短距起飞/垂直降落发动机建模技术研究
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摘要
参考常规双轴涡扇发动机数学模型,建立了适用于短距起飞/垂直降落(STOVL)飞机的变循环发动机部件级数学模型;通过特性外推,建立了轴驱动升力风扇数学模型;采用神经网络映射涵道总压损失的方法,建立了滚转喷管和外涵模型.根据STOVL发动机结构和部件变化特点,建立了稳态和动态共同工作方程.参照国外文献仿真数据进行设计点计算,并按照Bevilaqua提出方法开展了由常规涡轮风扇模式到悬停涡轮轴模式的过渡态仿真.仿真结果表明:建立的数学模型在悬停状态设计点和高空巡航点与国外文献数据相比误差均小于1.5%,推力达到悬停状态要求,符合STOVL发动机的设计特点,验证了该建模方法的有效性.
The component-level model of variable cycle engine for short take off and vertical landing(STOVL)was built based on modeling method of two-spool-turbofan engine.On the basis of characteristics extrapolation method,the shaft-driven lift fan mathematical model was built.Models of the bypass duct were built using neural network for mapping the bypass total pressure loss.According to the structure and specialty of short takeoff and vertical landing,the static and dynamic co-working equations were set up.With reference to foreign researches simulation data,the design point was calculated. According to Bevilaquas method,transient simulation of switching between conventional turbofan and hover turboshaft cycle was carried out.The results of numerical simulation indicate that the error of the mathematical model and foreign research data is less than 1.5%,and the thrust meets hover state requirements.Both models can offer high levels of thrust by increasing the fuel flow a little.The performance variation in simulation is consistent with the specialty of STOVL,so the modeling method of STOVL proposed is feasible.
The component-level model of variable cycle engine for short take off and vertical landing(STOVL)was built based on modeling method of two-spool-turbofan engine.On the basis of characteristics extrapolation method,the shaft-driven lift fan mathematical model was built.Models of the bypass duct were built using neural network for mapping the bypass total pressure loss.According to the structure and specialty of short takeoff and vertical landing,the static and dynamic co-working equations were set up.With reference to foreign researches simulation data,the design point was calculated. According to Bevilaquas method,transient simulation of switching between conventional turbofan and hover turboshaft cycle was carried out.The results of numerical simulation indicate that the error of the mathematical model and foreign research data is less than 1.5%,and the thrust meets hover state requirements.Both models can offer high levels of thrust by increasing the fuel flow a little.The performance variation in simulation is consistent with the specialty of STOVL,so the modeling method of STOVL proposed is feasible.
引文
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[2]叶代勇,滕健,郭捷,等.短距起飞/垂直降落战斗机发动机发展及关键技术分析[J].航空发动机,2013,39(1):74-78.YE Daiyong,TENG Jian,GUO Jie,et al.Analysis of development and key technique for short takeoff and vertical landing(STOVL)fighter engine[J].Aeroengine,2013,39(1):74-78.(in Chinese)
[3]Biesiadny T J,Mcardle J G,Esker B S.Overview of STOVL aircraft propulsion research offtakes and vertical lift systems[R].AIAA 93-4865,1993.
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[7]Yin J,Pilidis P,Ramsden K W,et al.Assessment of variable-cycle propulsion systems for ASTOVL[J].Aircraft Engineering and Aerospace Technology,2000,72(6):537-544.
[8]Wood A,Pilidis P.A variable cycle jet engine for ASTOVL aircraft[J].Aircraft Engineering and Aerospace Technology,1997,69(6):534-539.
[9]Platt J T,Aerodrome W.Development of STOVL combat aircraft[J].AIAA 91-3183,1991.
[10]Varelis A G.Variable cycle engine for combat STOVL aircraft[D].Cranfiled,UK:Cranfield University,2007.
[11]张海明,骆广琦,孟龙,等.STOVL型战斗机变循环发动机性能数值模拟[J].空军工程大学学报:自然科学版,2012,12(6):13-17.ZHANG Haiming,LUO Guangqi,Meng Long,et al.Numerical simulation on performance of a variable cycle engine for STOVL fighter[J].Journal of Air Force Engineering University:Natural Science Edition,2012,12(6):13-17.(in Chinese)
[12]刘帅,王占学,蔡元虎,等.升力风扇和涡扇发动机组合动力系统性能模拟与分析[J].航空动力学报,2013,28(5):1095-1100.LIU Shuai,WANG Zhanxue,CAI Yuanhu,et al.Simulation and analysis of performance for combination of lift fan and turbofan engine power system[J].Journal of Aerospace Power,2013,28(5):1095-1100.(in Chinese)
[13]Maddock I A,Hirschberg M J.The quest for stable jet borne vertical lift:ASTOVL to F-35STOVL[R].AIAA-2011-6999,2011.
[14]方昌德.航空发动机的发展研究[M].北京:航空工业出版社,2009.
[15]Bevilaqua P.Future applications of the JSF variable propulsion cycle[R].AIAA-2003-2614,2003.
[16]郑志成,周洲,昌敏,等.升力风扇垂直起降飞机阻力特性分析[J].西北工业大学学报,2012,30(1):6-10.ZHENG Zhicheng,ZHOU Zhou,CHANG Min,et al.Analyzing drag characteristics to obtain effective guidelines for configuration design of lift-fan VTOL[J].Journal of Northwestern Polytechnical University,2012,30(1):6-10.(in Chinese)
[17]范作民,傅巽权.热力过程计算与燃气表[M].北京:国防工业出版社,1987.
[18]周文祥,黄金泉.涡扇发动机高空起动模型研究[J].航空动力学报,2007,22(8):1384-1390.ZHOU Wenxiang,HUANG Jinquan.Research on the startup model of turbofan engine at high altitude[J].Journal of Aerospace Power,2007,22(8):1384-1390.(in Chinese)
[19]Bevilaqua P.The shaft driven lift fan propulsion system for the joint strike fighter[R].Virginia:the American Helicopter Society 53rd Annual Forum,1997.
[2]叶代勇,滕健,郭捷,等.短距起飞/垂直降落战斗机发动机发展及关键技术分析[J].航空发动机,2013,39(1):74-78.YE Daiyong,TENG Jian,GUO Jie,et al.Analysis of development and key technique for short takeoff and vertical landing(STOVL)fighter engine[J].Aeroengine,2013,39(1):74-78.(in Chinese)
[3]Biesiadny T J,Mcardle J G,Esker B S.Overview of STOVL aircraft propulsion research offtakes and vertical lift systems[R].AIAA 93-4865,1993.
[4]Bevilaqua P,Eshleman J,Falabella D,et al.ASTOVL aircraft technology demonstration program[J].Lockheed Martin Skunk Works Report TR-96-1,1996.
[5]Zygmunt J P.Lift fan technology studies[R].NASA Report CR-761,1967.
[6]Drummond C K,Ouzts P J.Real-time simulation of an F110/STOVL turbofan engine[R].NASA-TM-89-102409,1989.
[7]Yin J,Pilidis P,Ramsden K W,et al.Assessment of variable-cycle propulsion systems for ASTOVL[J].Aircraft Engineering and Aerospace Technology,2000,72(6):537-544.
[8]Wood A,Pilidis P.A variable cycle jet engine for ASTOVL aircraft[J].Aircraft Engineering and Aerospace Technology,1997,69(6):534-539.
[9]Platt J T,Aerodrome W.Development of STOVL combat aircraft[J].AIAA 91-3183,1991.
[10]Varelis A G.Variable cycle engine for combat STOVL aircraft[D].Cranfiled,UK:Cranfield University,2007.
[11]张海明,骆广琦,孟龙,等.STOVL型战斗机变循环发动机性能数值模拟[J].空军工程大学学报:自然科学版,2012,12(6):13-17.ZHANG Haiming,LUO Guangqi,Meng Long,et al.Numerical simulation on performance of a variable cycle engine for STOVL fighter[J].Journal of Air Force Engineering University:Natural Science Edition,2012,12(6):13-17.(in Chinese)
[12]刘帅,王占学,蔡元虎,等.升力风扇和涡扇发动机组合动力系统性能模拟与分析[J].航空动力学报,2013,28(5):1095-1100.LIU Shuai,WANG Zhanxue,CAI Yuanhu,et al.Simulation and analysis of performance for combination of lift fan and turbofan engine power system[J].Journal of Aerospace Power,2013,28(5):1095-1100.(in Chinese)
[13]Maddock I A,Hirschberg M J.The quest for stable jet borne vertical lift:ASTOVL to F-35STOVL[R].AIAA-2011-6999,2011.
[14]方昌德.航空发动机的发展研究[M].北京:航空工业出版社,2009.
[15]Bevilaqua P.Future applications of the JSF variable propulsion cycle[R].AIAA-2003-2614,2003.
[16]郑志成,周洲,昌敏,等.升力风扇垂直起降飞机阻力特性分析[J].西北工业大学学报,2012,30(1):6-10.ZHENG Zhicheng,ZHOU Zhou,CHANG Min,et al.Analyzing drag characteristics to obtain effective guidelines for configuration design of lift-fan VTOL[J].Journal of Northwestern Polytechnical University,2012,30(1):6-10.(in Chinese)
[17]范作民,傅巽权.热力过程计算与燃气表[M].北京:国防工业出版社,1987.
[18]周文祥,黄金泉.涡扇发动机高空起动模型研究[J].航空动力学报,2007,22(8):1384-1390.ZHOU Wenxiang,HUANG Jinquan.Research on the startup model of turbofan engine at high altitude[J].Journal of Aerospace Power,2007,22(8):1384-1390.(in Chinese)
[19]Bevilaqua P.The shaft driven lift fan propulsion system for the joint strike fighter[R].Virginia:the American Helicopter Society 53rd Annual Forum,1997.