航天推进技术研究院主办
[1]范博,沈赤兵,王科.空气加热器喷雾燃烧流场仿真模拟[J].火箭推进,2023,49(05):13-22.
FAN Bo,SHEN Chibing,WANG Ke.Simulation on spray combustion flow field of the air heater[J].Journal of Rocket Propulsion,2023,49(05):13-22.
点击复制
FAN Bo,SHEN Chibing,WANG Ke.Simulation on spray combustion flow field of the air heater[J].Journal of Rocket Propulsion,2023,49(05):13-22.
空气加热器喷雾燃烧流场仿真模拟
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年05期
页码:
13-22
栏目:
目次
出版日期:
2023-10-25
- Title:
- Simulation on spray combustion flow field of the air heater
- 文章编号:
- 1672-9374(2023)05-0013-10
- Keywords:
- air combustor; spary combustion; flame stability; injection pressure drop; DPM
- 分类号:
- V411.7
- 文献标志码:
- A
- 摘要:
- 为研究喷注压降对空气加热器喷雾燃烧流场的影响规律,采用DPM离散相模型,结合考虑湍流燃烧效应的涡耗散模型对酒精/液氧/空气三组元加热器进行仿真计算,并与理论计算及试验结果进行对比,验证模型的准确性。仿真结果表明:在保持三组元流量恒定的条件下,提高空气喷注压降能够缩短酒精喷雾的雾化距离与火焰长度,当空气喷注压降提高后,能使喷雾距离缩短50%,火焰长度缩短40%,燃烧室内温度分布更加均匀,有利于提供满足试验需求的均匀热气流; 同时,降低酒精喷注压降能够减小酒精喷雾的穿透距离,使火焰更加集中于燃烧室轴线处; 当空气喷注压降超出工作范围时,火焰无法附着在喷嘴出口,容易造成加热器熄火; 过高的酒精喷注压降会使燃烧火焰周期性摆动,不利于燃烧室热防护。
- Abstract:
- In order to study the influence of injection pressure drop on the spray combustion flow field and combustion stability of the air heater. Discrete phase model(DPM)and eddy dissipation model considering the turbulent combustion effect were used to simulate the C2H5OH/LOx/Air tripropellant air heater, the simulation results were in good agreement with theoretical calculation and experiment, thereby the accuracy of the numerical models was verified. As the results shown, under the condition of maintaining a constant mass flow of the three-component propellant, increasing the air injection pressure drop could shorten the alcohol spray atomization distance and flame length, when the air injection pressure drop is increased to the critical pressure, the spray distance is shortened by 50% and the flame length is shortened by 40%. And the temperature distribution in the combustion chamber was more uniform, which could provide a uniform hot air flow to meet the test needs; reducing the alcohol injection pressure drop could reduce the alcohol spray penetration distance, and the flame was more concentrated on the axis of the combustion chamber. In addition, when the air injection pressure drop exceeded the working range, the flame would not be anchored to the injector outlet, which could cause the heater to shut down. Excessively high alcohol injection pressure drop would cause the combustion flame to oscillate periodically, which was not conducive to the thermal protection of the combustion chamber.
参考文献/References:
[1] LU F K,MARREN D E.Advanced hypersonic test facilities[M].Reston,Virigina:American Institute of Aeronautics and Astronautics,2002.
[2] SAARI D,CHU P,JAUCH C.Clean air regenerative storage heater technology for propulsion test facilities[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina:AIAA,2009.
[3] SMITH C,GARRARD D,JACKSON F.The future and way forward for the aerodynamic and propulsion test unit[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina:AIAA,2006.
[4] HODGE J,HARVIN S.Test capabilities and recent experiences in the NASA Langley 8-foot high temperature tunnel[C]//21st Aerodynamic Measurement Technology and Ground Testing Conference.Reston,Virigina:AIAA,2000.
[5] GARRARD D,SEELY J,ABEL L.An analysis of alternatives to provide a varying Mach number test capability at APTU[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina:AIAA,2006.
[6] ALEKSANDROV V Y,AREF'EV K Y,IL'CHENKO M A.Numerical and experimental study of oscillatory processes in small-size combustion heaters of air[J].Combustion,Explosion,and Shock Waves,2016,52(4):439-445.
[7] 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.
[8] HASHIMOTO T.Combustion stability of a vitiated-air heater using coaxial injectors[J].Energy Conversion and Management,1997,38(10/11/12/13):1083-1092.
[9] 王壮,胡锦华,杨建文,等.气-气同轴直流式喷注器结构参数对燃烧性能的影响[J].火箭推进,2022,48(3):32-39.
WANG Z,HU J H,YANG J W,et al.Effect of structural parameters of gas-gas coaxial direct-flow injector on combustion performance[J].Journal of Rocket Propulsion,2022,48(3):32-39.
[10] 杨样,晏至辉,蒲旭阳,等.新型液氧/空气/异丁烷燃烧加热器研制及流场校测[J].推进技术,2017,38(12):2830-2835.
[11] 熊剑,肖虹,李小平,等.宽范围变流量空气/液氧/酒精燃烧加热器试验[J].火箭推进,2020,46(3):56-61.
XIONG J,XIAO H,LI X P,et al.Experimental study on air/LOx/alcohol combustion heater with variable flow rate in large range[J].Journal of Rocket Propulsion,2020,46(3):56-61.
[12] 姜一通,田宁,肖虹,等.高温风洞气氧/煤油燃烧加热装置设计与试验[J].推进技术,2020,41(6):1210-1216.
[13] 林榕,魏建国,韩先伟.液氧酒精加热器等离子体点火试验及理论计算[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.
[14] 田亮,陈超群,徐旭,等.多喷嘴氢氧燃烧二元加热器设计与仿真[J].航空动力学报,2013,28(7):1475-1481.
[15] 李轩,徐旭.多喷嘴构型的轴对称氢氧加热器设计与仿真[J].航空动力学报,2016,31(6):1511-1520.
[16] 庄逢辰.液体火箭发动机喷雾燃烧的理论、模型及应用[M].长沙:国防科技大学出版社,1995.
[17] 聂万胜,丰松江.液体火箭发动机燃烧动力学模型与数值计算[M].北京:国防工业出版社,2011.
[18] 王振国.液体火箭发动机燃烧过程建模与数值仿真[M].北京:国防工业出版社,2012.
[19] 袁磊.空气加热器高频燃烧不稳定维持机理研究[D].长沙:国防科技大学,2018.
备注/Memo
收稿日期:2022-08-30; 修回日期:2022-09-15
基金项目:国家自然科学基金(12072367); 湖南省自然科学基金(2020JJ4666)
作者简介:范博(1998—),男,硕士,研究领域为液体火箭发动机燃烧稳定性。
通信作者:沈赤兵(1968—),男,研究员,研究领域为液体火箭发动机燃烧稳定性。
更新日期/Last Update:
1900-01-01