径向预旋系统温降与流阻特性的数值研究

张建超; 王锁芳

径向预旋系统温降与流阻特性的数值研究

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2012-09-29
- 刊出日期: 2013-10-28

Numerical study on characteristics of temperature reduction and flow loss in radial pre-swirl system

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 为了探索“预旋降温效应”在航空发动机中应用的新形式,研究径向预旋结构的温降和流阻特性,对径向预旋系统结构的简化模型进行了数值模拟,通过实验验证了数值方法,分析模型内部的流动结构,获得旋转雷诺数和无量纲质量流量对径向预旋系统温降和流阻特性的影响规律.结果表明:数值计算得到的结果与实验值趋势一致,最大相对误差不超过20%.计算的参数范围内,当流经径向预旋系统的冷气质量流量一定时,气流温降和压降均随旋转雷诺数的增大而降低;当径向预旋系统工作的旋转雷诺数一定时,气流温降和压降均随无量纲质量流量的增大而增加.
- 径向预旋 /
- 转静系 /
- 流阻 /
- 温降 /
- 旋流比
Abstract: To explore new method of structure design based on‘preswirl temperature-reduction effect’in preswirl system of aero-engine,the characteristics of temperature reduction and flow losses in radial pre-swirl system were studied,and numerical investigation was carried out on a simplified radial pre-swirl system.Numerical method was validated by experimental results;flow structure in the radial pre-swirl system was analyzed.Characteristics of temperature reduction and pressure losses were investigated with changes of rotational Reynolds number and non-dimensioned mass flow rate.The computational results show that:the numerical results coincide with the experimental results,and relative error is not more than 20%,proving that the reliability of CFD method;under certain conditions of the study,at the given non-dimensional mass flow rate,the temperature reduction and pressure losses of radial pre-swirl system decrease as the rotating Reynolds number increases;with the given rotational Reynolds number,the temperature reduction and pressure losses increase as the non-dimensional mass flow rate increases.
- radial pre-swirl /
- rotor-stator system /
- flow loss /
- temperature reduction /
- swirl ratio

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参考文献(15)

[1]	Geis T,Dittmann M,Dullenkopf K.Cooling air temperature reduction in a direct transfer preswirl system[J].Journal of Engineering for Gas Turbines and Power,2004,126(4):809-815.
[2]	Dittmann M,Geis T,Schramm V,et al.Discharge coefficients of a pre-swirl system in secondary air systems [EB/OL].[2012-09-15].http:[C]//cat.inist.fr/?aModele=afficheN&cpsidt=13502734.
[3]	Dittmann M,Dullenkopf K,Wittig S.Direct-transfer pre-swirl system:a one-dimensional modular characterization of the flow [EB/OL].[2012-09-15].http:[C]//cat.inist.fr/?aModele=afficheN&cpsidt=16846559.
[4]	Chew J W,Hills N J,Ciampoli F,et al.Pre-swirled cooling air delivery system performance [C]//Proceedings of ASME Turbo Expo 2008:Power for Land,Sea and Air.Reno-Tahoe,NV,United States:American Society of Mechanical Engineers,2005:1129-1137.
[5]	Karabay H,Chen J X,Pilbrow R,et al.Flow in a ‘cover-plate’ preswirl rotor-stator system[J].Journal of Turbomachinery,1999,121(1):160-166.
[6]	Lewis P,Wilson M,Lock G,et al.Physical interpretation of flow and heat transfer in preswirl systems[J].Journal of Engineering for Gas Turbines and Power,2007,129(3):769-777.
[7]	Lewis P,Wilson M,Lock G D,et al.Effect of radial location of nozzles on performance of preswirl systems:a computational and theoretical study[J].Journal of Power and Energy,2009,223(2):179-190.
[8]	Ciampoli F,Hills N J,Chew J W,et al.Unsteady numerical simulation of the flow in a direct transfer pre-swirl system [C]//Proceedings of ASME Turbo Expo 2008:Power for Land,Sea and Air.Berlin,Germany:ASME,2008:1647-1655.
[9]	王锁芳,朱强华,张羽,等.预旋进气位置对转静盘腔换热影响的数值研究[J].航空动力学报,2007,22(8):1227-1232. WANG Suofang,ZHU Qianghua,ZHANG Yu,et al.Numerical studies of heat transfer in a rotor-stator cavity with different radial positions of pre-swirl inlet[J].Journal of Aerospace Power,2007,22(8):1227-1232.(in Chinese)
[10]	何振威,冯青,刘松龄,等.带盖板预旋进气系统的温降实验误差分析[J].科学技术与工程,2010,10(26):6439-6444. HE Zhenwei,FENG Qing,LIU Songling,et al.The error analysis of an experiment about drop in temperature in a pre-swirl system with a cover-plate[J].Science Technology and Engineering,2010,10(26):6439-6444.(in Chinese)
[11]	朱晓华,刘高文,刘松龄,等.带盖板的预旋系统温降和压力损失数值研究[J].航空动力学报,2010,25(11):2498-2506. ZHU Xiaohua,LIU Gaowen,LIU Songling,et al.Numerical studies of temperature drop and pressure loss in a cover-plate preswirl system[J].Journal of Aerospace Power,2010,25(11):2498-2506.(in Chinese)
[12]	罗翔,徐国强,陶智,等.进气角度对旋转盘冷却效果的影响[J].推进技术,2007,53(3):240-243. LUO Xiang,XU Guoqiang,TAO Zhi,et al.Cooling effectiveness in a rotor-stator system with different pre-swirl angles[J].Journal of Propulsion Technology,2007,28(3):240-243.(in Chinese)
[13]	丁水汀,陶智,徐国强,等.旋转盘腔冷却问题的工程评价[J].航空动力学报,1999,14(1):84-87. DING Shuiting,TAO Zhi,XU Guoqiang,et al.An engineering evaluation system of turbine disk cooling configuration[J].Journal of Aerospace Power,1999,14(1):84-87.(in Chinese)
[14]	丁水汀,陶智,徐国强,等.带进气预旋的旋转空腔平均换热特性研究[J].航空动力学报,1998,13(3):277-280. DING Shuiting,TAO Zhi,XU Guoqiang,et al.A study on averaged heat transfer characteristics of a rotating cavity with preswirl inflow[J].Journal of Aerospace Power,1998,13(3):277-280.(in Chinese)
[15]	Radtke L J.Radial inflow blade cooling system:US,3990812 [P].1976-09-11.