非均匀来流下TBCC变几何进气道的数值优化

黄辉先; 庄选; 李斌; 李燕

doi:10.13433/j.cnki.1003-8728.2014.1235

非均匀来流下TBCC变几何进气道的数值优化

doi: 10.13433/j.cnki.1003-8728.2014.1235

1.
湘潭大学信息工程学院, 湘潭 411105

基金项目:

国家部委预先研究基金项目(2011846)资助

详细信息

作者简介:
黄辉先(1957- ),教授,博士生导师,研究方向为航空发动机进气道的研究和先进控制理论及应用,huanghx@xtu.edu.cn。

计量
- 文章访问数: 156
- HTML全文浏览量: 36
- PDF下载量: 4
- 被引次数: 0
出版历程
- 收稿日期: 2013-03-21
- 刊出日期: 2014-12-05

Numerical Simulation and Optimization for Variable Geometry Inlet of TBCC Under Non-uniform Incoming Flow

1.
College of Information Engineering, Xiangtan University, Xiangtan 411105

摘要

摘要: 为提高内并联式涡轮基组合循环发动机进气道的工作特性,设计了一种带多级楔板的扩压段二维进气道.采用数值模拟方法研究了非均匀来流对其流场特性及性能参数的影响,并与非均匀来流对常规型进气道特性的影响进行了比较.模拟结果表明:采用带多级楔板的扩压段二维进气道性能受非均匀来流影响更小,扩压段内出口流场有明显的提升;模态转换状态下,与常规型进气道相比,进气道出口总压恢复系数平均增大10%,总压畸变指数平均降低15%左右,冲压出口马赫数均小于0.41,出口温升比降低.从而使得发动机推力增加,耗油率降低,改善了TBCC发动机的性能.
- 涡轮基组合循环发动机 /
- 变几何进气道 /
- 非均匀来流 /
- 数值模拟 /
- 性能参数
Abstract: A two-dimensional inlet with multi-wedge plate diffuser is designed to improve the operating characteristics of the inlet in " over/under" TBCC(Turbine Based Combined Cycle). The effects of non-uniform flow on the flow-field characteristic and the performance parameter are investigated and compared with that on the the conventional inlet. The simulation results indicate that the two-dimensional inlet with multi-wedge plate diffuser is slightly influenced by non-uniform flow and the outlet flow field in diffuser is improved significantly. At mode transition,compared with the conventional inlet,the total pressure recovery ratio is increased by 10%,and the total pressure distortion indicator(DPt) is decreased by about 15%,the outlet Mach number of the ramjet diffuser is less than 0. 41 and the outlet temperature ratio(ψ) is decreased. Those make the engine thrust increased and make the specific fuel consumption reduced.

HTML全文

参考文献(15)

[1]	Charles E C,Aaron H A,Sharon SW,et al.Technology roadmap for dual-mode scramjet propulsion to support space-aecess vision vehictae development[R] AIAA2002-5188
[2]	邓远I[P超然冲压发动机隔离段流动特性研究[D] 西安:西北工业大学,2005 Deng Y H.Investigation of flow charactaeristict、of scramjet isolator[D]Xi'an:Northwestern Polytechnical University,2005(in Chinese)
[3]	汪维娜涡轮冲压组合发动机部件设计方法及内流场数值研究[D]西安:西北工业大学,2006 Wang W N.Design methods of components and the flow field numerical research based on combined〔yctae engine [D] Xi'an:Northwestern Polytechnical University,2006(in Chinese)
[4]	李超并联式TBCC排气系统的气动设计、性能研究及初步优化[D]南京:南京航空航天大学,2008 Li C.The aerodynamic: design,performance research and preliminary optimization based on over/under TBCC exhaust system[D]Nanjing; Nanjing University of Aeronautic、and Astronautic、,2008(in Chinese)
[5]	严红明,钟兢军,杨凌,等组合发动机可调进气道气动性能[J]航空动力学报,2011,26(2);458-467 Yan H M,Zhong J J,Yang L,et al.Aerodynamic charactaeristic research on variable geometry inlet of combinedyctae engine [J].Journal of Aerospace Power, 2011,26(2);458-467(in Chinese)
[6]	张华军,梁德旺,郭荣伟-种组合发动机变几何进气道流场特性研究[J]航空动力学报, 2009,24(10); 2201-2207 Zhanh H J,Lianh DW,Guo R W Study of flow characteristic、for a variable geometry inlet on combined engine[J].Journal of Aerospace Power,2009,24 (10): 2201-2207(in Chinese)
[7]	刘增文,王占学,蔡元虎,等涡轮基组合循环发动机性能数值模拟[J]推进技术,2009,30(1);1-5 Liu ZW,Wang Z X,Cai Y H,et al.Numerical simulation of performance for turbine based combined cyctae propulsion system[J]Journal of Propulsion Technology,2009,30 (1):1-5(in Chinese)
[8]	李龙,李博,梁德旺,等涡轮基组合循环发动机并联式进气道的气动特性[J]推进技术,2008,29(6); 667-672 Li L,Li B,Lang DW,et al.Aerodynam ict characteristic、of over/under inlet for turbine based combined c:ycae engine[J]Journal of Propulsion Technology,2008,29 (6); 667-672(in Chinese)
[9]	Timothy Kokan,John R.Olds,Virgil Hutchinson,John Daniel Reeves.Aztec:a tsto hypersonic: vehicae c:onc:ept utilizing tbec and hedm propulsion technologies[R] AIAA 2004-3728
[10]	Marshall AW,Gupta A K,Lewis M J.Critical Issues in TBCC Modeling[R].AIAA 2004-3827
[11]	黄中杰,陈迎春,张彬乾,等多段翼型后缘襟翼缝道参数影响研究[J]机械科学与技术,2012,31(1);4-9 Huang Z J,Chen Y C,Zhang B Q,et al.Study on the elfecta of flap parameters to multi-element airfoils[J] Mechanical Seience and Technology for Aerospace Engineering,2012,31(1);4-9(in Chinese)
[12]	Fluent 6.0 User's Guide[Z]Fluent Inct,Lebanon, 2001
[13]	张林,张塑元,王磊,等非均匀来流对新型高超弯曲激波二维进气道的影响[J]推进技术,2012,33(3); 338-345 Zhang L,Zhang K Y,Nan X J,et al.Investigation on a new hypersonic: curved shock 2-dimensional inlet under non-uniform coming flow[J]Journal of Propulsion Technology,2012,33 (3):338-345(in Chinese)
[14]	张塑元,萧旭东,徐辉非均匀超声速二维进气道绕流研究[J]空气动力学报,2000,18(1);92-96 Zhang K Y,Xiao X D,Xu H.Investigation of two-dimensional inlet under non-uniform supersonic: flow[J Actaa Aerodynamica Sinica,2000,18(1):92-96(in Chinese)
[15]	廉筱纯,吴虎航空发动机原理[M]西安:西北工业大学出版社,2005 Lian X C,Wu H.Aero-engine principle[M]Xi'an: Northwestern Polytechnical University,2005(in Chinese)