跨声速涡轮静叶尾缘激波对动叶前缘气膜冷却效果影响的研究
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摘要
为进一步探究跨声速涡轮中非定常激波对气膜冷却效果的影响,以跨声速涡轮级叶型作为研究对象,采用非定常数值模拟方法,通过在动叶前缘不同弦向位置进行冷气喷射,探讨了静叶尾缘外伸激波的扫掠对动叶前缘气膜冷却效率的影响。研究结果表明,静叶尾缘外伸波接触到动叶前缘时会导致接触点下游气膜冷却效率降低;冷气喷射孔距离前缘越近,每周期内受上游静叶尾缘外伸波影响时间越长,受影响时长在10%~20%周期之间;不同方案中气膜孔下游相同距离位置上,时均冷却效率相差最大可达89.5%。
In order to further clarify the effects of unsteady shockwave on film cooling performance in a transonic turbine,unsteady numerical simulations were conducted on the profiles of a transonic turbine stage. Film holes were located at different positions near leading edge of rotor blade to study the effects of sweeping vane trailing edge outer-extending shock wave on film cooling effectiveness near rotor blade leading edge. The results showed that the sweeping shockwave can cause a decrease in film cooling efficiency downstream of the shockwave on blade surface when it reaches rotor blade. The closer the film hole to the leading edge,the longer the time that coolant jet flow suffers from shockwave,which is within a range of 10%~20% of a period. At positions which have the same distance downstream of film holes,the maximum deviation of film cooling effectiveness can be89.5%.
In order to further clarify the effects of unsteady shockwave on film cooling performance in a transonic turbine,unsteady numerical simulations were conducted on the profiles of a transonic turbine stage. Film holes were located at different positions near leading edge of rotor blade to study the effects of sweeping vane trailing edge outer-extending shock wave on film cooling effectiveness near rotor blade leading edge. The results showed that the sweeping shockwave can cause a decrease in film cooling efficiency downstream of the shockwave on blade surface when it reaches rotor blade. The closer the film hole to the leading edge,the longer the time that coolant jet flow suffers from shockwave,which is within a range of 10%~20% of a period. At positions which have the same distance downstream of film holes,the maximum deviation of film cooling effectiveness can be89.5%.
引文
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[18]Akin M B,Sanz W.The Influence of Transition on CFD Calculations of a Two-Stage Counter-Rotating Turbine[R].ASME 2014-GT-26044.
[19]周莉,韦威,蔡元虎.非定常尾迹输运对动叶气膜冷却流场影响[J].航空动力学报,2012,27(8):1696-1703.
[20]Narzary D P,Gao Z,Mhetras S,et al.Effect of Unsteady Wake on Film-Cooling Effectiveness Distribution on a Gas Turbine Blade with Compound Shaped Holes[R].ASME 2007-GT-27070.
[2]Brachmanski R E,Niehuis R,Bosco A.Investigation of a Separated Boundary Layer and Its Influence on Secondary Flow of a Transonic Turbine Profile[R].ASME2014-GT-25890.
[3]Ochs M,Schulz A,Bauer H J.Investigation of the Influence of Trailing Edge Shock Waves on Film Cooling Performance of Gas Turbine Airfoils[R].ASME 2007-GT-27482.
[4]Adami P,Montomoli F,Belardini E,et al.Interaction Between Wake and Film Cooling Jets:Numerical Analysis[R].ASME 2004-GT-53178.
[5]Ou S,Han J C,Mehendale A B,et al.Unsteady Wake Over a Linear Turbine Blade Cascade with Air and CO2Film Injection,Part I:Effect on Heat Transfer Coefficients[J].Journal of Turbomachinery,1994,116(4):721-729.
[6]Mehendale A B,Han J C,Ou S,et al.Unsteady Wake Over a Linear Turbine Blade Cascade with Air and CO2Film Injection:Part II—Effect on Film Effectiveness and Heat Transfer Distributions[J].Journal of Turbomachinery,1994,116(4):730-737.
[7]李虹杨,郑赟.动静干涉对涡轮转子叶片气膜冷却的影响[J].北京航空航天大学学报,2016,42(1):139-146.
[8]Rigby M J,Johnson A B,Oldfield M L G.Gas Turbine Rotor Blade Film Cooling with and without Simulated NGV Shock Waves and Wakes[R].ASME 90-GT-78.
[9]周勇,赵晓路,徐建中.非定常激波对气膜冷却影响的数值模拟[J].工程热物理学报,2007,28(6):933-935.
[10]迟重然.气冷涡轮叶片的传热设计[D].哈尔滨:哈尔滨工业大学,2010.
[11]Chi Z,Wang S,Ren J,et al.Multi-Dimensional Platform for Cooling Design of Air-Cooled Turbine Blades[R].ASME 2012-GT-68675.
[12]罗磊,王松涛,迟重然,等.传热设计流程在涡轴涡轮冷却中的应用[J].推进技术,2013,34(11):1520-1529.(LUO Lei,WANG Song-tao,CHI Zhongran,et al.Application of Heat Transfer Design Process for Turbine in Turbo Shaft Engine[J].Journal of Propulsion Technology,2013,34(11):1520-1529.)
[13]罗磊,卢少鹏,迟重然,等.气热耦合条件下涡轮动叶叶型与冷却结构优化[J].推进技术,2014,35(5):603-609.(LUO Lei,LU Shao-peng,CHI Zhongran,et al.Conjugate Heat Transfer Optimization for Blade Profiles and Cooling Structure in Turbine Rotor[J].Journal of Propulsion Technology,2014,35(5):603-609.)
[14]卢少鹏,迟重然,罗磊,等.气热耦合条件下涡轮静叶三维优化[J].推进技术,2014,35(3):356-364.(LU Shao-peng,CHI Zhong-ran,LUO Lei,et al.Conjugate Heat Transfer 3-D Optimization for Turbine Stator[J].Journal of Propulsion Technology,2014,35(3):356-364.)
[15]Benabed M,Azzi A,Jubran B A.Numerical Investigation of the Influence of Incidence Angle on Asymmetrical Turbine Blade Model Showerhead Film Cooling Effectiveness[J].Heat and Mass Transfer,2010,46(8-9):811-819.
[16]Murari S,Sathish S,Shraman G,et al.CFD Aerodynamic Performance Validation of a Two-Stage High Pressure Turbine[R].ASME 2011-GT-45569.
[17]Martelli F,Adami P.Unsteady Aerodynamics and Heat Transfer in Transonic Turbine Stages:Modelling Approaches[C].Sharm El-Shiekh:8th International Congress of Fluid Dynamics&Propulsion,2006:14-17.
[18]Akin M B,Sanz W.The Influence of Transition on CFD Calculations of a Two-Stage Counter-Rotating Turbine[R].ASME 2014-GT-26044.
[19]周莉,韦威,蔡元虎.非定常尾迹输运对动叶气膜冷却流场影响[J].航空动力学报,2012,27(8):1696-1703.
[20]Narzary D P,Gao Z,Mhetras S,et al.Effect of Unsteady Wake on Film-Cooling Effectiveness Distribution on a Gas Turbine Blade with Compound Shaped Holes[R].ASME 2007-GT-27070.