低压涡轮导叶内环结构设计
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摘要
为实现低压涡轮导叶内环初步方案快速设计、降低低压涡轮工作叶片冷气相对总温和提高冷却效率,以某型低压涡轮导叶内环为研究对象,提出了1种基于等熵过程的低压涡轮导叶内环设计方法和流程,并采用3维数值仿真方法对设计结果进行了分析和验证,得到了不同预旋喷嘴径向高度对转、静子腔内的流动影响规律。结果表明:提出的低压涡轮导叶内环设计方法和流程能够满足初步方案的设计要求;预旋喷嘴的径向高度对工作叶片和涡轮盘表面的相对总温影响较大,工程上需综合考虑。
In order to quickly design the guide vane inner-ring of the low pressure turbine(LPT)of the preliminary scheme,improve the cold air relative total temperature and cooling efficiency of the rotor blade of the LPT,taking a LPT guide vane inner-ring as the research object,a design method and design process of the LPT guide vane inner-ring based on isentropic process was presented. The design results were analyzed and verified by a three-dimensional numerical simulation method,and the flow influence rules of the radial height of different pre-swirl nozzle in the cavity of rotor and stator were obtained. The results show that the design method and design process of LPT guide vane inner-ring can meet the design requirements of the preliminary scheme. The radial height of the pre-swirl nozzle has a great effect on the relative total temperature of the rotor blade and turbine disk,which needs to be considered comprehensively in engineering.
In order to quickly design the guide vane inner-ring of the low pressure turbine(LPT)of the preliminary scheme,improve the cold air relative total temperature and cooling efficiency of the rotor blade of the LPT,taking a LPT guide vane inner-ring as the research object,a design method and design process of the LPT guide vane inner-ring based on isentropic process was presented. The design results were analyzed and verified by a three-dimensional numerical simulation method,and the flow influence rules of the radial height of different pre-swirl nozzle in the cavity of rotor and stator were obtained. The results show that the design method and design process of LPT guide vane inner-ring can meet the design requirements of the preliminary scheme. The radial height of the pre-swirl nozzle has a great effect on the relative total temperature of the rotor blade and turbine disk,which needs to be considered comprehensively in engineering.
引文
[1]赵斌,李绍斌,周盛,等.航空发动机空气系统气源引气的研究进展[J].航空工程进展,2012,3(4):476-485.ZHAO Bin,LI Shaobin,ZHOU Sheng,et al. Research progress on the aircraft engine air system bleeding[J].Advances in Aeronautical Science and Engineering,2012,3(4):476-485.(in Chinese)
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[4] EL-Oun Z,Owen J M. Pre-swirl blade-cooling effectiveness in an adiabatic rotor-stator system[J]. Journal of Turbomachinery,1988,111(4):522-529.
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[7]张建超.冷气预旋结构的温降与流阻特性研究[D].南京:南京航空航天大学,2014.ZHANG Jianchao. Research on characteristics of temperature reduction and flow resistance of pre-swirl system[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2014.(in Chinese)
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[9]刘高文,李碧云,蒋兆午,等.预旋角度对预旋孔流动特性的影响[J].推进技术,2012,33(5):740-746.LIU Gaowen,LI Biyun,JIANG Zhaowu,et al. Effects of pre-swirl angle on flow characteristics of pre-swirl nozzle[J]. Journal of Propulsion Technology,2012,33(5):740-746.(in Chinese)
[10]孙占东,罗翔,黄由之,等.预旋结构影响带盖盘预旋系统流动的实验[J].推进技术,2017,38(8):1826-1832.SUN Zhandong,LUO Xiang,HUANG Youzhi,et al. Experiment of flow of a cover-plate pre-swirl system influenced by pre-swirl structrue[J]. Journal of Propulsion Technology,2017,38(8):1826-1832.(in Chinese)
[11]朱强华.预旋孔径向位置变化对转—静盘腔内换热影响的研究[D].南京:南京航空航天大学,2006.ZHU Qianghua. Studies of the heat transfer in a rotor-stator cavity with the change of the radial position of pre-swirl nozzle[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2006.(in Chinese)
[12]王锁芳,朱强华,栾海峰,等.高位预旋进气转静盘腔换热实验[J].航空动力学报,2007,22(8):1216-1221.WANG Suofang,ZHU Qianghua,LUAN Haifeng,et al. Experimental study on heat transfer in rotor-stator cavity with high-positioned pre-swirl inflow[J].Journal of Aerospace Power, 2007,22(8):1216-1221.(in Chinese)
[13]林立,谭勤学,吴康.低位预旋进气转静系盘腔流动特性研究[J].推进技术,2016,37(2):258-265.LIN Li,TAN Qinxue,WU Kang.Study on flow characteristics of disc cavity in rotating-stator system with low pre-swirl inflow[J]. Journal of Propulsion Technology,2016,37(2):258-265.(in Chinese)
[14]王锁芳,朱强华,张宇,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)
[15]曾军,张剑,黄康才.预旋进气转-静盘腔中的流动和传热数值研究[J].航空动力学报,2008,23(7):1168-1173.ZENG Jun,ZHANG Jian,HUANG Kangcai. Flow and heat transfer investigation in pre-swirl inflow rotor-stator cavity[J]. Journal of Aerospace Power,2008,23(7):1168-1173.(in Chinese)
[2]梁春华.未来的航空涡扇发动机技术[J].航空发动机,2005,31(4):54-58.LIANG Chunhua. Future aircraft turbofan engine technologies[J].Aeroengine,2005,31(4):54-58.(in Chinese)
[3] J Michael Owen. Modelling internal air systems in gas turbine engines[J].Journal of Aerospace Power,2007,22(4):505-520.
[4] EL-Oun Z,Owen J M. Pre-swirl blade-cooling effectiveness in an adiabatic rotor-stator system[J]. Journal of Turbomachinery,1988,111(4):522-529.
[5] Karabay H,Pilbrow R,Wilson M,et al. Performance of pre-swirl rotating-disc systems[J]. ASME Journal of Gas Turbine and Power,2000,122(3):422-450.
[6]徐昊,王索芳.预旋喷嘴对预旋系统温降特性的数值研究[J].重庆理工大学学报(自然科学),2015(3):30-36.XU Hao,WANG Suofang. Numerical research on influences of pre-swirl nozzle on temperature reduction characteristic of pre-swirl system[J].Journal of Chongqing University of Technol ogy(Natural Science),2015(3):30-36.(in Chinese)
[7]张建超.冷气预旋结构的温降与流阻特性研究[D].南京:南京航空航天大学,2014.ZHANG Jianchao. Research on characteristics of temperature reduction and flow resistance of pre-swirl system[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2014.(in Chinese)
[8]刘育心,刘高文,吴衡,等.叶型孔式预旋喷嘴流动特性数值研究[J].推进技术,2016,37(2):333-337.LIU Yuxin,LIU Gaowen,WU Heng,et al. Numerical investigation on flow characteristics of a vane shaped hole pre-swirl nozzle[J]. Journal of Propulsion Technology,2016,37(2):333-337.(in Chinese)
[9]刘高文,李碧云,蒋兆午,等.预旋角度对预旋孔流动特性的影响[J].推进技术,2012,33(5):740-746.LIU Gaowen,LI Biyun,JIANG Zhaowu,et al. Effects of pre-swirl angle on flow characteristics of pre-swirl nozzle[J]. Journal of Propulsion Technology,2012,33(5):740-746.(in Chinese)
[10]孙占东,罗翔,黄由之,等.预旋结构影响带盖盘预旋系统流动的实验[J].推进技术,2017,38(8):1826-1832.SUN Zhandong,LUO Xiang,HUANG Youzhi,et al. Experiment of flow of a cover-plate pre-swirl system influenced by pre-swirl structrue[J]. Journal of Propulsion Technology,2017,38(8):1826-1832.(in Chinese)
[11]朱强华.预旋孔径向位置变化对转—静盘腔内换热影响的研究[D].南京:南京航空航天大学,2006.ZHU Qianghua. Studies of the heat transfer in a rotor-stator cavity with the change of the radial position of pre-swirl nozzle[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2006.(in Chinese)
[12]王锁芳,朱强华,栾海峰,等.高位预旋进气转静盘腔换热实验[J].航空动力学报,2007,22(8):1216-1221.WANG Suofang,ZHU Qianghua,LUAN Haifeng,et al. Experimental study on heat transfer in rotor-stator cavity with high-positioned pre-swirl inflow[J].Journal of Aerospace Power, 2007,22(8):1216-1221.(in Chinese)
[13]林立,谭勤学,吴康.低位预旋进气转静系盘腔流动特性研究[J].推进技术,2016,37(2):258-265.LIN Li,TAN Qinxue,WU Kang.Study on flow characteristics of disc cavity in rotating-stator system with low pre-swirl inflow[J]. Journal of Propulsion Technology,2016,37(2):258-265.(in Chinese)
[14]王锁芳,朱强华,张宇,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)
[15]曾军,张剑,黄康才.预旋进气转-静盘腔中的流动和传热数值研究[J].航空动力学报,2008,23(7):1168-1173.ZENG Jun,ZHANG Jian,HUANG Kangcai. Flow and heat transfer investigation in pre-swirl inflow rotor-stator cavity[J]. Journal of Aerospace Power,2008,23(7):1168-1173.(in Chinese)