不同缝槽进气孔间距的纯气膜绝热温比试验研究

张弛; 许全宏; 林宇震

不同缝槽进气孔间距的纯气膜绝热温比试验研究

北京航空航天大学航空航天大学能源与动力工程学院航空发动机气动热力重点实验室, 北京 100083

计量
- 文章访问数: 1334
- HTML浏览量: 2
- PDF量: 448
- 被引次数: 0
出版历程
- 收稿日期: 2005-06-22
- 修回日期: 2005-09-10
- 刊出日期: 2006-06-28

Experimental Investigation on the Film-Cooling Adiabatic Effectiveness with Different Slot Inlet Hole Pitches

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 通过传热试验法对不同缝槽进气孔间距的纯气膜冷却效率进行研究。研究所用气膜缝槽结构无收缩,进气孔与舌片垂直。试验中主流湍流强度在10%以上,测量气膜绝热壁温以确定其重要冷却效率描述参数——绝热温比。试验结果表明:缝槽进气孔间距对气膜冷却效率影响很大,减小进气孔间距,可以减小缝槽几何特征参数MIX_N,明显提高气膜的绝热温比。
- 航空、航天推进系统 /
- 航空发动机 /
- 燃烧室 /
- 气膜冷却 /
- 绝热温比 /
- 缝槽几何特征参数
Abstract: The film-cooling adiabatic effectiveness was investigated by the heat-transfer experimental method with different pitch between inlet holes of the slot film.The adiabatic wall temperature was measured to calculate the important parameter for film-cooling effectiveness,defined as adiabatic effectiveness.The slot film configurations featured no convergence and inlet holes perpendicular to slot lip.The main stream turbulent level was higher than 10% in all experiments.The experimental results indicate that the pitch between inlet holes plays important role in film-cooling effectiveness.The adiabatic film-cooling effectiveness increases with the decrease of the pitch between the inlet holes and the slot geometric parameter MIX_N.
- aerospace propulsion system /
- aircraft engine /
- combustion chamber /
- film cooling /
- film-cooling adiabatic effectiveness /
- slot geometric parameter

HTML

参考文献(9)

[1]	Sturgess G J.Design of Combustor Cooling Slots for High Film Effectiveness:Part Ⅰ-Film General Development[J].Transactions of the ASME,Journal of Engineering for Gas Turbine and Power,1986,108:354～ 360.
[2]	Sturgess G J,Pfeifer G D.Design of Combustor Cooling Slots for High Film Effectiveness:Part Ⅱ -Film Initial Region[J].Transactions of the AS M E,Journal of Engineering for Gas Turbine and Power,1986,108:361～369.
[3]	Li S C,Mongia H C.An Improved Method for Correlation of Film-Cooling Effectiveness of Gas Turbine Combustor Liners[R].AIAA Paper 2001-3268,2001.
[4]	Mongia H C,Kumar G N.Validation of An Advanced Turbulence Model with DoE Film-Effectiveness Test Data on a Machined Ring Liner[R].AIAA Paper 2001-3269,2001.
[5]	Kumar G N,Duncan B S,Mongia H C.Results of a DOE on the Film-Cooling Effectiveness of a Modern Combustor with Machined Ring Liners[R].AIAA Paper 2000-3354,2000.
[6]	赵强,刘庆国.火焰筒壁气膜冷却效果试验研究[J].航空发动机,1999,(3):51～56.Zhao Qiang,Liu Qinguo.An Experimental Investigation of Film-Cooling Effectiveness of Combustor Liners[J].Aeroengine,1999,(3):51 ～ 56.
[7]	Hyung Hee Cho,Jin Ki Ham.Influence of Injection Type and Feed Arrangement on Flow and Heat Transfer in an Injection Slot[R].2000-GT-0238,ASME Turbo Expo 2000.
[8]	James E Mayhew,James W Baughn,Aaron R Byerley.The Effect of Freestream Turbulence on Film Cooling Adiabatic Effectiveness[R].GT-2002-30172,ASME Turbo Expo 2002.
[9]	Lefebvre A H.Weak Extinction Limits of Turbulence Heterogeneous Fuel/Air Mixtures[J].Transactions of ASME,Journal of Engineering for Power,1980,102:416～421.