采用射流掺混增强的前可调面积涵道引射器数值模拟
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摘要
为了提高风扇外涵和核心机驱动风扇级外涵流体的掺混效率,提出一种采用射流掺混增强的前可调面积引射器设计方案。通过数值模拟的手段对流量特性、流动掺混和总压损失等方面进行了研究,并同基准模型进行了对比分析,结果表明:采用波瓣混合器结构的前可调面积引射器设计,显著地增加了较高出口背压工况下风扇外涵的流通能力;新的设计方案不仅没有增加低出口背压工况下的总压损失,还减小了高背压出口工况下的流动损失;流向涡的特征尺度是提高掺混效率的关键,可以进一步优化波瓣混合器几何轮廓,以满足调节机构对结构设计的要求。
In order to improve the mixing performance of fan bypass and CDFS(core driven fan stage) bypass,a innovative configuration of FVABI(front variable area bypass injector) with jet mixing enhancement was proposed.Numerical simulation was performed to investigate mass flow rate characteristic,flow mixing and total pressure loss of FVABI configuration with lobed mixer.Compared with the baseline configuration,the predictions are discussed and several conclusions can be summarized.Firstly,the significant improvement in fan bypass mass flow rate is achieved by jet mixing enhanced configuration at high back pressure operating point.Secondly,the performance is not degraded at low back pressure operating situation,but the total pressure loss is decreased at high back pressure operating point.Finally,the characteristic length of stream-wise vortex is the key to improve mixing performance,and the optimization of lobed mixer is available to match further structural requirement of adjust configuration.
In order to improve the mixing performance of fan bypass and CDFS(core driven fan stage) bypass,a innovative configuration of FVABI(front variable area bypass injector) with jet mixing enhancement was proposed.Numerical simulation was performed to investigate mass flow rate characteristic,flow mixing and total pressure loss of FVABI configuration with lobed mixer.Compared with the baseline configuration,the predictions are discussed and several conclusions can be summarized.Firstly,the significant improvement in fan bypass mass flow rate is achieved by jet mixing enhanced configuration at high back pressure operating point.Secondly,the performance is not degraded at low back pressure operating situation,but the total pressure loss is decreased at high back pressure operating point.Finally,the characteristic length of stream-wise vortex is the key to improve mixing performance,and the optimization of lobed mixer is available to match further structural requirement of adjust configuration.
引文
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[7]周红,王占学,刘增文,等.可变面积涵道引射器对变循环发动机性能影响[J].航空动力学报,2016,31(12):2842-2850.ZHOU Hong,WANG Zhanxue,LIU Zengwen,et al.Impact of variable area bypass injector on variable cycle engine performance[J].Journal of Aerospace Power,2016,31(12):2842-2850.(in Chinese)
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[9]冷中明,周建华.非轴对称前涵道引射器性能的数值研究[J].推进技术,2015,36(10):1465-1473.LENG Zhongming,ZHOU Jianhua.Numerical investigation for performance of non-axisymmetric front variable area bypass injector[J].Journal of Propulsion Technology,2015,36(10):1465-1473.(in Chinese)
[10]张晓曼,周建华.前可变面积涵道引射器过渡态特性研究[C]//第十二届长三角能源论坛,2015.ZHANG Xiaoman,ZHOU Jianhua.Transient analysis of the front variable area bypass injector[C]//Proceedings of Yangtze River Delta Energy Forum,2015.(in Chinese)
[11]周红.变循环发动机特性分析及其与飞机一体化设计研究[D].西安:西北工业大学,2016.ZHOU Hong.Investigation on the variable cycle engine characteristics and integration design with aircraft[D].Xi'an:Northwestern Polytechnical University,2016.(in Chinese)
[12]Wagenknecht C D,Faust G K.Individual bypass injector valves for a double bypass variable cycle turbofan engine:USA,US4175384[P].1979-11-27.
[13]雷志军.进口预旋条件下涡扇发动机波瓣射流掺混机理的实验研究[D].北京:中国科学院工程热物理研究所,2011.LEI Zhijun.Experimental study on the mixing mechanism of lobed mixer with inlet swirl in model turbofan engines[D].Beijing:Institute of Engineering Thermophysics,Chinese Academy of Sciences,2011.(in Chinese)
[2]Howlett R,Streicher F.Advanced supersonic propulsion system technology study,Phase IV final report:NASA CR-135273[R].Washington,USA:NASA,1978.
[3]Hines R W.Variable stream control engine for supersonic propulsion[J].Journal of Aircraft,1978,15(6):321-325.
[4]French M,Allen G.NASA VCE test bed engine aerodynamic performance characteristics and test results[C]//Proceedings of 17th Joint Propulsion Conference,1981.
[5]Morgenfeld T A.YF-22A prototype advanced tactical fighter demonstration/validation flight test program overview[C]//Proceedings of Aerospace Design Conference,1981.
[6]晏武英.美国自适应发动机研制进展[J].国际航空,2015(3):53-56.YAN Wuying.U.S.adaptive engine in progress[J].International Aviation,2015(3):53-56.(in Chinese)
[7]周红,王占学,刘增文,等.可变面积涵道引射器对变循环发动机性能影响[J].航空动力学报,2016,31(12):2842-2850.ZHOU Hong,WANG Zhanxue,LIU Zengwen,et al.Impact of variable area bypass injector on variable cycle engine performance[J].Journal of Aerospace Power,2016,31(12):2842-2850.(in Chinese)
[8]刘宝杰,贾少锋,于贤君.变循环发动机前可调面积涵道引射器的通流计算方法[J].推进技术,2017,38(8):1689-1698.LIU Baojie,JIA Shaofeng,YU Xianjun.Throughflow calculation method of variable cycle engine forward variable area bypass injector[J].Journal of Propulsion Technology,2017,38(8):1689-1698.(in Chinese)
[9]冷中明,周建华.非轴对称前涵道引射器性能的数值研究[J].推进技术,2015,36(10):1465-1473.LENG Zhongming,ZHOU Jianhua.Numerical investigation for performance of non-axisymmetric front variable area bypass injector[J].Journal of Propulsion Technology,2015,36(10):1465-1473.(in Chinese)
[10]张晓曼,周建华.前可变面积涵道引射器过渡态特性研究[C]//第十二届长三角能源论坛,2015.ZHANG Xiaoman,ZHOU Jianhua.Transient analysis of the front variable area bypass injector[C]//Proceedings of Yangtze River Delta Energy Forum,2015.(in Chinese)
[11]周红.变循环发动机特性分析及其与飞机一体化设计研究[D].西安:西北工业大学,2016.ZHOU Hong.Investigation on the variable cycle engine characteristics and integration design with aircraft[D].Xi'an:Northwestern Polytechnical University,2016.(in Chinese)
[12]Wagenknecht C D,Faust G K.Individual bypass injector valves for a double bypass variable cycle turbofan engine:USA,US4175384[P].1979-11-27.
[13]雷志军.进口预旋条件下涡扇发动机波瓣射流掺混机理的实验研究[D].北京:中国科学院工程热物理研究所,2011.LEI Zhijun.Experimental study on the mixing mechanism of lobed mixer with inlet swirl in model turbofan engines[D].Beijing:Institute of Engineering Thermophysics,Chinese Academy of Sciences,2011.(in Chinese)