Volume 29 Issue 5
May  2014
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2014  >  (5): 993-1000
ZHENG Long-xi, LU Jie, YAN Chuan-jun, QIU Hua, WANG Zhi-wu, HUANG Xi-qiao, LI Xiao-feng. Research progress on pulse detonation turbine engine[J]. Journal of Aerospace Power, 2014, (5): 993-1000.
Citation: ZHENG Long-xi, LU Jie, YAN Chuan-jun, QIU Hua, WANG Zhi-wu, HUANG Xi-qiao, LI Xiao-feng. Research progress on pulse detonation turbine engine[J]. Journal of Aerospace Power, 2014, (5): 993-1000.
shu

Research progress on pulse detonation turbine engine

  • School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

  • Received Date: 2013-03-19
  • Publish Date: 2014-05-28
    Abstract
  • Basic concept,main structures and primary characteristics were reviewed of pulse detonation turbine engine.A detail trend at home and abroad of its development was presented;the results of our recent experimental researches were summarized;the key technology and research areas of pulse detonation turbine engine were discussed.Performance calculations show that the specific fuel consumption of pulse detonation turbine engine could have a reduction about 5% to 15% compared with that of traditional turbine jet engine. The specific power of the turbine driven by pulse detonation combustor is higher than that driven by constant pressure combustor under the same inlet conditions of the combustors.A self-aspirated model was successfully achieved by driving the turbine with pulse detonation combustor whose oxidant was supplied by the turbine driven compressor.The results verify the feasibility of substituting the traditional constant pressure combustor with pulse detonation combustor.

     

    • FullText(HTML)
  • loading
    • References(49)
  • [1]
    Kailasanath K.Research on pulse detonation combustion systems:a status report[R].AIAA-2009-631, 2009.
    [2]
    严传俊, 范玮, 黄希桥.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.
    [3]
    Petters D P, Felder J L.Engine system performance of pulse detonation concepts using the NPSS program[R].AIAA-2002-3910, 2002.
    [4]
    Mawid M A, Park T W, Sekar B.Performance analysis of a pulse detonation device as an afterburner[R].AIAA-2000-3474, 2000.
    [5]
    Mawid M A, Park T W.Towards replacement of turbofan engines afterburners with pulse detonation devices[R].AIAA-2001-3470, 2001.
    [6]
    Mawid M, Arana C, Park T, et al.Turbofan engine thrust augmentation with pulse detonation afterburners-nozzle influence[R].AIAA-2002-4073, 2002.
    [7]
    Rasheed A, Furman A H, Dean A J.Experimental investigations of an axial turbine driven by a multi-tube pulsed detonation combustor system[R].AIAA-2005-4209, 2005.
    [8]
    Andrus I Q, King P I.Evaluation of a high bypass turbofan hybrid utilizing a pulsed detonation combustor[R].AIAA-2007-5074, 2007.
    [9]
    Pintgen F, Tangirala V.Effect of mixture properties on the performance estimates of a pulse detonation combustor-based hybrid engine[R].AIAA-2007-5391, 2007.
    [10]
    Fuhua M, Thomas L, Venkat T.Limit cycle investigations of pulse detonation combustor for pulse detonation turbine engine[R].AIAA-2010-6714, 2010.
    [11]
    Rasheed A, Tangirala V E, Vandervort C L, et al.Interactions of a pulsed detonation engine with a 2D turbine blade cascade[R].AIAA-2004-1207, 2004.
    [12]
    Nango A, Inaba K, Kojima T.Aerodynamic effect of turbine blade geometry in pulse detonation combustor[R].AIAA-2007-1176, 2007.
    [13]
    Nango A, Inaba K, Kojima T, et al.Numerical study of detonation interaction with a single-stage axial turbine[R].AIAA-2008-985, 2008.
    [14]
    Nango A, Inaba K, Kojima T, et al.Numerical study on single-stage axial turbine with pulse detonation combustor[R].AIAA-2009-294, 2009.
    [15]
    Kojima T, Tsuboi N, Taguchi H, et al.Design study of turbine for pulse detonation combustor[R].AIAA-2007-5081, 2007.
    [16]
    Xia G, Li D, Merkle C.Modeling of pulse detonation tubes in turbine systems[R].AIAA-2005-0225, 2005.
    [17]
    Van Zante D, Envia E, Turner M.The attenuation of a detonation wave by an aircraft engine axial turbine stage[R].NASA TM-2007-214972, 2007.
    [18]
    Hoke J, Bradley R, Stutrud J, et al.Integration of a pulsed detonation engine with an ejector pump and with a turbo-charger as methods to self-asperate[R].AIAA-2002-0615, 2002.
    [19]
    Schauer F, Bradley R, Hoke J.Interaction of a pulsed detonation engine with a turbine[R].AIAA-2003-0891, 2003.
    [20]
    Rouser K P, King P I, Schauer F R, et al.Unsteady performance of a turbine driven by a pulse detonation engine[R].AIAA-2010-1116, 2010.
    [21]
    Rouser K P, Schauer F R, Sondergaard R, et al.Parametric study of unsteady turbine performance driven by a pulse detonation combustor[R].AIAA-2010-6536, 2010.
    [22]
    Rouser K P, King P I, Schauer F R, et al.Time-accurate flow field and rotor speed measurements of a pulsed detonation driven turbine[R].AIAA-2011-0577, 2011.
    [23]
    Rouser K P, King P I, Schauer F R, et al.Performance of a turbine driven by a pulsed detonation combustor.Denver, Colorado, US:The ASME 2011 International Mechanical Engineering Congress and Exposition, 2011.
    [24]
    Rankin B A, Gore J P, Hoke J L, et al.Radiation measurements and temperature estimates of unsteady exhaust plumes exiting from a turbine driven by pulsed detonation combustion[R].AIAA-2013-0886, 2013.
    [25]
    Rouser K P, King P I, Schauer F R, et al.Experimental performance evaluation of a turbine driven by pulsed detonations[R].AIAA-2013-1212, 2013.
    [26]
    Rasheed A, Furman A, Dean A J.Experimental investigations of an axial turbine driven by a multi-tube pulsed detonation combustor system[R].AIAA-2005-4209, 2005.
    [27]
    Baptista M, Rasheed A, Badding B, et al.Mechanical response in a multi-tube pulsed detonation combustor-turbine hybrid system[R].AIAA-2006-1234, 2006.
    [28]
    Rasheed A, Furman A, Dean A.Wave attenuation and interactions in a pulsed detonation combustor-turbine hybrid system[R].AIAA-2006-1235, 2006.
    [29]
    Rasheed A, Furman A, Dean A J.Wave interactions in a multi-tube pulsed detonation combustor-turbine hybrid system[R].AIAA-2006-4447, 2006.
    [30]
    Rasheed A, Furman A H, Dean A J.Pressure measurements and attenuation in a hybrid multi-tube pulse detonation system[J].Journal of Propulsion and Power, 2009, 25(1):148-161.
    [31]
    Rasheed A, Furman A H, Dean A J.Experimental investigations of the performance of a multitube pulse detonation turbine system[J].Journal of Propulsion and Power, 2011, 27(3):586-596.
    [32]
    Glaser A J, Caldwell N, Gutmark E.Performance measurements of a pulse detonation combustor array integrated with an axial flow turbine[R].AIAA-2006-1232, 2006.
    [33]
    Caldwell N, Glaser A, Gutmark E.Acoustic interactions of a pulse detonation engine array with a gas turbine[R].AIAA-2006-1233, 2006.
    [34]
    Glaser A J, Caldwell N, Gutmark E.Performance of an axial flow turbine driven by multiple pulse detonation combustors[R].AIAA-2007-1244, 2007.
    [35]
    Caldwell N, Brunet R, Antoine A, et al.Experimental analysis of a hybrid pulse detonation combustor/gas turbine engine[R].AIAA-2008-121, 2008.
    [36]
    Caldwell N, Gutmark E.Performance analysis of a hybrid pulse detonation combustor/gas turbine system[R].AIAA-2008-4880, 2008.
    [37]
    Tsukui A, Matsumoto K, Kasahara J, et al.Research on interaction between an intermittent flow and a PDE turbine[R].AIAA-2009-295, 2009.
    [38]
    Tsuji T, Shirakawa S, Yoshihashi T, et al.Interaction between two cylinders in a pulse detonation engine[J].International Journal of Energetic Materials and Chemical Propulsion, 2009, 8(6):489-500.
    [39]
    Munday D, George A S, Driscoll R, et al.The design and validation of a pulse detonation engine facility with and without axial turbine integration[R].AIAA-2013-0275, 2013.
    [40]
    George A S, Driscoll R, Munday D, et al.Experimental investigation of axial turbine performance driven by steady and pulsating flows[R].AIAA-2013-0276, 2013.
    [41]
    Fernelius M H, Gorrell S E, Hoke J L, et al.Design and fabrication of an experimental test facility to compare the performance of pulsed and steady flow through a turbine[R].AIAA-2013-0277, 2013.
    [42]
    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)
    [43]
    陈文娟, 范玮, 邱华, 等.外涵装有脉冲爆震加力燃烧室的涡扇发动机热力性能分析[J].西北工业大学学报, 2010, 28(2):240-244. CHEN Wenjuan, FAN Wei, QIU Hua, et al.Exploring calculation of thermodynamic performance of the turbo-fan engine with PDCs(pulse detonation combustors) in BD(bypass duct)[J].Journal of Northwestern Polytechnical University, 2010, 28(2):240-244.(in Chinese)
    [44]
    CHEN Wenjuan, FAN Wei, QIU Hua, et al.Thermodynamic performance analysis of turbofan engine with a pulse detonation duct heater[J].Aerospace Science and Technology, 2011, 23(1):206-212.
    [45]
    蒋联友, 严传俊, 邓君香, 等.爆震波与涡轮叶片相互作用的数值模拟[J].航空动力学报, 2009, 24(1):60-64. JIANG Lianyou, YAN Chuanjun, DENG Junxiang, et al.Numerical simulation of detonation wave interacting with turbine blade[J].Journal of Aerospace Power, 2009, 24(1):60-64.(in Chinese)
    [46]
    郑龙席, 邓君香, 严传俊, 等.混合式脉冲爆震发动机原理性试验系统设计、集成与调试[J].实验流体力学, 2009, 23(1):74-78. ZHENG Longxi, DENG Junxiang, YAN Chuanjun, et al.Design integration and debugging on principle test system of hybrid pulse detonation engine[J].Journal of Experiments in Fluid Mechanics, 2009, 23(1):74-78.(in Chinese)
    [47]
    DENG Junxiang, ZHENG Longxi, YAN Chuanjun, et al.Experimental investigations of a pulse detonation combustor integrated with a turbine[J].Internationai Journal of Turbo & Jet-Engines, 2008, 25(4):247-257.
    [48]
    邓君香, 郑龙席, 严传俊, 等.脉冲爆震燃烧室与涡轮相互作用的试验[J].航空动力学报, 2009, 24(2):307-312. DENG Junxiang, ZHENG Longxi, YAN Chuanjun, et al.Experimental investigations of interaction of a pulse detonation combustor with a turbine[J].Journal of Aerospace Power, 2009, 24(2):307-312.(in Chinese)
    [49]
    邓君香, 郑龙席, 严传俊, 等.脉冲爆震燃烧室与涡轮组合的性能试验研究[J].西北工业大学学报, 2009, 27(3):300-304. DENG Junxiang, ZHENG Longxi, YAN Chuanjun, et al.Studying experimentally performances of a pulse detonation combustor(PDC)integrated with a turbine[J].Journal of Northwestern Polytechnical University, 2009, 27(3):300-304.(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(966.0KB)
    XML

    Article Metrics

    Article views (2477) PDF downloads(1283) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return