Flight characteristic comparison of STS and DTSbased on mathematical model
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摘要: 研究了单级涡轮增压活塞螺旋桨推进系统(STS)的部件法数学模型,给出了STS的联合工作方程组,给出了STS的调节方式,计算了STS的高度速度特性.从总体及各部件的高度速度特性方面比较了STS和双级涡轮增压活塞螺旋桨推进系统(DTS).研究表明:选择的STS调节方式可满足其设计目标,相比于DTS实际功率保持高度为12.5km,STS的实际功率保持高度可达到5.5km;在选用相同的螺旋桨和发动机的前提下,STS和DTS中各部件特性的变化规律基本一致,但STS的推进效率、单位推力耗油率、推进系统总效率在高度速度特性图中的变化范围大大窄于DTS的.Abstract: A componentlevel characteristic simulation method for singlestage turbocharging reciprocating engine propeller propulsion system (STS) was studied. A regulating method of STS was proposed, the jointworking equations of STS were solved, and the altitudevelocity characteristic of STS were simulated. The flying characteristics of overall performance and each component were compared between a STS and a dualstage turbocharging reciprocating engine propeller propulsion system (DTS). Result shows that, the regulating method of STS can meet the design objectives, the full power holding altitude of STS can achieve 5.5km while that of the DTS is 12.5km. When selecting the same propeller and engine, the characteristics of each component between STS and DTS are similar, and the variation ranges of the altitude and velocity of the propulsion efficiency, specific fuel consumption, total efficiency of STS are narrower than those of the DTS.
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[1] Wilkinson R E,Benway R B.Liquid cooled turbocharged propulsion system for hale application[R].ASME Paper 91-GT-399,1991. [2] Bents D J,Mockler T,Maldonado J.Propulsion selection for 85 kft remotely piloted atmospheric science aircraft[R].NASA TM-107302,1996. [3] Harp J.Turbocharger system developmental and propulsion system testing[R].Thermo Mechanical Systems 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].Journal of Engineering for Gas Turbines and Power,2005,127:525-530. [6] Loth J L,Morris G J,Metlapalli P B.Staged turbocharging for high altitude IC engines[R].AIAA 97-3970,1997. [7] Metlapalli P K.Threestaged turbocharger modeling with passive control system[D].Morgantown:West Virginia University,1996. [8] Lee B.Dualstage 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 twostage turbocharging system of gasoline aeroengines[J].Journal of Engineering Thermophysics,2009,30(7):1119-1124.(in Chinese) [10] 周亦成,单鹏,朱德轩.双级涡轮增压活塞发动机螺旋桨推进系统部件法数学模型与飞行特性分析[J].航空动力学报,2014,29(11):2621-2632. ZHOU Yicheng,SHAN Peng,ZHU Dexuan.Component level mathematical model of twostage turbocharging reciprocating engine propeller propulsion system and analysis of its flying characteristic[J].Journal of Aerospace Power,2014,29(11):2621-2632.(in Chinese) [11] McKinney J S.Simulation of turbofan engine:Part Ⅰ description of method and balancing technique[R].Air Force Aero Propulsion Lab,AD-825197,1967. [12] Koenig R W,Fishbach L H.GENENG:Ⅰ a program for calculating design and offdesign performance for turbojet and turbofan engine[R].NASA TN D-6552,1972. [13] Fishbach L H.,Koenig R W.GENENG:Ⅱ a program for calculating design and offdesign performance of twoand threespool turbofans with as many as three nozzles[R].NASA TN D-6553,1972. [14] James F S,Carl J D.DYNGEN:a program for calculating steadystate and transient performance of turbojet and turbofan engines[R].NASA TN D-7901,1975. [15] 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) [16] 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):1009-1103. WANG Yanhua,LI Yunqing,CHEN Xiaolong,et al.Twostage turbocharging matching of light aeroengine at high altitude[J].Journal of Aerospace Power,2011,26(5):1009-1103.(in Chinese) [17] 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) [18] 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 twostage supercharging aircraft piston engines[J].Journal of Aerospace Power,2012,27(3):496-500.(in Chinese)
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