脉冲爆震涡轮发动机共同工作特性
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摘要
为了研究脉冲爆震涡轮发动机(pulse detonation turbine engine,PDTE)共同工作特性和整机性能,建立了其共同工作分析模型。一方面,利用该模型对PDTE原理样机的性能进行了评估并与试验结果进行对比,计算结果表明,模型计算误差不大于11.2%,随着工作频率的提高,PDTE原理样机推力可进一步提升,但共同工作线朝压气机喘振边界靠近。另一方面,以某涡喷发动机为原型,对利用脉冲爆震燃烧室(pulsedetonation combustor,PDC)替换主燃烧室后的整机性能进行了研究。计算结果显示:保持PDTE的迎风面积和涡轮前温度与原涡喷相同,PDTE的最佳压气机增压比从原发动机的5.5减小到2.25,当PDTE工作频率达41.5Hz时,流量与原涡喷相同,此时推力比原涡喷提升20.2%,耗油率降低14.0%。
The cooperating work analysis model of pulsed detonation turbine engine(PDTE)was established in order to analyze the cooperating work characteristics of PDTE and its overall performance.On the one hand,using the model to evaluate the performance of PDTE prototype and compare it with the experimental results,the calculation results showed that:the model calculation error was no more than 11.2%.With the increase of operating frequency,the thrust of PDTE prototype can be further improved,but the cooperating work line gradually moved to the compressor surge boundary.On the other hand,the engine performance after replacing the main combustion chamber with a pulse detonation combustor(PDC)was studied by using a turbojet engine as a prototype.The calculation results showed that the windward area and the turbine inlet temperature of the PDTE were the same with the original turbojet engine.The optimal compression ratio of compressor of the PDTE was reduced from 5.5 of the original engine to 2.25.The flow rate was the same with that of the original turbojet engine when the PDTE operating frequency reached 41.5 Hz,meanwhile,the thrust increased by 20.2% compared with the original turbojet engine,and the specific fuel consumption reduced by 14.0%.
The cooperating work analysis model of pulsed detonation turbine engine(PDTE)was established in order to analyze the cooperating work characteristics of PDTE and its overall performance.On the one hand,using the model to evaluate the performance of PDTE prototype and compare it with the experimental results,the calculation results showed that:the model calculation error was no more than 11.2%.With the increase of operating frequency,the thrust of PDTE prototype can be further improved,but the cooperating work line gradually moved to the compressor surge boundary.On the other hand,the engine performance after replacing the main combustion chamber with a pulse detonation combustor(PDC)was studied by using a turbojet engine as a prototype.The calculation results showed that the windward area and the turbine inlet temperature of the PDTE were the same with the original turbojet engine.The optimal compression ratio of compressor of the PDTE was reduced from 5.5 of the original engine to 2.25.The flow rate was the same with that of the original turbojet engine when the PDTE operating frequency reached 41.5 Hz,meanwhile,the thrust increased by 20.2% compared with the original turbojet engine,and the specific fuel consumption reduced by 14.0%.
引文
[1]严传俊,范玮,郑龙席,等.脉冲爆震发动机原理及关键技术[M].西安:西北工业大学出版社,2005.
[2]郑龙席,卢杰,严传俊,等.脉冲爆震涡轮发动机研究进展[J].航空动力学报,2014,29(5):993-1000.ZHENG Longxi,LU Jie,YAN Chuanjun,et al.Research progress on pulse detonation tubine engine[J].Journal of Aerospace Power,2014,29(5):993-1000.(in Chinese)
[3]邓君香,严传俊,郑龙席,等.装有脉冲爆震主燃烧室的燃气涡轮发动机热力性能计算[J].西北工业大学学报,2008,26(3):362-367.DENG Junxiang,YAN Chuanjun,ZHENG Longxi,et al.Calculating performance of gas turbine engine with embedded PDC[J].Journal of Northwestern Polytechnical University,2008,26(3):362-367.(in Chinese)
[4]何龙,郑龙席,邱华,等.脉冲爆震涡轮发动机性能计算[J].推进技术,2012,33(5):665-670.HE Long,ZHENG Longxi,QIU Hua,et al.Calculating performance of pulse detonation turbo engine[J].Journal of Propulsion Technology,2012,33(5):665-670.(in Chinese)
[5]PAXSON D E.A performance map for ideal air breathing pulse detonation engines[R].AIAA-2001-3465,2001.
[6]TANGIRALA V E,RASHEED A,DEAN A J.Performance of a pulse detonation combustor-based hybrid engine[R].ASME Paper GT2007-28056,2007.
[7]GOLDMEER J,TANGIRALA V,DEAN A.System-level performance estimation of a pulse detonation based hybrid engine[J].Journal of Engineering for Gas Turbines and Power,2008,130(1):82-93.
[8]ENDO T,FUJIWARA T.A simplified analysis on a pulse detonation engine model[J].Transactions of the Japan Society for Aeronautical and Space Sciences,2002,44(146):217-222.
[9]ENDO T,FUJIWARA T.Analytical estimation of performance parameters of an ideal pulse detonation engine[J].Transactions of the Japan Society for Aeronautical and Space Sciences,2003,45(150):249-254.
[10]ENDO T,KASAHARA J,MATSUO A,et al.Pressure history at the thrust wall of a simplified pulse detonation engine[J].AIAA Journal,2004,42(9):1921-1930.
[11]LU Jie,ZHENG Longxi,XU Zheyang,et al.Performance investigation of a pulse detonation turbine engine[J].Journal of Aerospace Engineering,2016,230(2):350-359.
[12]XIA Guoping,LI Ding,MERKLE C L.Modeling of pulsed detonation tubes in turbine systems[R].AIAA 2005-225,2005.
[13]AYAKA N,KAZUAKI I,TAKAYUKI K,et al.Aerodynamic effect of turbine blade geometry in pulse detonation combustor[R].AIAA 2007-1176,2007.
[14]SURESH A,HOFER D C,TANGIRALA V E.Turbine efficiency for unsteady periodic flows[R].AIAA 2009-504,2009.
[15]廉筱纯,吴虎.航空燃气轮机原理[M].西安:西北工业大学出版社,2005.
[16]李晓丰.脉冲爆震涡轮发动机技术研究[D].西安:西北工业大学,2013.LI Xiaofeng.The technology research on the pulse detonation turbine engine[D].Xian:Northwestern Polytechnical University,2013.(in Chinese)
[17]李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验[J].航空动力学报,2013,28(12):2731-2736.LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Principle experiment of two-phase pulse detonation turbine engine[J].Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese)
[18]李晓丰,郑龙席,邱华,等.脉冲爆震涡轮发动机原理性试验研究[J].实验流体力学,2013,27(6):1-5.LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental study on the principle of pulse detonation turbine engine[J].Journal of Experiments in Fluid Mechanics,2013,27(6):1-5.(in Chinese)
[19]邱华,徐泽阳,郑龙席,等.脉冲爆震涡轮发动机增推装置性能试验[J].航空学报,2016,37(2):522-532.QIU hua,XU Zheyang,ZHENG Longxi,et al.Tests of pulse detonation turbine engine performance with thrust augmentation devices[J].Acta Aeronautica et Astronautica Sinica,2016,37(2):522-532.(in Chinese)
[20]张义宁,王家骅,张靖周.频率30~50Hz两相脉冲爆震发动机研究[J].航空学报,2006,27(6):993-997ZHANG Yining,WANG Jiahua,ZHANG Jingzhou.Investigationon two phase pulse detonation engine at the frequency 30-50Hz[J].Acta Aeronautica et Astronautica Sinica,2006,27(6):993-997.(in Chinese)
[2]郑龙席,卢杰,严传俊,等.脉冲爆震涡轮发动机研究进展[J].航空动力学报,2014,29(5):993-1000.ZHENG Longxi,LU Jie,YAN Chuanjun,et al.Research progress on pulse detonation tubine engine[J].Journal of Aerospace Power,2014,29(5):993-1000.(in Chinese)
[3]邓君香,严传俊,郑龙席,等.装有脉冲爆震主燃烧室的燃气涡轮发动机热力性能计算[J].西北工业大学学报,2008,26(3):362-367.DENG Junxiang,YAN Chuanjun,ZHENG Longxi,et al.Calculating performance of gas turbine engine with embedded PDC[J].Journal of Northwestern Polytechnical University,2008,26(3):362-367.(in Chinese)
[4]何龙,郑龙席,邱华,等.脉冲爆震涡轮发动机性能计算[J].推进技术,2012,33(5):665-670.HE Long,ZHENG Longxi,QIU Hua,et al.Calculating performance of pulse detonation turbo engine[J].Journal of Propulsion Technology,2012,33(5):665-670.(in Chinese)
[5]PAXSON D E.A performance map for ideal air breathing pulse detonation engines[R].AIAA-2001-3465,2001.
[6]TANGIRALA V E,RASHEED A,DEAN A J.Performance of a pulse detonation combustor-based hybrid engine[R].ASME Paper GT2007-28056,2007.
[7]GOLDMEER J,TANGIRALA V,DEAN A.System-level performance estimation of a pulse detonation based hybrid engine[J].Journal of Engineering for Gas Turbines and Power,2008,130(1):82-93.
[8]ENDO T,FUJIWARA T.A simplified analysis on a pulse detonation engine model[J].Transactions of the Japan Society for Aeronautical and Space Sciences,2002,44(146):217-222.
[9]ENDO T,FUJIWARA T.Analytical estimation of performance parameters of an ideal pulse detonation engine[J].Transactions of the Japan Society for Aeronautical and Space Sciences,2003,45(150):249-254.
[10]ENDO T,KASAHARA J,MATSUO A,et al.Pressure history at the thrust wall of a simplified pulse detonation engine[J].AIAA Journal,2004,42(9):1921-1930.
[11]LU Jie,ZHENG Longxi,XU Zheyang,et al.Performance investigation of a pulse detonation turbine engine[J].Journal of Aerospace Engineering,2016,230(2):350-359.
[12]XIA Guoping,LI Ding,MERKLE C L.Modeling of pulsed detonation tubes in turbine systems[R].AIAA 2005-225,2005.
[13]AYAKA N,KAZUAKI I,TAKAYUKI K,et al.Aerodynamic effect of turbine blade geometry in pulse detonation combustor[R].AIAA 2007-1176,2007.
[14]SURESH A,HOFER D C,TANGIRALA V E.Turbine efficiency for unsteady periodic flows[R].AIAA 2009-504,2009.
[15]廉筱纯,吴虎.航空燃气轮机原理[M].西安:西北工业大学出版社,2005.
[16]李晓丰.脉冲爆震涡轮发动机技术研究[D].西安:西北工业大学,2013.LI Xiaofeng.The technology research on the pulse detonation turbine engine[D].Xian:Northwestern Polytechnical University,2013.(in Chinese)
[17]李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验[J].航空动力学报,2013,28(12):2731-2736.LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Principle experiment of two-phase pulse detonation turbine engine[J].Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese)
[18]李晓丰,郑龙席,邱华,等.脉冲爆震涡轮发动机原理性试验研究[J].实验流体力学,2013,27(6):1-5.LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental study on the principle of pulse detonation turbine engine[J].Journal of Experiments in Fluid Mechanics,2013,27(6):1-5.(in Chinese)
[19]邱华,徐泽阳,郑龙席,等.脉冲爆震涡轮发动机增推装置性能试验[J].航空学报,2016,37(2):522-532.QIU hua,XU Zheyang,ZHENG Longxi,et al.Tests of pulse detonation turbine engine performance with thrust augmentation devices[J].Acta Aeronautica et Astronautica Sinica,2016,37(2):522-532.(in Chinese)
[20]张义宁,王家骅,张靖周.频率30~50Hz两相脉冲爆震发动机研究[J].航空学报,2006,27(6):993-997ZHANG Yining,WANG Jiahua,ZHANG Jingzhou.Investigationon two phase pulse detonation engine at the frequency 30-50Hz[J].Acta Aeronautica et Astronautica Sinica,2006,27(6):993-997.(in Chinese)