发散孔结构参数对横向波纹表面气膜绝热冷却效率的影响

渠立红; 张靖周; 谭晓茗

doi:10.13224/j.cnki.jasp.2018.03.010

发散孔结构参数对横向波纹表面气膜绝热冷却效率的影响

doi: 10.13224/j.cnki.jasp.2018.03.010

1.
南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京 210016
2.
南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京 210016；先进航空发动机协同创新中心,北京 100191

基金项目: 国家自然科学基金（U1508212）；航空科学基金（2015ZB52019）

计量
- 文章访问数: 1299
- HTML浏览量: 228
- PDF量: 756
- 被引次数: 0
出版历程
- 收稿日期: 2016-07-21
- 刊出日期: 2018-03-28

Effects of structural parameters of effusion holes on adiabatic film cooling effectiveness over transverse corrugated surface

摘要

摘要: 针对加力燃烧室特定横向波纹结构的隔热屏发散冷却进行数值模拟,主要研究发散孔孔节距、孔径以及开孔率等3个结构参数对发散冷却效率的影响。结果表明：由于处于波纹波谷的相邻气膜射流更易于形成相干,从而在波谷形成更强的集聚效应,造成波谷附近的绝热壁面温度低于波峰区域；在相同的壁面单位面积冷气用量下,减小孔径、增大开孔率均显著改善气膜冷却效率,尤其是在发散气膜的前排起始段；发散孔流向节距大于展向节距的长菱形排布相对较优,但在小吹风比下发散孔排布节距比对展向平均绝热冷却效率的影响非常微弱。
- 横向波纹 /
- 隔热屏 /
- 发散冷却 /
- 结构参数 /
- 气膜冷却效率
Abstract: Numerical simulation was carried out to study the effusion cooling on a specific transverse corrugated heat-shield used in aero-engine afterburner. Three main geometric parameters, including spanwise-to-streamwise pitch ratio, hole diameter and perforated percentage, were taken into consideration. Result showed that, in the wavy valley of transverse corrugated surface, the coolant jets ejected from adjacent holes were prone to interact each other, thus forming more coolant accumulation. Due to this feature, the adiabatic wall temperature on the wavy valley of transverse corrugated surface was relatively lower than that on the wavy peak. In general, reducing the hole diameter and enlarging the perforated percentage were illustrated to be significantly helpful to enhance the film cooling effectiveness under the same coolant usage for a given protected area, especially in the front developing zone of an effusion cooling scheme. Besides, the effusion holes arranged in a super-long-diamond mode where the streamwise hole-to-hole pitch was bigger than spanwise hole-to-hole pitch showed more favorable. However, the effect of spanwise-to-streamwise pitch ratio on the laterally-averaged adiabatic film cooling effectiveness was very weak at low blowing ratio.
- transverse corrugated /
- heat shield /
- effusion cooling /
- structural parameter /
- film cooling effectiveness

HTML

参考文献(20)

[1]	CERRI G,GIOVANNELLI A,BATTISTI L,et al.Advances in effusive cooling techniques of gas turbines［J］.Applied Thermal Engineering,2007,27(4):692-698.
[2]	LEGER B,MIRON P,EMIDIO J M.Geometric and aero-thermal influences on multi-holed plate temperature:application on combustor wall［J］.International Journal of Heat and Mass Transfer,2003,46(7):1215-1222.
[3]	林宇震,宋波,李彬,等.不同倾斜角多斜孔壁冷却方式绝热温比研究［J］.航空学报,1999,20(3):201-204.LIN Yuzhen,SONG Bo,LI Bin,et al.Investigation of adiabatic wall effectiveness of the inclined multihole wall film cooling with different angles to the wall surface［J］.Acta Aeronautica et Astronautica Sinica,1999,20(3):201-204.(in Chinese)
[4]	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.
[5]	ZHANG C,SONG B,LIN Y Z,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.
[6]	BOHN D,MORITZ N.Influence of hole shaping of staggered multi-hole configurations on cooling film development［R］.AIAA-2000-2579,2000.
[7]	丁阳,常海萍,杜治能.具有相反横向射流角的全覆盖气膜孔冷却特性［J］.航空动力学报,2014,29(3):511-518.DING Yang,CHANG Haiping,DU Zhineng.Cooling characteristics of full coverage film holes with opposite lateral ejection angle［J］.Journal of Aerospace Power,2014,29(3):511-518.(in Chinese)
[8]	PETRE B,DORIGNAC E,VULLIERME J J.Study of influence of the number of holes rows on the convective heat transfer in the case of full coverage film cooling［J］.International Journal of Heat and Mass Transfer,2003,46(18):3477-3496.
[9]	YANG C F,ZHANG J Z.Influence of multi-holes arrangement on cooling film development［J］.Chinese Journal of Aeronautics,2012,25(2):182-188.
[10]	LIN Y Z,SONG B,LI B,et al.Investigation of film cooling effectiveness of full-coverage inclined multihole walls with different hole arrangements［R］.ASME Paper GT2003-38881,2003.
[11]	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)
[12]	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.
[13]	SHINBO K,KOIDE Y,KASHIWAGI T,et al.Research of heat transfer of a liner for an afierburner［R］.AIAA 97-3005,1997.
[14]	FUNAZAKI K,IGARASHI T,KOIDE Y,et al.Studies on cooling air ejected over a corrugated wall:its aerodynamic behavior and film effectiveness［R］.ASME Paper 2001-GT-143,2001.
[15]	唐婵,常海萍,毛军逵.离散孔纵向波纹隔热屏气膜冷却特性研究［J］.工程热物理学报,2007,28(3):487-489.TANG Chan,CHANG Haiping,MAO Junkui.Numerical simulation of discrete holes on the longitudinal ripple wavy liner［J］.Journal of Engineering Thermophysics,2007,28(3):487-489.(in Chinese)
[16]	唐婵,常海萍.发散孔纵向波纹隔热屏气膜冷却特性［J］.航空动力学报,2009,22(1):37-41.TANG Chan,CHANG Haiping.Numerical simulation of effusion holes on the longitudinal ripple heat shield［J］.Journal of Aerospace Power,2009,22(1):37-41.(in Chinese)
[17]	常国强,常海萍,常飞,等.多孔纵向波纹表面气膜冷却效率实验研究［J］.航空动力学报,2009,24(3):513-518.CHANG Guoqiang,CHANG Haiping,CHANG Fei,et al.Experimental investigation on film cooling effectiveness of multi-hole at longitudinal wavy surface［J］.Journal of Aerospace Power,2009,24(3):513-518.(in Chinese)
[18]	HARRISON K,BOGARD D.Comparison of RANS turbulence models for prediction of film cooling performance［R］.ASME Paper GT2008-50366,2008.
[19]	SILIETI M,KASSAB A J,DIVO E.Film cooling effectiveness:comparison of adiabatic and conjugate heat transfer CFD models［J］.International Journal of Thermal Science,2009,48(12):2237-2248.
[20]	YAO Y,ZHANG J Z,TAN X M.Numerical study of film cooling from converging slot-hole on a gas turbine blade suction side［J］.International Communications in Heat and Mass Transfer,2014,52(2):61-72.