RBCC发动机燃料喷注位置变化对混合燃烧模式燃烧的影响

潘科玮; 何国强; 刘佩进; 秦飞; 杨斌

RBCC发动机燃料喷注位置变化对混合燃烧模式燃烧的影响

西北工业大学航天学院燃烧、热结构与内流场重点实验室,西安 710072

计量
- 文章访问数: 1600
- HTML浏览量: 2
- PDF量: 27
- 被引次数: 0
出版历程
- 收稿日期: 2010-07-07
- 修回日期: 2010-10-11
- 刊出日期: 2011-08-28

Numerical investigation of combustion about injection positions in rocket induced secondary combustion of RBCC engine

Science and Technology on Combustion,Internal Flow and Thermal-structure Laboratory, School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China

摘要

摘要: 为了研究混合燃烧模式下燃料喷注位置对燃烧的影响,通过数值模拟的方法,研究了喷注位置变化时,流道组分质量分数分布、高温放热区域及流道压强分布的变化规律.结果表明,混合燃烧模式中,喷注位置变化对燃烧流场影响很大.在燃烧室中,燃料喷注位置靠前能给燃烧带来帮助,提高燃料与二次来流的掺混能力,并且由于燃料与一次火箭高温羽流相互掺混等影响提前,加快燃料的雾化蒸发,促进燃烧流场的火焰传播,减少煤油点火延迟时间,提高了燃烧效率.因此为了提高混合燃烧模式下的燃烧性能,应尽可能选择燃烧室前端位置进行燃料喷注.
- 火箭基组合动力循环(RBCC)发动机 /
- 喷注位置 /
- 燃烧 /
- 煤油 /
- 数值模拟
Abstract: In order to investigate the influence on combustion by changing the injection positions in the rocket induced secondary combustion,the numerical simulation was used to study the rule of the distribution of component in the flow,the area of high temperature heat release and the distribution of pressure in the flow.The results show that:the combustion flow is obviously affected by changing the injection positions.In the combustor,the combustion performance could be improved by putting the fuel injection position forwards,helping to strengthen the mixing capability of fuel.For the fuel mixed ahead the flame of primary rocket,it accelerates the fuel spray evaporation effect,improves the flame spread and increases the combustion efficiency.In order to improve the performance of combustion in the rocket induced secondary combustion,the fuel injection positions should be placed at front end in the combustor.
- rocket based combined cycle (RBCC) engine /
- injection position /
- combustion /
- kerosene /
- numerical simulation

HTML

参考文献(16)

[1]	Young D A,Kokan T S,Clark I G,et al.A SSTO hypersonic vehicle concept utilizing RBCC and HEDM propulsion technologies.AIAA Paper 2006-8099,2006.
[2]	Hank J M,Franke M E.TSTO reusable launch vehicles using airbreathing propulsion.AIAA Paper 2006-4962,2006.
[3]	Pastrone D,Sentinellay M R.Evolutionary algorithm based approach for RBCC engines optimization.AIAA Paper 2008-5170,2008.
[4]	ZHANG Man,HE Guoqiang,LIU Peijin.Performance improved by multistage rockets ejection in RBCC engine.AIAA Paper 2008-4504,2008.
[5]	Luetke N,Mohieldin T O,Tiwari S N.Numerical optimization study of a rocket based combined cycle.AIAA Paper 2007-5390,2007.
[6]	Tomioka S,Takegoshi M,Kudo K,et al.Performance of a rocket-ramjet combined-cycle engine model in ejector mode operation.AIAA Paper 2008-2618,2008.
[7]	Billig F S,Waltrup P J,Stockbridge R D.Integral-rocket dual-combustion ramjets:a new propulsion concept[J].Journal of Space Craft,1979,17(5):416-424.
[8]	Billig F S.Research on supersonic combustion[J].Journal of Propulsion and Power,1993,9(4):499-514.
[9]	Sullins G A.Demonstration of mode transition in a scramjet combustor[J].Journal of Propulsion and Power,1993,9(4):515-520.
[10]	Minato R,Niioka T.Effect of hydrogen jet position relative to plasma torch on supersonic combustion.AIAA Paper 2003-6908,2003.
[11]	Jeong E,O'Byrne S,Jeung I S,et al.Supersonic combustion of hydrogen fuel injection locations in a cavity-based combustor.AIAA Paper 2008-4576,2008.
[12]	Sadiki A,Maltsev A,Wegner B,et al.Unsteady methods (URANS and LES) for simulation of combustion systems[J].International Journal of Thermal Sciences,2006,45(8):760-773.
[13]	Boudier G,Gicquel L Y M,Poinsot T,et al.Comparison of LES,RANS and experiments in an aeronautical gas turbine combustion chamber[J].Proceedings of the Combustion Institute,2007,31(2):3075-3082.
[14]	Tucker P K,Menon S,Merkle C L,et al.Validation of high-fidelity CFD simulations for rocket injector design.AIAA Paper 2008-5226,2008.
[15]	Roux A,Reichstadt S,Bertier N.Comparison of numerical methods and combustion models for LES of a ramjet[J].Combustion for Aerospace Propulsion,2009,337(6):352-361.
[16]	Routovsky V.Autoignition study on kerosene combustion in supersonic flow.Moscow:Moscow State Aviation Institute Technical Report,Contract No.F61708-96-WO286,1997.