PDF下载 分享
[1]陈 磊,李光熙,梁俊龙,等.地面试验中的超燃冲压发动机特性分析[J].火箭推进,2023,49(06):73-81.
　CHEN Lei,LI Guangxi,LIANG Junlong,et al.Analysis of scramjet characteristics in ground experiment[J].Journal of Rocket Propulsion,2023,49(06):73-81.
点击复制

地面试验中的超燃冲压发动机特性分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 49 期数: 2023年06期 页码: 73-81 栏目: 目次 出版日期: 2023-12-25
Title:
Analysis of scramjet characteristics in ground experiment
文章编号:
1672-9374(2023)06-0073-09
作者:
陈 磊1; 李光熙2; 梁俊龙1; 王玉峰1; 杜 泉1; 李江涵1
1.西安航天动力研究所,陕西 西安 710100; 2.航天推进技术研究院,陕西 西安 710100
Author(s):
CHEN Lei1;  LI Guangxi2;  LIANG Junlong1;  WANG Yufeng1;  DU Quan1;  LI Jianghan1
1.Xi'an Aerospace Propulsion Institute, Xi'an 710100, China; 2.Academy of Aerospace Propulsion Technology, Xi'an 710100, China
关键词:
超燃冲压发动机;  直连式试验;  自由射流试验;  进气道内流特征;  进-发匹配特性;  发动机总体性能
Keywords:
scramjet engine;  direct connection experiment;  free flow experiment;  inlet flow pattern;  inlet-engine matching;  engine performance
分类号:
V235.21
文献标志码:
A
摘要:
直连式试验和自由射流试验是冲压发动机开展地面模拟试验验证过程中最为普遍的两类试验。通过对比两类试验对来流条件的实现情况,说明加热器工作参数和来流组分等模拟要素符合试验要求,在此基础上分析同款超燃冲压发动机的直连式和自由射流试验结果,并结合仿真分析结果开展论述。结果表明:针对相近试验工况,两类试验中进气道流动形态一致性较好; 进-发匹配工作特性方面,自由射流试验中的结尾激波位置普遍靠后,其安全工作裕度高于直连式试验; 在直连式试验中,基于沿程静压测值方法得到的发动机比冲与自由射流试验台测得的发动机比冲接近。
Abstract:
Direct connection experiment and free flow experiment are the two most common experiments in the ground simulation experiment of scramjet engine.By comparing the concrete simulation of two kinds of experiments, it indicated that the operating parameters of the heater and incoming flow components meet the experiment requirements.On this basis, the performance of the same type of scramjet in these two kinds of experiments was analyzed, and combined with the numerical simulation analysis results to carry out the discussion.The results show that, in the two kinds of experiment, the flow pattern of the inlet is consistent.In terms of the working characteristics of the inlet and engine matching, the position of the ending shock wave in the free flow experiment is generally far behind, and its safety margin is higher than that in the direct connection experiment.The engine specific impulse ratings obtained from the two types of experiments are similar.The results show that the relative accuracy of engine performance can be obtained by the method based on the static pressure along the direct connecting experiment.

参考文献/References:

[1] 胡建新,张为华,夏智勋,等.冲压推进技术[M].长沙:国防科技大学出版社,2013.
[2] HEISER W H,PRATT D T.高超声速吸气式推进[M].俞刚,译.北京:航空工业出版社,2013.
[3] 史超.冲压发动机地面试验技术及试验能力述评[J].火箭推进,2021,47(1):1-12.
SHI C.Review of ramjet ground-test facilities and relevant technology development[J].Journal of Rocket Propulsion,2021,47(1):1-12.
[4] SMART M K,HASS N E,PAULL A.Flight data analysis of the HyShot 2 scramjet flight experiment[J].AIAA Journal,2006,44(10):2366-2375.
[5] VINOGRADOV V A,KOBIGSKY S A,PETROV M D.Experimental investigation of kerosene fuel combustion in supersonic flow[J].Journal of Propulsion and Power,1995,11(1):130-134.
[6] YU G,LI J G,ZHANG X Y,et al.Experimental investigation on flameholding mechanism and combustion performance in hydrogen-fueled supersonic combustors[J].Combustion Science and Technology,2002,174(3):1-27.
[7] MITANI T,HIRAIWA T,TARUKAWA Y,et al.Drag and total pressure distributions in scramjet engines at Mach 8 flight[J].Journal of Propulsion and Power,2002,18(4):953-960.
[8] IGARASHI Y,NAKAHASHI K,KODERA M,et al.Comparative studies on scramjet engine drag by experiments and numerical analysis[C]//8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virginia:AIAA,1998.
[9] 贺伟,于时恩,李宏斌.高超声速一体化飞行器推阻特性测量研究[J].实验流体力学,2010,24(2):65-68.
[10] 闫熙.液体冲压发动机直连试车台方案设计及参数分析[D].长沙:国防科学技术大学,2013.
[11] 黄乐萍,豆飞龙,刘昊,等.RBCC燃烧室冲压模态数值模拟及试验验证[J].火箭推进,2022,48(6):69-73.
HUANG L P,DOU F L,LIU H,et al.Numerical simulation and experimental verification of RBCC combustor in ramjet mode[J].Journal of Rocket Propulsion,2022,48(6):69-73.
[12] 包恒.低飞行马赫数下煤油超燃冲压发动机的直接点火[D].长沙:国防科技大学,2017.
[13] 吴先宇,陈晖,刘睿,等.碳氢燃料超燃冲压发动机燃烧室控制试验[J].航空动力学报,2008,23(8):1541-1545.
[14] 潘余,李大鹏,刘卫东,等.超燃冲压发动机燃烧模态转换试验研究[J].爆炸与冲击,2008,28(4):293-297.
[15] ARAD E,YOKEV N,BROD H E,et al.From supersonic combustion to thermal choking:Numerical and experimental analysis of a scramjet engine[C]//AIAA Aviation 2020 Forum.Reston,Virginia:AIAA,2020.
[16] 王元光,徐旭,蔡国飙.自由射流超燃冲压发动机燃烧室流场对比计算研究[J].宇航学报,2006,27(5):825-829.
[17] 张冬青,邓维鑫,邢建文,等.10 Ma条件超燃冲压发动机自由射流试验过程[J].航空动力学报,2023,38(3):735-742.
[18] 卢洪波,陈星,谌君谋,等.新建高焓激波风洞Ma=8飞行模拟条件的实现与超燃实验[J].气体物理,2019,4(5):13-24.
[19] 吴颖川,贺元元,张小庆,等.超燃冲压发动机推力性能评估方法[J].推进技术,2019,40(1):26-32.
[20] 吕重阳,宋文艳,刘彬.试验气体污染对超燃冲压发动机进气道起动性能影响研究[C]//中国航天第三专业信息网第三十九届技术交流会暨第三届空天动力联合会议论文集——S03吸气式与组合推进技术.洛阳:中国航天第三专业信息网,2018.
[21] GU H B,CHEN L H,CHANG X Y.Experimental investigation on the cavity-based scramjet model[J].Chinese Science Bulletin,2009,54(16):2794-2799.

相似文献/References:

[1]朱舒扬.全尺寸超燃冲压发动机推力测量台架研制[J].火箭推进,2015,41(05):106.
　ZHU Shuyang.Development of thrust measurement platform for full-scale scramjet[J].Journal of Rocket Propulsion,2015,41(06):106.
[2]姚照辉,李光熙,张蒙正,等.燃油分配对超燃冲压发动机的性能影响仿真分析[J].火箭推进,2013,39(04):30.
　YAO Zhao-hui,LI Guang-xi,ZHANG Meng-zheng,et al.Simulation and analysis for influence of fuel distribution on scramjet performance[J].Journal of Rocket Propulsion,2013,39(06):30.
[3]刘 昊,李光熙,杜 泉,等.超燃冲压发动机全流道反应流场仿真分析[J].火箭推进,2013,39(06):1.
　LIU Hao,LI Guang-xi,DU Quan,et al.Numerical simulation of reaction flow field in full flowpath of scramjet[J].Journal of Rocket Propulsion,2013,39(06):1.
[4]张 倩,王 兵,张耘隆,等.RBCC的可实现性方案—DRBCC分析[J].火箭推进,2014,40(05):1.
　ZHANG Qian,WANG Bing,ZHANG Yun-long,et al.An analysis of RBCC realizability scheme: DRBCC[J].Journal of Rocket Propulsion,2014,40(06):1.
[5]赵宏亮,张蒙正.超燃冲压发动机推阻力特性研究综述[J].火箭推进,2014,40(06):41.
　ZHAO Hong-liang,ZHANG Meng-zheng.Investigation of thrust/drag property of scramjet[J].Journal of Rocket Propulsion,2014,40(06):41.
[6]张蒙正,邹 宇.美国典型高超飞行器项目研发及启示[J].火箭推进,2012,38(02):1.
　ZHANG Meng-zheng,ZOU Yu.Development of American typical hypersonic flight vehicles and its enlightenment[J].Journal of Rocket Propulsion,2012,38(06):1.
[7]李龙飞,王延涛,杨伟东,等.超声速燃烧地面试验的蓄热式加热器及其关键技术[J].火箭推进,2012,38(02):16.
　LI Long-fei,WANG Yan-tao,YANG Wei-dong,et al.Thermal energy storage heater and its key technologies for supersonic combustion ground test facilities[J].Journal of Rocket Propulsion,2012,38(06):16.
[8]文 科,李旭昌,马岑睿,等.不同入口马赫数对超燃冲压发动机尾喷管的性能影响研究[J].火箭推进,2011,37(03):18.
　WEN Ke,LI Xu-chang,MA Cen-rui,et al.Influence of nozzle inlet Mach number on performance of scramjet nozzle[J].Journal of Rocket Propulsion,2011,37(06):18.
[9]冯锦虎,高峰,何至林.超燃冲压发动机隔离段内附面层/激波串相互干扰研究[J].火箭推进,2010,36(02):5.
　Feng Jinhu,Gao Feng,He Zhilin.Investigation of boundary layer/shock wave train interference in a scramjet isolator[J].Journal of Rocket Propulsion,2010,36(06):5.
[10]王玉峰,吴宝元,王东东.变比热对超燃冲压发动机尾喷管设计的影响分析[J].火箭推进,2010,36(02):43.
　Wang Yufeng,Wu BaoYuan,Wang Dongdong.Scramjet engine nozzle design with variable specific heat[J].Journal of Rocket Propulsion,2010,36(06):43.

备注/Memo

收稿日期:2023-06-01; 修回日期:2023-07-30
基金项目:国家自然科学基金(u1967203)
作者简介:陈 磊(1993—),男,硕士,研究领域为冲压发动机。
通信作者:李光熙(1976—),男,博士,研究员,研究领域为冲压及组合发动机。

更新日期/Last Update: 1900-01-01