出口侧向扩张孔流量系数试验

万卜铭; 曹俊; 黎超超; 陈江

doi:10.13224/j.cnki.jasp.20200548

出口侧向扩张孔流量系数试验

doi: 10.13224/j.cnki.jasp.20200548

中国航空发动机集团有限公司湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
万卜铭（1993-），男，工程师，硕士生，主要从事航空发动机燃烧室冷却相关研究。

中图分类号: V231.1
计量
- 文章访问数: 99
- HTML浏览量: 6
- PDF量: 108
- 被引次数: 0
出版历程
- 收稿日期: 2020-12-23
- 刊出日期: 2021-11-28

Experiment on discharge coefficients for outlet lateral dilated hole

Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要: 采用试验研究的方法，探讨了不同结构参数出口侧向扩张孔的流量系数在不同工况下的变化规律。通过试验研究发现：出口侧向扩张孔圆柱段孔径为0.6 mm时的流量系数比孔径为0.8 mm时大3%；当孔倾角由30°减小至25°时，流量系数随之增大，当倾角继续减小至20°时，流量系数不变；当扩张角由20°增大至40°时，流量系数先增大后减小，且在扩张角为25°时最大；流量系数与次流通道雷诺数成正比，雷诺数越大，流量系数达到极限值所需的压降系数越小，且当压降系数大于0.9后，不同次流雷诺数下的流量系数差别在2%左右。
- 燃烧室 /
- 出口侧向扩张孔 /
- 流量系数 /
- 扩张角 /
- 压降系数
Abstract: The experimental study on the discharge coefficient of outlet lateral dilated hole was conducted to investigate the trend of discharge coefficients with different structure parameters and aerodynamic parameters.Research showed that the diacharge coefficient of outlet lateral dilated hole cylindrical segment diameter 0.6 mm 3% larger than 0.8 mm.When the hole inclination angle was reduced from 30° to 25°，the discharge coefficient increased，and when the inclination decreased to 20°，the discharge coefficient remains unchanged.When the expansion angle grew from 20° to 40°，the discharge coefficient increased first and then decreased，and reached the maximum value when the expansion angle was 25°.Meanwhile the discharge coefficient was proportional to the secondary flow Reynolds number，and the larger secondary flow Reynolds number indicated the smaller pressure drop needed to reach the limit coefficient value.When the preesure drop was greater than 0.9，the difference of the discharge coefficient at different secondary flow Reynolds number was about 2%.
- combustor /
- outlet lateral dilated hole /
- discharge coefficient /
- expansion angle /
- pressure drop coefficient

HTML

参考文献(18)

[1]	朱惠人,许都纯,刘松龄,等.气膜孔形状对流量系数影响的实验研究[J].推进技术,1998,19（1）:42-45.
[2]	GRITSCH M,SCHULZ A,WITTIG S.Discharge coefficient measurements of film-cooling holes with expanded exits[J].Journal of Turbomachinery,1997,120（3）:557-563.
[3]	谢婕,张靖周.带偏转角气膜出流发散壁冷却特性的数值分析[J].南京航空航天大学学报,2013，45（2）:157-161.
[4]	杨彬,徐国强,丁水汀,等.旋转状态下气膜冷却特性的数值研究[J].航空学报,2008,29（2）:274-279.
[5]	GRITSCH M,SCHULZ A,WITTIG S.Adiabatic wall effectiveness measurements of film-cooling holes with expanded exits[R].ASME Paper 97-GT-164,1997.
[6]	杨卫华,马国锋,张靖周,等.气膜冷却孔几何结构对流量系数的影响[J].推进技术,2005,26（5）:413-416.
[7]	FORGHAN F.Discharge coefficient of diffusion holes[R].AAIA-95-3622,1995.
[8]	AN B T,LIU J J .Numerical investigation on diffusion slot hole with various cross-sectional end shapes[J].Journal of Heat Transfer,2017,139:091703.1-091703.13.
[9]	SAVARY N,AUPOIX T,DUCHAINE P,et al.Effusion cooling 3D simulations to establish a discharge coefficient correlation[R].ASME Paper GT2017-64264,2017.
[10]	张魏，李广超，彭大维，等.旋转对带斜肋和双排孔通道孔流量系数影响[J].航空动力学报,2010,25（6）:1258-1263.
[11]	李广超,朱惠人,樊慧明.角度和孔间距对双向扩张型孔流量系数影响的实验[J].航空动力学报,2009,24（3）:499-506.
[12]	宋新伟,毛军逵，屠泽灿,等.双层壳型冲击/气膜综合流量系数实验研究[J].推进技术,2012,33（6）:875-880.
[13]	向安定,朱惠人,刘松龄，等.涡轮导向叶片表面气膜孔流量系数的实验研究[J].推进技术,2003,24（3）:216-219,239.
[14]	方韧，林宇震，李彬，等.燃烧室多斜孔壁流量系数研究[J].航空动力学报，1998,13（1）:61-64.
[15]	曹宗华,何跃龙.具有复合角的多斜孔板流量系数研究[J].燃气涡轮试验与研究,2011,24（4）:28-31.
[16]	陈江,宋双文,陈剑.逆向进气复合角发散冷却孔流量系数试验[J].航空动力学报,2019,34（1）:45-50.
[17]	彭中九.一种测量火焰筒进气孔流量系数的试验装置及方法：CN107036665A[P].2017-08-11.
[18]	黄开明,黄金泉,任丹，等.涡轴发动机性能参数的等效换算[J].航空动力学报,2010,25（9）:2036-2040.