西北工业大学, 2013: 78-86.(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2013-11-21；修订日期:2014-04-10。作者简介:刘洋(1979—),男,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