叶顶间隙对多级轴流涡轮气动特性影响的非定常数值计算

推进技术 ›› 2017, Vol. 38 ›› Issue (1): 85-93.

叶顶间隙对多级轴流涡轮气动特性影响的非定常数值计算

李钰洁,刘永葆

海军工程大学动力工程学院舰船动力工程军队重点实验室，湖北武汉 430033,海军工程大学动力工程学院舰船动力工程军队重点实验室，湖北武汉 430033

发布日期:2021-08-15
作者简介:李钰洁，男，博士，研究领域为舰船动力及热力系统的监测。
基金资助:
国家自然科学基金(50721005)；国防预研基金(4010303010303)。

Numerical Simulation on Effects of Tip Clearance on Unsteady Aerodynamic Performance of Multistage Axial Turbine

Military Key Laboratory for Naval Ship Power Engineering，College of Power Engineering， Naval University of Engineering，Wuhan 430033，China and Military Key Laboratory for Naval Ship Power Engineering，College of Power Engineering， Naval University of Engineering，Wuhan 430033，China

Published:2021-08-15

摘要/Abstract

摘要： 涡轮叶顶间隙对其气动特性产生非常明显的影响，为了研究叶顶间隙对涡轮效率以及叶片温度场分布的非定常影响，采用非线性谐波法对多级亚声速轴流涡轮进行了非定常数值计算，与实验结果进行对比后发现，对于本文研究对象，4阶次谐波是考虑计算成本与计算精度的优化值；R1叶顶间隙由0.5%叶高增大至1.5%叶高，涡轮效率降低了0.44%，R4叶顶间隙由0.5%叶高增大至1.5%叶高，涡轮效率降低了0.76%；叶片高温主要集中在近叶顶区域，尾缘温度梯度变化最为剧烈；叶栅级间干涉效应导致高温区温度的周期性波动，温度波动幅值不受叶顶间隙高度的影响但波动区间随间隙增大而升高，静叶相对动叶温度波动幅值较大，S2温度波动保持在11K左右。

关键词: 非线性谐波法；多级轴流涡轮；数值计算；叶顶间隙；温度

Abstract: Turbine tip clearance has obvious effects on the aerodynamic performance of turbine. In order to study the unsteady effects of tip clearance on turbine efficiency and blade temperature field distribution，unsteady numerical simulation on multistage subsonic axial turbine was calculated by the Non-linear harmonic method. Effects of tip clearance on the turbine efficiency and blade temperature field distribution were analyzed. Results show that the fourth-order harmonic was fine enough between calculation resource and precision. When the tip clearance of R1 and R4 increased from 0.5% span to 1.5% span，the turbine efficiency will decrease by 0.44% and 0.76%，respectively. The near-tip region is the major high temperature region while the trailing edge has the sharpest temperature change. The rotor-stator interaction results in temperature periodic fluctuation of the high temperature field. Tip clearance height has no affect on the amplitude of temperature fluctuation but increased the fluctuation range. Vane has larger amplitude than blade does while the S2 has 11K fluctuation amplitude.

Key words: Non-linear harmonic method；Multistage axial turbine；Numerical simulation；Tip clearance；Temperature

李钰洁,刘永葆. 叶顶间隙对多级轴流涡轮气动特性影响的非定常数值计算[J]. 推进技术, 2017, 38(1): 85-93.

LI Yu-jie,LIU Yong-bao. Numerical Simulation on Effects of Tip Clearance on Unsteady Aerodynamic Performance of Multistage Axial Turbine[J]. Journal of Propulsion Technology, 2017, 38(1): 85-93.

参考文献

[1] Huang A C, Greitzer E M, Tan C S. Blade Loading Effects on Axial Turbine Tip Leakage Vortex Dynamics and Loss[R]. ASME GT2012-68302.
[2] Michael H, Grant I. Endwall Profiling with Tip Clearance Flows[R]. ASME GT2012-68488.
[3] Clemens B, Wolfram C, Ullrich I R. Numerical Study of Incidence Angles and Gap Heights in Turbine Cascades and Rotors on Tip Clearance Losses[R]. ASME GT2013-94872.
[4] Maesschalck C D, Lavagnoli S, Paniagua G. Blade Ttip Shape Optimization for Enhanced Turbine Aerothermal Performance[J]. Journal of Turbomachinery, 2013, 136.
[5] Anto K, Xue S, Ng W F. Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer[R]. ASME GT2013-94345.
[6] 李钰洁, 刘永葆, 贺星. 间隙变化对新型涡轮密封气动性能影响的数值分析[J]. 推进技术, 2015, 36(8): 1179-1185. (LI Yu-jie, LIU Yong-bao, HE Xing. Numerical Simulation for Effects of Clearance Change of a Novel Seal on Aerodynamic Performance of Gas Turbine[J]. Journal of Propulsion Technology, 2015, 36(8): 1179-1185.)
[7] Ralph J V, Christopher D G, Mounir B I. Effects of Periodic Unsteadiness on Secondary Flows in High Pressure Turbine Passages[R]. ASME GT2013-95881.
[8] He L. Fourier Methods for Turbomachinery Applications[J]. Progress in Aerospace Sciences, 2010, 46(8): 329-341.
[9] Vilmin S, Tartinville B, Lorrain E, et al. The Nonlinear Harmonic Method Applied to the Combined Effects of Multi-Row Unsteady Flows[R]. ASME GT2013-94847.
[10] Sirdhar M, Sunnam S, Ramakumar B, et al. Effect of Turbulent Intensity and Axial Gap on Turbine Heat Transfer using Steady and Harmonic Models[R]. ASME GT2013-94600.
[11] 赵军, 刘宝杰. 非线性谐波法的进一步校验分析[J]. 航空动力学报, 2008, 23(4): 680-686.
[12] Mohammad R S, Hossein S. The Effects of Tip Clearance on Performance of a Heavy Duty Multi Stages Axial Turbine[R]. ASME GT2012-69553.
[13] He L. Harmonic Solution of Unsteady Flow Around Blades with Separation[J]. AIAA Journal, 2008, 46(6):1299-1307.
[14] Guillaume D, Xavier C, Nicol'as G R. Nonlinear Harmonic Simulations of the Unsteady Aerodynamics of a Fan Stage Section at Windmill[R]. ASME GT2013-95485.
[15] 王晓东, 康顺. 低速轴流涡轮非定常数值模拟的非线性谐波法[J]. 工程热物理学报, 2009, 30(6): 949-952.
[16] 王雷, 刘波. 非线性谐波法在对转压气机中的校检分析[J]. 航空动力学报, 2012, 27(7): 1448-1452.
[17] Md H R, Sung I K, Ibrahim H. Unsteady Tip Leakage Flow Characteristics and Heat Transfer on Turbine Blade Tip and Casing[R]. ASME GT2010-22104.　　　　　　　　　　　　　*　收稿日期:2015-09-08；修订日期:2015-10-27。基金项目:国家自然科学基金(50721005)；国防预研基金(4010303010303)。作者简介:李钰洁,男,博士,研究领域为舰船动力及热力系统的监测。E-mail: 570208063@qq.com(编辑:张荣莉)