Components level mathematical model of two-stage turbocharging reciprocating engine propeller propulsion system and analysis of its flying characteristic
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摘要: 对适用于高度为10~20km的中速、低速多用途飞行器的双级涡轮增压活塞发动机螺旋桨推进系统的特性计算方法进行了研究.引用涡轮发动机的部件法,建立基于各部件特性的代数数学模型,推进系统各部件工作点则由Newton法求解系统联合工作方程组得到.给出了方程组中的活塞发动机功率保持工作条件及增压器与活塞发动机联合工作条件,分析了推进系统功率保持工况和减功率工况的调节规律,及其对涡轮增压器工作线的影响.分析了推进系统总体及各部件的高度-速度特性.研究表明:该特性计算方法收敛快,一个工况点一般迭代5~6次即可;两个燃气旁通阀的调节规律不但可以满足推进系统的设计目标,同时还可对增压器工作点进行有效的优化调节;该特性计算方法可直接推广到更复杂的多级涡轮增压系统中.Abstract: A flying characteristic simulation method was studied for two-stage turbocharging reciprocating engine propeller propulsion system suitable for medium/high altitude low-speed long-endurance multi-role aerial vehicle systems at 10-20 kilometers height. With introduction of the simulation method for gas turbine engine with component models, and based upon component maps or algebraic equations, this method solved joint-working equations of the propulsion system by Newton iteration method to obtain co-operation points of the system. A full-power holding requirement and turbocharger-engine collaboration condition were stated. The regulating rules in both full-power holding mode and power lapse mode were analyzed. The influences of regulating rules on turbocharger operating lines were discussed. Finally, the altitude-velocity characteristics of the propulsion system and components were investigated. The research shows three results. This method enables rapid convergence and usually needs only 5-6 iterations to obtain one operating point. The regulation scheme of two gas-bypass valves can not only meet the design objectives, but also allow effective adjustment to the operating points of the turbochargers. This method can be extended conveniently to the simulations of more complex multi-stage turbocharging systems.
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[1] Bents D J,Mockler T,Maldonado J.Propulsion selection for 85 kft remotely piloted atmospheric science aircraft[R].NASA TM-107302,1996. [2] Wilkinson R E,Benway R B.Liquid cooled turbocharged propulsion system for hale application[R].ASME Paper 91-GT-399,1991. [3] Harp J.Turbocharger system developmental and propulsion system testing[R].TMS Report No.SR-36,1994. [4] Rodgers C.Turbocharging a high altitude UAV C I engine[R].AIAA 2001-3970,2001. [5] Korakianitis T,Sadoi T.Turbocharger design effects on gasoline engine performance[J].ASME Journal of Engineering for Gas Turbines and Power,2005,127(3):525-530. [6] Loth J L,Morris G J,Metlapalli P B.Staged turbocharging for high altitude IC engines[R].AIAA 1997-3970,1997. [7] Metlapalli P K.Three-staged turbocharger modeling with passive control system[D].Morgantown:West Virginia University,1996. [8] Lee B.Dual-stage boosting systems:modeling of configurations,marching and boost control options[D].Ann Arbor:University of Michigan,2009. [9] 单鹏,朱德轩,陈小龙,等.航空双级涡轮增压器系统的基本模型[J].工程热物理学报,2009,30(7):1119-1124. SHAN Peng,ZHU Dexuan,CHEN Xiaolong,et al.Essential model for cycle design and altitude performance analysis of the two-stage turbocharging system of gasoline aeroengines[J].Journal of Engineering Thermophysics,2009,30(7):1119-1124.(in Chinese) [10] 陈妍,王洪铭.一种带涡轮增压器的活塞发动机调节及其特性[J].北京航空航天大学学报,1998,24(1):16-19. CHEN Yan,WANG Hongming.Control and performance of a turbosupercharged piston engine[J].Journal of Beijing University of Aeronautics and Astronautics,1998,24(1):16-19.(in Chinese) [11] 王艳华,李云清,陈小龙,等.轻型航空发动机二级涡轮增压匹配模拟[J].航空动力学报,2011,26(5):1099-1103. WANG Yanhua,LI Yunqing,CHEN Xiaolong,et al.Two-stage turbocharging matching of light aero-engine at high altitude[J].Journal of Aerospace Power,2011,26(5):1099-1103.(in Chinese) [12] 胡延领,徐斌,杨世春.基于螺旋桨特性的活塞发动机涡轮废气阀的调节[J].航空动力学报,2011,26(8):1814-1818. HU Yanling,XU Bin,YANG Shichun.Regulating turbine exhaust valve about piston engine based on analyzing propeller[J].Journal of Aerospace Power,2011,26(8):1814-1818.(in Chinese) [13] 徐斌,夏绍军,杨世春,等.航空活塞发动机两级增压匹配方法[J].航空动力学报,2012,27(3):496-500. XU Bin,XIA Shaojun,YANG Shichun,et al.Matching of two-stage supercharging aircraft piston engines[J].Journal of Aerospace Power,2012,27(3):496-500.(in Chinese) [14] McKinney J S.Simulation of turbofan engine:Part Ⅰ description of method and balancing technique[R].Ohio:Air Force Aero Propulsion Laboratory,AD-825197,1967. [15] Koenig R W,Fishbach L H.GENENG:a program for calculating design and off-design performance for turbojet and turbofan engine[R].NASN TN D-6552,1972. [16] Fishbach L H,Koenig R W.GENENG Ⅱ:a program for calculating design and off-design performance of two-and three-spool turbofans with as many as three nozzles[R].NASA TN D-6553,1972. [17] James F S,Carl J D.DYNGEN:a Program for calculating steady-state and transient performance of turbojet and turbofan engines[R].NASA TN D-7901,1975. [18] Standards Policy and Strategy Committee.BS ISO 3046-1:2002,reciprocating internal combustion engines-performance:Part 1 declarations of power,fuel and lubricating oil consumptions,and test methods:additional requirements for engines for general use[S].London:Standards Policy and Strategy Committee,2002. [19] 蒋德明.内燃机的涡轮增压[M].北京:机械工业出版社,1986. [20] Ehrlich D A.Characterization of unsteady on-engine turbocharger turbine performance[D].West Lafayette:Purdue University,1998. [21] Hu X.An advanced turbocharger model for the internal combustion engine[D].West Lafayette:Purdue University,2000. [22] Chen H,Hakeem I,Martinez-Botas R F.Modelling of a turbocharger turbine under pulsating inlet conditions[J].IMechE,1996,201(5):397-408. [23] 潘锦珊,单鹏,刘火星,等.气体动力学基础[M].修订本.北京:国防工业出版社,2012.
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