Volume 32 Issue 6
Jun.  2017
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2017  >  32(6): 1321-1327
Modeled experiment on overall cooling effectiveness of effusion holes in front of outer liner of annular slinger combustor[J]. Journal of Aerospace Power, 2017, 32(6): 1321-1327. doi: 10.13224/j.cnki.jasp.2017.06.006
Citation: Modeled experiment on overall cooling effectiveness of effusion holes in front of outer liner of annular slinger combustor[J]. Journal of Aerospace Power, 2017, 32(6): 1321-1327. doi: 10.13224/j.cnki.jasp.2017.06.006
shu

Modeled experiment on overall cooling effectiveness of effusion holes in front of outer liner of annular slinger combustor

doi: 10.13224/j.cnki.jasp.2017.06.006
  • Received Date: 2015-06-14
  • Publish Date: 2017-06-28
    Abstract
  • An experimental model for simulating the local primary flow field near the front of outer liner of annular slinger combustor was designed to study the effusion cooling performance. The surface temperature distribution on the perforated plate was measured by the infrared camera, and the effects of blowing ratio, effusion holes-array arrangement, hole diameter and perforated percentage on the overall cooling effectiveness were then compared. Three effusion holes-array arrangements including square-diamond mode, long-diamond mode and super-long-diamond mode were adopted. The hole diameter varied from 0.6mm to 1.0mm, the perforated percentage varied from 3% to 6% and the blowing ratio varied from 1 to 6. The results show that the overall cooling effectiveness increases firstly along the streamwise direction and then decreases downstream due to the existence of recirculation zone in the front of outer liner. The blowing ratio of 2 results in the highest overall cooling effectiveness and the long-diamond holes-array arrangement seems to be advantageous. The decrease of hole diameter is helpful for improving the overall cooling effectiveness under the same perforated percentage. When the perforated percentage increases from 3% to 4.8%, the overall cooling effectiveness is significantly enhanced.

     

    • FullText(HTML)
  • loading
    • References(24)
  • [1]
    KREWINKEL R.A review of gas turbine effusion cooling studies［J］.International Journal of Heat and Mass Transfer,2013,66:706-722.
    [2]
    LEGER B,MIRON P,EMIDIO J M.Geometric and aero-thermal influences on multiholed plate temperature:application on combustor wall［J］.International Journal of Heat and Mass Transfer,2003,46(7):1215-1222.
    [3]
    ANDREINI A,BONINI A,CACIOLLI G,et al.Numerical study of aerodynamic losses of effusion cooling holes in aero-engine combustor liners［R］.ASME Paper GT2010-22942,2010.
    [4]
    SCRITTORE J J,THOLE K A,BURD S W.Investigation of velocity profiles for effusion cooling of a combustor liner［J］.Journal of Turbomachinery,2007,129(3):518-526.
    [5]
    BOHN D,MORITZ N.Influence of hole shaping of staggered multi-hole configurations on cooling film development［R］.AIAA-2000-2579,2000.
    [6]
    FACCHIRI L,TARCHI L,TORI L,et al.Investigation of circular and shaped effusion cooling arrays for combustor liner application:Part 1 experiment analysis［R］.ASME Paper GT2009-60037,2009.
    [7]
    HARRINGTON M K,MCWATERS M A,BOGARD D G,et al.Full-coverage film cooling with short normal injection holes［J］.Journal of Turbomachinery,2001,123(4):798-805.
    [8]
    ZHANG Chi,LIN Yuzhen,XU Quanhong,et al.Cooling effectiveness of effusion walls with deflection hole angles measured by infrared imaging［J］.Applied Thermal Engineering,2009,29(5-6):966-972.
    [9]
    杨成凤,张靖周,杨卫华.全覆盖气膜孔阵列方式对冷却特性的影响［J］.航空动力学报,2010,25(7):1524-1529.YANG Chengfeng,ZHANG Jingzhou,YANG Weihua.Effect of the holes array arrangement on the full coverage film cooling characteristics［J］.Journal of Aerospace Power,2010,25(7):1524-1529.(in Chinese)
    [10]
    YANG Chengfang,ZHANG Jingzhou.Influence of multi-hole arrangement on cooling film development［J］.Chinese Journal of Aeronautics,2012,25(2):182-188.
    [11]
    LIGRANI P,GOODRO M,FOX M,et al.Full-coverage film cooling:film effectiveness and heat transfer coefficients for dense and sparse hole arrays at different blowing ratios［J］.Journal of Turbomachinery,2012,134(6):061039.1-061039.13.
    [12]
    ZHANG Jingzhou,XIE Hao,YANG Chengfeng.Numerical study on of flow and heat transfer of impingement-effusion cooling［J］.Chinese Journal of Aeronautics,2009,22(4):343-348.
    [13]
    JUNG E Y,LEE D H,OH S H,et al.Total cooling effectiveness on a staggered full-coverage film cooling plate with impinging jet［R］.ASME Paper GT2010-23725,2010.
    [14]
    杨谦,林宇震,张弛,等.发散冷却与冲击/发散冷却的冷却效率对比［J］.航空动力学报,2014,29(2):268-275.YANG Qian,LIN Yuzhen,ZHANG Chi,et al.Cooling effectiveness comparison between effusion cooling and impingement/effusion cooling［J］.Journal of Aerospace Power,2014,29(2):268-275.(in Chinese)
    [15]
    刘友宏,李英,杨旭.冲击/发散冷却层板隔热屏冷却性能及对比［J］.航空动力学报,2014,29(6):1272-1278.LIU Youhong,LI Ying,YANG Xu.Cooling performance and comparison of impingement/effusion cooling lamilloy used as heat shiel卤挻楊攽渮捊敯??の????????????ち?e Power,2014,29(6):1272-1278.(in Chinese)
    [16]
    赵梦梦,张驰,林宇震,等.弯曲多孔壁不同倾斜角气膜孔整体气膜冷却效率研究［J］.航空动力学报,2007,22(2):210-215.ZHAO Mengmeng,ZHANG Chi,LIN Yuzhen,et al.Study of overall cooling effectiveness of discrete holes with different angles to concave wall［J］.Journal of Aerospace Power,2007,22(2):210-215.(in Chinese)
    [17]
    罗国良,杨卫华,曹俊,等.弯曲段壁面冲击发散冷却结构流量系数与冷却效率的实验［J］.航空动力学报,2011,26(8):1688-1694.LUO Guoliang,YANG Weihua,CAO Jun,et al.Experimental study of discharge coefficient and cooling effectiveness for impingement effusion cooling in curved section［J］.Journal of Aerospace Power,2011,26(8):1688-1694.(in Chinese)
    [18]
    王倚阳,宋双文,陈延庚.某折流燃烧室火焰筒壁温试验［J］.航空动力学报,2011,26(11):2480-2484.WANG Yiyang,SONG Shuangwen,CHEN Yangeng.Experiment on the liner wall temperature of a slinger combustor［J］.Journal of Aerospace Power,2011,26(11):2480-2484.(in Chinese)
    [19]
    TARCHI L,FACCHINI B,MAIUOLO F,et al.Experimental investigation on the effects of a large recirculating area on the performance of an effusion cooled combustor liner［J］.Journal of Engineering for Gas Turbines and Power,2012,134(4):041505.1-041505.9.
    [20]
    CHOI S,LEE D,PARK J.Ignition and combustion characteristics of the gas turbine slinger combustor［J］.Journal of Mechanical Science and Technology,2008,22(3):538-544.
    [21]
    LEE S,PARK S H,LEE D.Numerical simulation of slinger combustor using 2-D axisymmetric computational model［J］.AIP Conference Proceedings,2010,1225(1):941-951.
    [22]
    颜应文,宋双文,胡好生,等.折流燃烧室两相喷雾燃烧流场数值模拟［J］.航空动力学报,2011,26(5):1003-1010.YAN Yingwen,SONG Shuangwen,HU Haosheng,et al.Numerical investigations of two-phase spray combustion flow fields in slinger annular combustor［J］.Journal of Aerospace Power,2011,26(5):1003-1010.(in Chinese)
    [23]
    CARLOMAGNO G M,CARDONE G.Infrared thermography for convective heat transfer measurements［J］.Experiments in Fluids,2010,49(6):1187-1218.
    [24]
    YANG Chengfang,ZHANG Jingzhou.Experimental investigation on film cooling characteristics from a row of holes with ridge-shaped tabs［J］.Experimental Thermal and Fluid
    • 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(987.0KB)
    XML

    Article Metrics

    Article views (1157) PDF downloads(453) 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