TBCC进气道变几何泄流腔研究
Study of variable geometry bleed cavity of TBCC inlet
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摘要: 提出了一种用于内并联型涡轮基组合循环(TBCC)进气道全马赫数范围的可变几何泄流腔方案,给出了可变几何泄流腔的设计方法;研究了泄流腔及其几何特征参数对进气道流场特征和气动性能的影响,获得了几何特征参数对进气道气动性能的影响规律.最后,采用三维流场数值模拟手段,对泄流腔可变型面参数随飞行马赫数Ma0的调节规律和进气道在全马赫数范围内的气动特性进行了研究,结果表明:泄流腔开启之后,随着Ma0的增加,泄流腔进口宽度和喉道高度不断减小,且均呈前急后缓的减小趋势;在Ma0≤2.0和Ma0≥2.5时,泄流腔进口前角均随Ma0的增加而减小;当Ma0≤2.5时,进气道的总压恢复系数均在0.8以上,当2.5<Ma0≤4.5时,进气道的总压恢复系数均在0.3以上,符合进气道总体方案的要求;冲压模态下,冲压通道的出口马赫数均小于0.4,出口静压均大于0.5个标准大气压(50.6625kPa),均能满足冲压燃烧室的燃烧需求.结合高速风洞试验研究结果,印证了可变几何泄流腔方案的可行性.Abstract: Scheme of variable geometry bleed cavity which was used in over/under type of turbine-based combined cycle(TBCC) inlet in full Mach number range and its design method were presented.The characteristic of inlet flow field and the inlet aerodynamic performance affected by bleed cavity and the configuration of cavity geometry parameters were investigated, based on which the law of inlet aerodynamic performance affected by cavity geometry parameters was abtained.Three-dimensional numerical simulation of over/under type TBCC inlet with bleed cavity was performed. The paper presents the influence of free stream Mach number on variable geometry design parameters, and aerodynamic characteristics of the inlet in full Mach range. Once the bleed cavity is opened, the width of the cavity entrance and the height of the throat keep decreasing. The decreasing rate is very high at the beginning, but becomes relatively low later. When the free stream Mach number is lower than 2.0, or higher than 2.5, the leading angle at the entrance of the bleed cavity is decreasing as the increase of Mach number. When the free stream Mach number is less than 2.5, the total pressure recovery of the inlet is beyond 0.8.When the free stream Mach number is from 2.5 to 4.5, the total pressure recovery of the inlet is beyond 0.3. The aerodynamic characteristics of the inlet meet the demands of the scheme. At ramjet mode, the exit Mach number of the ramjet diffuser is all below 0.4 and the exit pressure of the ramjet diffuser is all beyond 0.5 standard atmosphere pressure(50.6625kPa). The ramjet diffuser can fulfill the combustion condition of the ramjet combustion chamber.The feasibility of the variable geometry bleed cavity scheme was confirmed by the numerical and wind tunnel test results.
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Key words:
- combined engine /
- over/under type /
- inlet /
- variable geometry bleed cavity /
- numerical simulation
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[1] Watanabe Y,Miyagi H,Sekido T,et al.Conceptual design study on combined-cycle engine for hypersonic transport[R].ISABE 1993-7018,1993. [2] Pegg R J,Hunt J L,Petley D H.Design of a hypersonic waverider-derived airplane[R].AIAA 1993-0401,1993. [3] Kousuke I,Junsuke O,Takeshi M.A feasibility study of an ATREX engine at approved technology levels[R].AIAA-2001-1836,2001. [4] Utaka Y,Taneda H,Murakami A,et al.The aerodynamic design and wind tunnel tests of a combined intake for a supersonic transport[R].ISABE 1997-7139,1997. [5] Spoth K A,Moses P L.Structural design and analysis of a Mach zero to five turbo-ramjet system[R].AIAA-1993-1983,1993. [6] Takayuki K,Nobuhiro T,Tetsuya S,et al.Development study on axisymmetric air inlet for ATREX engine[R].AIAA-2001-1895,2001. [7] 张晓嘉,梁德旺,黄国平.二元高超声速进气道内压缩通道/隔离段曲面构型[J].推进技术,2008,29(1):49-53.ZHANG Xiaojia,LIANG Dewang,HUANG Guoping.Curved surface structure of internal contraction tunnel/isolator of two-dimensional hypersonic inlet[J].Journal of Propulsion Technology,2008,29(1):49-53.(in Chinese) [8] Espinosa A M.Intergration of turbine engines in hypersonic airbreathing vehicles[R].AIAA-2003-4408,2003. [9] 张华军,郭荣伟,李博.TBCC进气道研究现状及其关键技术[J].空气动力学学报,2010,28(5):613-620.ZHANG Huajun,GUO Rongwei,LI Bo.Research status of TBCC inlet and its key technologies[J].Acta Aerodynamica Sinica,2010,28(5):613-620.(in Chinese) [10] 诸惠民.涡轮冲压(串联布局)组合发动机基准概念方案研究[J].航空发动机,1997,23(2):1-12.ZHU Huimin.Proposal study of datum concept for turbo-ramjet(tandem configurations) combined engine[J].Aeroengine,1997,23(2):1-12.(in Chinese) [11] 朱大明,陈敏,唐海龙.高超声速涡轮/冲压组合发动机方案[J].北京航空航天大学学报,2006,32(3):263-266.ZHU Daming,CHEN Min,TANG Hailong.“Over-under” concept hypersonic turbo-ramjet combined propulsion system[J].Journal of Beijing University of Aeronautics and Astronautics,2006,32(3):263-266.(in Chinese) [12] 张华军,郭荣伟,谢旅荣.内并联型TBCC进气道方案设计及验证[J].航空动力学报,2012,27(11):2475-2483.ZHANG Huajun,GUO Rongwei,XIE Lürong.Design and validation of scheme for an over/under TBCC inlet[J].Journal of Aerospace Power,2012,27(11):2475-2483.(in Chinese)
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