预旋进气小尺寸涡轮叶片冷却的流场研究

推进技术 ›› 2012, Vol. 33 ›› Issue (5): 732-739.

预旋进气小尺寸涡轮叶片冷却的流场研究

朱强华,吉洪湖,张勃,陈宝延,关胜如

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;中国航天科工集团三十一研究所,北京 100074;中国航天科工集团三十一研究所,北京 100074

发布日期:2021-08-15
作者简介:朱强华(1980—),男,博士生,研究领域为传热与传质。E-mail:zqh_0702108@sina.com.cn

Numerical Study of Pre-Swirl Flow in Rotating Cascade of a Small Gas Turbine

College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;The 31st Research Institute of CASIC, Beijing 100074, China;The 31st Research Institute of CASIC, Beijing 100074, China

Published:2021-08-15

摘要/Abstract

摘要： 为了了解和掌握一种具有直通式冷气预旋进气系统的小型燃气轮机涡轮转子叶片的流场,在旋转雷诺数Reθ=4.66×10⁶和冷却空气的无量纲质量流量C_w=1750时改变预旋角θ的大小,使其在15°~90°变化,通过数值研究得到了预旋角对涡轮盘腔、连管和涡轮叶片内冷却空气的流动以及叶栅通道中燃气的流动的影响。结果表明:(1)预旋角的变化会改变涡轮盘腔、连管和涡轮叶片冷气进口附近局部区域的流场,但是对涡轮叶片内其它区域和叶栅通道中的流动基本没有影响。(2)随着预旋角的增大,涡轮盘腔内预旋进气冷气射流的轴向穿透深度先增大后减小；当θ<45°时冷却空气沿外围屏流向转盘接收孔,而当θ>45°时冷却空气沿内围屏流向转盘接收孔；气流的周向速度随着预旋角的增大而减小。(3)垂直进气时连管内存在多个回流区和很大的涡流,流动损失较大,而采用预旋进气能够减弱或消除这些流动结构,存在最优预旋角θ_opt,θ_opt≈45°,此时连管的有效流通面积最大。 

关键词: 燃气轮机;涡轮叶片;转静盘腔;预旋;流动;数值模拟

Abstract: A CFD numerical study on the flow field in a rotating cascade of a small gas turbine, which adopted direct-transfer pre-swirl cooling system, was conducted by using ANSYS CFX 12.0 with shear stress transport (SST) turbulence model. A numerical model was obtained according to the actual turbine blade geometry and operating conditions. In the calculations, the pre-swirl angle θ ranges 15°~90° for rotational Reynolds number and non-dimensional mass flow rate of cooling air equals to 4.66×10⁶ and 1750, respectively. The effects of pre-swirl angle on the flow in cavity, connector pipe, inside and outside of the blade were analyzed. The results show that:(1) The flow behavior of cavity, connector pipe and area around the serpentine inlet changes with pre-swirl angle, but the flow in other places is basically invariable when pre-swirl angle changes.(2)The axial depth which can be reached by the pre-swirl air jet in cavity is observed to increase firstly and then decrease as pre-swirl angle increases. The circumferential velocity diminishes with increasing pre-swirl angle.(3)Several recirculation and vortex exist simultaneously in the connector pipe when θ=90°, and these flow structures can be weakened or removed if θ<90°. There is an optimal pre-swirl angle θ_opt≈45°.

Key words: Gas turbine; Turbine blade; Rotor-stator cavity; Pre-swirl; Flow; Numerical simulation

朱强华,吉洪湖,张勃,陈宝延,关胜如. 预旋进气小尺寸涡轮叶片冷却的流场研究[J]. 推进技术, 2012, 33(5): 732-739.

参考文献

[2] Karabay H．Flow and Heat Transfer in a Cover-Plate Pre-Swirl Rotating-Disc System[D]．UK:University of Bath,1998．
[3] Popp O, Zimmermann H, Kutz J．CFD Analysis of Cover-Plate Receiver Flow[J]．Journal of Turbomachi-nery,1998,120(1):43-49．
[4] Geis T, Dittmann M, Dullenkopf K．Cooling Air Temperature Reduction in a Direct Transfer Pre-Swirl System[R]．ASME 2003-GT-38231．
[5] Ciampoli F, Hills N J, Chew J W, et al．Unsteady Numer-ical Simulation of the Flow in a Direct Transfer Pre-Swirl System[R]．ASME 2008-GT-51198．
[6] 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．
[7] 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,2007,28(3):240-243．(LUO Xiang, XU Guo-qiang, 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．)
[8] 白洛林, 冯青, 刘松龄, 等．预旋进气的盘腔系统内流场的数值研究[J]．推进技术,2003,24(2):135-137．(BAI Luo-lin, FENG Qing, LIU Song-ling, et al． Numerical Investigation on Preswirl Flow in Rotating Disc System[J]．Journal of Propulsion Technology,2003,24(2):135-137．)
[9] 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．
[10] 冶萍, 张靖周．有预旋进气转静盘腔中的流动和换热特性数值研究[J]．航空动力学报,2004,19(3)．
[11] 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．
[12] ZHU Qiang-hua, JI Hong-hu, WANG Suo-fang.Cooling Air Temperature Reduction and Iocal Heat Transfer in a Pre-Swirl Shrouded Rotor-Stator System[C].Nanjing:The 3rd International Symposium on Jet Propulsion and Power Engineering, 2005.
[13] 董平, 黄洪雁, 冯国泰．高压燃气涡轮径向内冷叶片气热耦合的数值分析[J]．航空动力学报,2008,23(2):201-207．
[14] 张立超, 何建元, 马晓虹．矩阵式高温涡轮叶片热流耦合计算及验证[J]．舰船科学技术,2010,32(8)．
[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．