Advanced Search
Volume 41 Issue 7
Jul.  2015
Turn off MathJax
Article Contents
Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(7): 1215-1222.
CHU Min, XU Xu. Acoustic numerical simulation of high frequency combustion instability[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(7): 1215-1222. doi: 10.13700/j.bh.1001-5965.2014.0527(in Chinese)
Citation: CHU Min, XU Xu. Acoustic numerical simulation of high frequency combustion instability[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(7): 1215-1222. doi: 10.13700/j.bh.1001-5965.2014.0527(in Chinese)
shu

Acoustic numerical simulation of high frequency combustion instability

doi: 10.13700/j.bh.1001-5965.2014.0527

  • School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 26 Aug 2014
  • Rev Recd Date: 07 Oct 2014
  • Publish Date: 20 Jul 2015
    Abstract
  • High frequency combustion instability is one of the major issues existed in design process of liquid rocket engine. A time domain numerical simulation was used to predict high frequency combustion instability of hypergolic propellant orbit maneuvering engine (OME) by computational aeroacoustics, which was less dispersive and dissipative. The coupling between unsteady heat release and acoustics was realized by Crocco's pressure time lag model. The effects of different parameters of pressure time lag model on stability were analyzed, and the stability map was obtained. The first order transverse mode and the first order radial mode were recognized as the most dominant instable modes, which were consisted with the instable modes recognized from experimental results of ground test. The results show that high frequency combustion instability can be successfully predicted, when acoustic perturbation equations with Crocco's pressure time lag model are solved in the time domain by computational aeroacoustics.

     

    • FullText(HTML)
  • loading
    • References(17)
  • [1]
    刘国球.液体火箭发动机原理[M].北京: 宇航出版社, 1993: 251-252.Liu G Q.The Princple of liquid rocket engine[M].Beijing: Astronautic Publishing House, 1993: 251-252(in Chinese).
    [2]
    Zinn B T. Pulsating combustion, advanced combustion methods[M].London: Academic Press, 1986: 113-181.
    [3]
    Culick F E C.A note on Rayleigh's criterion[J].Combustion Science and Technology, 1987, 56(4-6): 159-166.
    [4]
    Habiballah M, Lourme D, Pit F.A comprehensive model for combustion stability studies applied to the Ariane Viking engine, AIAA-1988-0086[R].Reston: AIAA, 1988: 1-7.
    [5]
    尕永婧, 张会强, 王希麟.隔板对燃烧室压力高频自激振荡的抑制作用[J].清华大学学报, 2012, 52(7): 1007-1012. Ga Y J, Zhang H Q, Wang X L.Effects of baffles on self-triggered high frequency pressure oscillations in a thrust chamber[J].Journal of Tsinghua University, 2012, 52(7): 1007-1012(in Chinese).
    [6]
    Matthew E H, William E A, Charles L M.Analysis of self-excited combustion instabilities using two-and three-dimensional simulations[J].Journal of Propulsion and Power, 2013, 29(2): 396-409.
    [7]
    Pieringer J, Sattelmayer T, Fassl F.Simulation of combustion instabilities in liquid rocket engines with acoustic perturbation equations [J].Journal of Propulsion and Power, 2009, 25(5): 1020-1031.
    [8]
    Oberger C L, Hines W S, Falk A Y.High-temperature earth-storable propellant acoustic cavity technology, NASA N75-19460[R].California: Rocketdyne Division, 1974: 1-82.
    [9]
    Kim J S. Effects of turbulence on linear acoustic instability: Spatial inhomogeneity[C]//Progress in Aeronautics and Astronautics.Reston: AIAA, 1995, 169: 431-454.
    [10]
    Ewert R, Schröder W.Acoustic perturbation equations based on flow decomposition via source filtering[J].Journal of Computational Physics, 2003, 188(2): 365-398.
    [11]
    Laroche E, Habiballah M, Kuentzmann P.Numerical analysis of liquid rocket combustion instability: Preliminary 3D acoustic calculations[C]//35th Intersociety Energy Conversion Engineering Conference and Exhibit. Reston: AIAA, 2000: 1-9.
    [12]
    Tam C K W, Webb J C.Dispersion-relation-preserving finite difference schemes for computational acoustics[J].Journal of Computational Physics, 1993, 107(2): 262-281.
    [13]
    Gaitonde D V, Visbal M R.Padé-type higher-order boundary filters for the Navier-Stoke equations[J].AIAA Journal, 2000, 38(11): 2103-2112.
    [14]
    Tam C K W, Dong Z.Wall boundary conditions for high-order finite-difference schemes in computational aeroacoustics[J].Theoretical and Computional Fluid Dynamics, 1994, 6(5-6): 303-322.
    [15]
    Laudien E, Pongratz R, Pierro R, et al.Experimental procedures aiding the design of acoustic cavities[C]//Progress in Aeronautics and Astronautics.Reston: AIAA, 1995, 169: 377-402.
    [16]
    Harrje D T, Reardon F H.Liquid rocket combustion instabilities, NASA SP-194[R].Reston: AIAA, 1972.
    [17]
    Milano D, Kirkpatrick A T, Quinlan J M, et al.Computation of acoustic oscillations and combustion stability in a rocket engine with combined hub/blade baffles, AIAA-2009-4866[R].Reston: AIAA, 2009.
    • 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
    XML

    Article Metrics

    Article views(901) PDF downloads(585) Cited by()
    Proportional views
    Related

    Copyright © Journal of Beijing University of Aeronautics and Astronautics

    Address: Editorial Department of Journal of Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Post Code: 100191 Email: jbuaa@buaa.edu.cn

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

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return