Volume 34 Issue 6
Jun.  2019
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Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude[J]. Journal of Aerospace Power, 2019, 34(6): 1273-1251. doi: 10.13224/j.cnki.jasp.2019.06.010
Citation: Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude[J]. Journal of Aerospace Power, 2019, 34(6): 1273-1251. doi: 10.13224/j.cnki.jasp.2019.06.010

Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude

doi: 10.13224/j.cnki.jasp.2019.06.010
  • Received Date: 2018-11-06
  • Publish Date: 2019-06-28
  • Based on characterizations of the structure and aerodynamic stability, the experimental investigation on the inlet total pressure distortion of the middle-bypass ratio turbofan engine at high altitude was carried out. The detailed available distortion project designs, distortion installations selection, and data processing standard were introduced. The test results showed that within the range of flight height less than 14 km, the height affected the steady state comprehensive distortion index a little. When flight height was 11km, and flight Mach number was 0.8, under the comprehensive distortion index less greater than 12%, the middle-bypass ratio turbofan engine could work steadily at military cruising regime and military climbing regime with air bleeding, and power extractions was 136 kW, when the flight height was 14 km, and flight Mach number was 0.39.

     

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  • [1]
    刘大响,叶培梁,胡骏,等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:航空工业出版社,2004.
    [2]
    国防科学技术工业委员会.航空燃气涡轮发动机稳定性设计与评定方法:GJB/Z224-2005[S].北京:中国标准出版社,2005:1-42.
    [3]
    胡骏,赵运生,丁宁,等.进气畸变对大涵道比涡扇发动机稳定性的影响[J].航空发动机,2013,39(6):6-12.HU Jun,ZHAO Yunsheng,DING Ning,et al.Investigation of influence of inlet distortion on high bypass ratio turbofan engine stability[J].Aeroengine,2013,39(6):6-12.(in Chinese)
    [4]
    严红明,赵运生,周淼,等.压力畸变对大涵道比涡扇发动机影响仿真[J].节能技术,2015,33(5):403-407.YAN Hangming,ZHAO Yunsheng,ZHOU Miao,et al.Simulation of the pressure distortion effect on high bypass ratio turbofan engine[J].Energy Conservation Technology,2015,33(5):403-407.(in Chinese)
    [5]
    NAKANO T,BREEZE-STRINGFELLOW A.A method for evaluating the effect of circumferential inlet distortion on the aerodynamic stability of multi-Stage axial-Flow compressors[R].ASME Paper GT2010-23541,2010.
    [6]
    SHIELDS M,MOHSENI K.Aerodynamic stability modes of low aspect ratio wings[R].AIAA-2013-4939,2013.
    [7]
    PEI J,WALL J.Estimation of aerodynamic stability derivatives for space launch system and impact on stability margins[R].AIAA-2013-4684,2013.
    [8]
    Society of Automotive Engineers.Inlet total pressure distortion considerations for gas turbine engines[R].AIR-1983-1419,1983.
    [9]
    Society of Automotive Engineers.Gas turbine engine inlet flow distortion guidelines[R].ABP-2002-1420B,2002.
    [10]
    彭生红,钟华贵,吴锋,等.移动插板容腔对发动机压力畸变流场影响[J].航空动力学报,2018,33(9):2242-2247.PENG Shenghong,ZHONG Huagui,WU Feng,et al.Effect on total pressure distortion flow distribution of engine with the movable flat baffle’s plenum volume[J].Journal of Aerospace Power,2018,33(9):2242-2247.(in Chinese)
    [11]
    BEALE D K,CRAMER K B.Development of improved method for simulation aircraft inlet distortion in turbine engine ground tests[R].AIAA-2002-3045,2002.
    [12]
    BION J R.Steady and unsteady distorted inlet flow simulation for engine ground tests[R].AIAA 84-1490,1984.
    [13]
    田金虎,乔渭阳,彭生红.航空发动机高空压力畸变试验[J].航空动力学报,2014,29(4):817-823.TIAN Jinhu,QIAO Weiyang,PENG Shenghong.the Experimental investigation on aero-engine altitude simulated inlet total pressure distortion[J].Journal of Aerospace Power,2014,29(4):817-823.(in Chinese)
    [14]
    江勇,张发启.基于实验的插板式进气畸变稳态压力场估计[J].空军工程大学学报(自然科学版),2007,8(2):1-3.JIANG Yong,ZHANG Faqi.Base on experiment the air inlet flow steady pressure distortion field estimate with the inserted board[J].Journal of Air Force Engineering University(Natural Science Edition),2007,8(2):1-3.(in Chinese)
    [15]
    林左鸣.世界航空发动机手册[M].北京:航空工业出版社,2012.
    [16]
    蒋聪.大涵道比涡扇发动机气动稳定性评定方法和软件研究[D].南京:南京航空航天大学,2016.JIANG Cong.Aerodynamic stability assessment and software research of high bypass ratio turbofan engine[D].Nanjing University of Aeronautics and Astronautics,2016.(in Chinese)
    [17]
    PETER G,MARTINN H.Modeling the dynamics of supersonic inlet/gas-turbine engine system for large-amplitude high-frequency disturbances[R].AIAA-2000-3594.2000.
    [18]
    REYNOLDS G.An experimental evaluation of unsteady flow effects on an axial compressor-p3 generator program[R].AFAPL-TR-73-43,1973.
    [19]
    程邦勤,陶增元,李军.某型涡扇发动机进气总压畸变的试验研究[J].推进技术,2003,24(1):21-23.CHENG Bangqin,TAO Zenyuan,LI Jun.Aerodynamic stability analysis of inlet total pressure distortion for turbofan[J].Journal of Propulsion Technology,2003,24(1):21-23.(in Chinese)
    [20]
    李文峰,马利东.某涡扇发动机压力畸变评定技术[J].西北工业大学学报,2003,21(5):540-543.LI Wenfeng,MA Lidong.Method and experimental facility for assessing pressure distortion of a certain turbofan engine[J].Journal of Northwestern Polytechnical University,2003,21(5):540-543.(in Chinese)
    [21]
    SMITH R E.Marrying airframes and engines in ground test facilities:an evolutionary revolution[R].AIAA 95-0950,1995.
    [22]
    DAVIS M,BEALE D,BOYER K.An example for integrated gas turbine engine testing and analysis using modeling and simulation[R].Las Cruces,NM:the ITEA Modeling and Simulation Conference,2006.
    [23]
    CHUNG K,HOSNY W M,STEENKEN W G.Aerodynamic stability analysis of NASA J85-13 planar pressure pulse generator installation[R].NASA-CR-165141,1980.
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