FLADE变循环发动机模态转换过程特性分析
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摘要
为对带FLADE(Fan on Blade)的变循环发动机总体性能进行评估,发展了FLADE部件计算方法以及带FLADE的双外涵变循环发动机稳态性能计算模型,加入反映转子惯性效应和部件容积效应的动力学方程,建立了变循环发动机过渡态性能计算模型。分析了FLADE变循环发动机在双外涵与单外涵模式之间的模态转换过渡态特性,重点研究了几何参数调节及其不同组合形式对FLADE变循环发动机模态转换过程的影响。结果表明,带FLADE的双外涵变循环发动机的模态转换过程只与FLADE导叶角度和FLADE喷管面积有关,且两者应同时放大或关小;FLADE的开/关对风扇外涵气流及核心机的影响较小。
The variable cycle engine(VCE)with FLADE(Fan on Blade)is one of the research hotspots for future military and civil aircraft power device,which shows outstanding performance advantages. For evaluating its performance,the method for FLADE component simulation and the steady-state performance simulation model for the double bypass VCE with FLADE are developed. The transient performance simulation model for VCE is also established,which considered the effects of the polar moment of inertia and the component volumes during the dynamic equation constructing. The transient performance at mode transition state of the FLADE VCE between double bypass mode and single bypass mode is discussed,and the influence of geometric parameters on the mode transition state of FLADE VCE is deeply analyzed. It can be concluded that the mode transition characteristic of the double bypass FLADE VCE is only related to the angle of inlet guide vane of FLADE and the area of the FLADE nozzle,and both should be enlarged or closed at the same time. The state of FLADE is on or off which has small impact on airflow of fan bypass and core engine.
The variable cycle engine(VCE)with FLADE(Fan on Blade)is one of the research hotspots for future military and civil aircraft power device,which shows outstanding performance advantages. For evaluating its performance,the method for FLADE component simulation and the steady-state performance simulation model for the double bypass VCE with FLADE are developed. The transient performance simulation model for VCE is also established,which considered the effects of the polar moment of inertia and the component volumes during the dynamic equation constructing. The transient performance at mode transition state of the FLADE VCE between double bypass mode and single bypass mode is discussed,and the influence of geometric parameters on the mode transition state of FLADE VCE is deeply analyzed. It can be concluded that the mode transition characteristic of the double bypass FLADE VCE is only related to the angle of inlet guide vane of FLADE and the area of the FLADE nozzle,and both should be enlarged or closed at the same time. The state of FLADE is on or off which has small impact on airflow of fan bypass and core engine.
引文
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[4]Sriram K Rallabhandi,Dimitri N Mavris.Simultaneous Airframe and Propulsion Cycle Optimization for Supersonic Aircraft Design[R].AIAA 2008-143.
[5]French M W,Allen G L.NASA VCE Test Bed Engine Aerodynamic Performance Characteristics and Test Results[R].AIAA 81-1594.
[6]Vdoviak J W,Knott P R,Ebacker J J.Aerodynamic/Acoustic Performance of YJ101/Double Bypass VCE with Coannular Plug Nozzle[R].NASA CR-159869,1981.
[7]Stephen M Rock,Ronald L De Hoff.Variable Cycle Engine Multivariable Control Synthesis Interim ReportControl Structure Definition[R].AFAPL-TR-79-2043.
[8]Przybylko S J,Rock S M.Evaluation of a Multivariable Control Design on a Variable Cycle Engine Simulation[R].AIAA 82-1077.
[9]唐海龙.面向对象的航空发动机性能仿真系统及其应用[D].北京:北京航空航天大学,2000.
[10]周红,王占学,张晓博,等.变循环发动机模态转换的几何调节规律[J].航空动力学报,2015,30(9):2160-2166.
[11]苟学中,周文祥,黄金泉.变循环发动机部件级建模技术[J].航空动力学报,2013,28(1):104-111.
[12]谢振伟,郭迎清,陆军.容积与转子状态量在变循环发动机数值仿真中的应用[J].推进技术,2015,36(7):1085-1092.(XIE Zhen-wei,GUO Ying-qing,LU Jun.Application of Volume and Rotor State Values in Variable Cycle Engine Numerical Simulation[J].Journal of Propulsion Technology,2015,36(7):1085-1092.)
[13]李斌,陈敏,朱之丽,等.自适应循环发动机不同工作模式稳态特性研究[J].推进技术,2013,34(8):1009-1015.(LI Bin,CHEN Min,ZHU Zhi-li,et al.Steady Performance Investigation on Various Modes of an Adaptive Cycle Aero-Engine[J].Journal of Propulsion Technology,2013,34(8):1009-1015.)
[14]Lyu Y,Tang H,Chen M.A Study on Combined Variable Geometries Regulation of Adaptive Cycle Engine during Throttling[J].Applied Sciences,2016,6(12).
[15]Zheng Jun-Chao,Chen Min,Tang Hai-Long.Matching Mechanism Analysis on an Adaptive Cycle Engine[J].Chinese Journal of Aeronautics,2017,(2).
[16]Aspi Rustom Wadia.FLADE Fan with Different Inner and Outer Airfoil Stagger Angles at a Shroud There between[P].US:7758303,2010-07-20.
[17]樊思齐.航空发动机控制(下册)[M].西安:西北工业大学出版社,2008:81-141.
[18]骆广琦,桑增产,王如根,等.航空燃气涡轮发动机数值仿真[M].北京:国防工业出版社,2006:82-91.
[19]James F Sellers,Carl J Daniele.DYNGEN-A Program for Calculating Steady-State and Transient Performance of Turbojet and Turbofan Engines[R].NASA TN-D-7901,1975.