Volume 42 Issue 6
Jun.  2016
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LIU Chengchuan, XU Quanhong, YU Bowenet al. Influence of primary swirl offset on downstream flowfield of dual-swirl cup[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(6): 1244-1249. doi: 10.13700/j.bh.1001-5965.2015.0402(in Chinese)
Citation: LIU Chengchuan, XU Quanhong, YU Bowenet al. Influence of primary swirl offset on downstream flowfield of dual-swirl cup[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(6): 1244-1249. doi: 10.13700/j.bh.1001-5965.2015.0402(in Chinese)

Influence of primary swirl offset on downstream flowfield of dual-swirl cup

doi: 10.13700/j.bh.1001-5965.2015.0402
  • Received Date: 18 Jun 2015
  • Publish Date: 20 Jun 2016
  • Dual-swirl cup has been widely used in aero-engine combustor because of excellent comprehensive combustion performance. But it is inevitable that there will be slight misalignment during its assembly, and in order to examine whether these subtle errors will affect combustion performance, more detailed study of the effect of local structure and aerodynamic characteristics on the downstream flow field in a double swirl cup is required. Therefore, we tested downstream cold flow field of the dual-swirl cup using particle image velocimetry (PIV) technology under normal temperature and pressure conditions to explore the impact law of the offset distance of the primary swirl on downstream flow field of the reverse double swirl cup. The results show that with the increase of the offset distance, in a small non dimensional offset area, downstream flow field does not change, and when the offset distance continues to increase, downstream flow field will apparently shift with excellent symmetry, which provides a reference for swirl cup installation.

     

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  • [1]
    陈大光,张津,朱之丽.推重比15一级发动机有关总体性能的关键技术和难点分析[J].航空动力学报,2001,16(1):8-12.CHEN D G,ZHANG J,ZHU Z L.Performance related key technologies and difficulties of engines with thrust to weight ratio up to level of 15[J].Journal of Aerospace Power,2001,16(1):8-12(in Chinese).
    [2]
    王占学,刘增文,蔡元虎,等.推重比15一级发动机关键技术及分析[J].航空发动机,2010,36(1):57-62.WANG Z X,LIU Z W,CAI Y H,et al.Key technologies and analysis of aeroengine with thrust to weight ratio up to level of 15[J].Aeroengine,2010,36(1):57-62(in Chinese).
    [3]
    林宇震,林阳,张弛,等.先进燃烧室中心分级燃烧空气流量分配的探讨[J].航空动力学报, 2010,25(9):1923-1930.LIN Y Z, LIN Y, ZHANG C,et al.Discussion on combustion airflow distribution of advanced staged combustor[J].Journal of Aerospace Power,2010,25(9):1923-1930(in Chinese).
    [4]
    李继保,胡正义.高温升高热容燃烧室设计技术分析[J].燃气涡轮试验与研究,2000,13(4):5-8.LI J B, HU Z Y.Design technology analysis of high temperature rise and high volumetric heat combustor[J].Gas Turbine Experiment and Research,2000,13(4):5-8(in Chinese).
    [5]
    MONGIA H C,AI-ROUB M,DANIS A,et al.Swirl cup modeling Part I :AIAA-2001-3576[R].Reston:AIAA,2001.
    [6]
    彭云辉,林宇震,许全宏,等.双旋流空气雾化喷嘴喷雾、流动和燃烧性能[J].航空学报,2008,29(1):1-14.PENG Y H,LIN Y Z,XU Q H,et al.Atomization, aerodynamics and combustion performance of swirl cup[J].Acta Aeronautica et Astronautica Sinica,2008,29(1):1-14(in Chinese).
    [7]
    WANG H R,MCDONELL V G,SAMUELSEN G S.Influence of hardware design on the flow field structures and the patterns of droplet dispersion Part I:Mean quantities[J].Journal of Engineering for Gas Turbine and Power,1995,117(2):286-292.
    [8]
    LANG H J,HUANG R,GUO Z H.The flow fields in a model combustor with primary holes after different swirl cups:ASME GT 2006-90489[R].New York:ASME,2006.
    [9]
    ATESHKADI A, MCDONELL V G,SAMUELSEN G S.Effect of mixer geometry on fuel spray distribution,emissions and stability:AIAA-1998-0247[R].Reston:AIAA,1998.
    [10]
    袁怡祥,林宇震,刘高恩,等.燃油周向分级对贫油熄火油气比的影响[J].航空动力学报,2003,18(5):639-644.YUAN Y X,LIN Y Z,LIU G N,et al.The effect of fuel-circumferential-staging on lean blowout limit at idle condition[J].Journal of Aerospace Power,2003,18(5):639-644(in Chinese).
    [11]
    MEHTA J M,SHIN H W,WISLER D C.Mean velocity and turbulent flow field characteristics inside an advanced combustor swirl cup:AIAA-1989-0215[R].Reston:AIAA,1989.
    [12]
    张雪琴,黄勇.某旋流杯环形燃烧室三维湍流流动的数值模拟[C]//中国航空学会第六届动力年会2006.北京:中国航空学会,2006:236-245.ZHANG X Q,HUANG Y.Numerical simulation of three-dimensional flow and combustor in an annular gas turbine[C]//Chinese Society of Aeronautics and Astronautics 6th Annual Meeting 2006.Beijing:Chinese Society of Aeronautics and Astronatutics,2006:236-245(in Chinese).
    [13]
    党新宪,赵坚行,徐榕,等.试验研究旋流数对燃烧室气动性能的影响[J].航空动力学报, 2011,26(1):21-27.DANG X X,ZHAO J X,XU R,et al.Experimental investigation on effects of swirl number on aerodynamic characteristics of combustor[J].Journal of Aerospace Power,2011,26(1):21-27(in Chinese).
    [14]
    ROSFJORD T J,RUSSELL S.Nozzle design and manufacturing influences on fuel spray circumferential uniformity[J].Journal of Propulsion and Power,1989,5(2):144-150.
    [15]
    ROSFJORD T J,ECKERLE W A.Aerating fuel nozzle design influence on airflow features[J].Journal of Propulsion and Power,1991,7(6):849-856.
    [16]
    COHEN J M,ROSFJORD T J.Influences on the sprays formed by high-shear fuel nozzle/swirler assemblies[J].Journal of Propulsion and Power,1993,9(1):16-27.
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