航天推进技术研究院主办
[1]丁旭,吴传伟,刘涛,等.涡轮叶片U型冷却通道旋转流动特性模拟[J].火箭推进,2022,48(03):50-56.
DING Xu,WU Chuanwei,LIU Tao,et al.Simulation of rotating flow characteristics in U-shaped cooling channel of turbine blade[J].Journal of Rocket Propulsion,2022,48(03):50-56.
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DING Xu,WU Chuanwei,LIU Tao,et al.Simulation of rotating flow characteristics in U-shaped cooling channel of turbine blade[J].Journal of Rocket Propulsion,2022,48(03):50-56.
涡轮叶片U型冷却通道旋转流动特性模拟
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年03期
页码:
50-56
栏目:
研究与设计
出版日期:
2022-06-22
- Title:
- Simulation of rotating flow characteristics in U-shaped cooling channel of turbine blade
- 文章编号:
- 1672-9374(2022)03-0050-07
- 分类号:
- V235.21
- 文献标志码:
- A
- 摘要:
- 为了研究发动机涡轮叶片U型通道在旋转条件下的流动特性,采用 Fluent 中双精度速度压力耦合求解器的简单算法,湍流模型采用k-ω SST模型,压力动量项和密度项用二阶迎风差分格式数值计算,能量项用快速格式计算,建立了旋转条件下涡轮叶片U型通道内的数值模拟方法,分析对比了静止条件下和旋转条件下U型通道内的流动特性。结果表明,相对于静止条件,旋转使得U型通道内液体的流动更加复杂,二次流现象更加严重,湍流程度加剧,换热加强,在科氏力作用下径向出流和径向入流呈相反的流动,在横管段由于旋转和迪恩涡双层作用,换热效果最强。
- Abstract:
- In order to study the flow characteristics in U-channel of engine turbine blade under rotating condition, a numerical simulation method for U-channel of turbine blade under rotating condition is established by fluent.In the simulation with fluent, the simple algorithm of the double-precision velocity-pressure coupled solver is used, the k-ω SST model is used for the turbulence model, the second-order upwind difference scheme is used for the pressure momentum term and density term, the fast scheme is used for the calculation of energy term.The flow characteristics in U-channel under the static condition and the rotating condition are analyzed and compared.The results show that compared with the static condition, rotation makes the flow of liquid in the U-shaped channel more complicated and the secondary flow more serious, the degree of turbulence intensifies and the heart transfer is enhanced.Under the action of Coriolis force, the radial outflow and the radial inflow flow are opposite.In the horizontal pipe section, the heat transfer effect is the strongest due to the combined effect of rotation and Dean Vortex.
参考文献/References:
[1] 郭琦.TBCC用涡轮发动机技术的发展[J].燃气涡轮试验与研究,2013,26(6):15-20.
[2] 曹玉璋.航空发动机传热学[M].北京:北京航空航天大学出版社,2005.
[3] 刘维.管道网络法在涡轮叶片传热设计中的应用研究[D].哈尔滨:哈尔滨工业大学,2014.
[4] BUNKER R S.A review of shaped hole turbine film-cooling technology[J].Journal of Heat Transfer,2005,127(4):441-453.
[5] MAZAHERI K,ZEINALPOUR M,BOKAEI H R.Turbine blade cooling passages optimization using reduced conjugate heat transfer methodology[J].Applied Thermal Engineering,2016,103:1228-1236.
[6] 张洪.燃气透平叶片冷却通道及叶顶间隙流动和换热研究[D].合肥:中国科学技术大学,2012.
[7] 秦江,孙红闯,白新阳,等.油冷涡轮动叶方案中旋转冷却效应分析[J].推进技术,2017,38(2):399-407.
[8] 于文力.超临界压力下正癸烷对流换热实验研究[D].哈尔滨:哈尔滨工业大学,2014.
[9] 吴传伟.U型旋转通道内碳氢燃料的换热特性研究[D].哈尔滨:哈尔滨工业大学,2018.
[10] 李国强.超临界流体旋转传热试验台研发[D].杭州:浙江大学,2016.
[11] 丁旭.正癸烷高温燃烧特性实验与数值模拟研究[D].哈尔滨:哈尔滨工业大学,2017.
[12] 蒋劲.超燃冲压发动机燃烧室再生冷却研究[D].西安:西北工业大学,2006.
[13] 陈华军.旋转曲线管道内流动结构与换热特性研究[D].杭州:浙江大学,2003.
[14] 客进友.Cross流体在圆管和环空内流动流场的摄动解[J].石油大学学报(自然科学版),1991,15(2):132-138.
[15] KALPAKLI VESTER A,?L?R,ALFREDSSON P H.Turbulent flows in curved pipes:recent advances in experiments and simulations[J].Applied Mechanics Reviews,2016,68(5):0508025.
[16] LIOU T M,CHEN C C.LDV study of developing flows through a smooth duct with a 180 deg straight-corner turn[J].Journal of Turbomachinery,1999,121(1):167-174.
[17] JOHNSON B V,WAGNER J H,STEUBER G D,et al.Heat transfer in rotating serpentine passages with trips skewed to the flow[C]//ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition.New York:ASME,1992.
[18] JOHNSON B V,WAGNER J H.Heat transfer experiments in the internal cooling passages of a cooled radial turbine rotor[EB/OL].https://www.researchgate.net/publication/24325197_Heat_Transfer_Experiments_in_the_Internal_Cooling_Passages_of_a_Cooled_Radial_Turbine_Rotor,1996.
[19] YOU R Q,LI H W,TAO Z.Experimental investigation on two-dimensional heat transfer and secondary flow in a rotating smooth channel[J].International Journal of Heat and Mass Transfer,2017,113:342-353.
备注/Memo
收稿日期:2020-08-31 修回日期:2021-03-13
基金项目:国家自然科学基金(91741204)
作者简介:丁旭(1993—),男,硕士,工程师,研究领域为航空发动机鉴定试飞及整机地面试验技术。
更新日期/Last Update:
1900-01-01