高压涡轮气冷叶片冷却掺混损失数值研究

推进技术 ›› 2018, Vol. 39 ›› Issue (2): 342-350.

高压涡轮气冷叶片冷却掺混损失数值研究

侯伟涛,潘贤德,张洪,慕粉娟

中国航发商用航空发动机有限责任公司，上海 200241,中国航发商用航空发动机有限责任公司，上海 200241,中国航发商用航空发动机有限责任公司，上海 200241,中国航发商用航空发动机有限责任公司，上海 200241

发布日期:2021-08-15
作者简介:侯伟涛，男，博士，工程师，研究领域为涡轮气动设计技术。

Numerical Investigation into Coolant Mixing Loss of High Pressure Turbine Air-Cooled Blade

AECC Commercial Aircraft Engine Co. LTD.，Shanghai 200241，China,AECC Commercial Aircraft Engine Co. LTD.，Shanghai 200241，China,AECC Commercial Aircraft Engine Co. LTD.，Shanghai 200241，China and AECC Commercial Aircraft Engine Co. LTD.，Shanghai 200241，China

Published:2021-08-15

摘要/Abstract

摘要： 为探索高压涡轮气冷叶片多排冷却孔出流对各排孔冷却掺混损失的影响，采用三维粘性流场数值模拟技术，对典型气冷叶片多排孔冷却射流流场和叶栅性能进行了研究，并将冷却掺混损失数值计算结果与Hartsel模型预测值进行了对比。研究结果表明:气冷叶片表面多排冷却孔射流相互作用对各排冷却射流与主流掺混引入的流动损失影响较小，各排射流冷却掺混损失相互独立具有简单的可叠加性质；叶片表面各区域冷却射流出流对叶栅性能影响程度有所不同，尾缘劈缝与吸力面冷却射流对叶栅性能影响较大，前缘区域次之，压力面冷却射流对叶栅性能影响较小；和数值计算结果相比，总压损失系数Hartsel冷却掺混损失模型预测值偏高，尤其对于尾缘和吸力面主流马赫数较大的区域，损失模型预测值为计算结果的2～4倍，而前缘和压力面预测值和计算结果符合性较好。

关键词: 气冷叶片；冷却掺混损失；数值模拟

Abstract: In order to investigate the effects of air-cooled blade in high pressure turbine multi-row injection on the mixing loss of each cooling row， the flow fields and performance for a typical multi-row injection air-cooled blade planar cascade by using 3D viscous CFD simulation were presented， and the coolant mixing loss coefficient from numerical simulation results were contrasted to the Hartsel mixing loss prediction value. The investigation results illustrate that the multi-row injection interaction in air-cooled blade has little effect on coolant mixing loss from each row， the total loss could be obtained simply by adding each mixing loss. The coolant injections from different blade surface location have different extent of influence to blade performance. The trailing edge slot and suction side coolant injection affect more important than leading edge injection， and the pressure side cooling almost has no effect to blade performance. Comparing to the simulation results， the mixing loss model predicted larger total pressure loss coefficient， especially for trailing edge and suction side coolant injections where the main flow Mach number higher than other regions， the loss model predicted values are 2 to 4 times simulation results. For the leading edge and pressure side coolant injections the prediction value shows acceptable agreement.

Key words: Air-cooled blade；Coolant mixing loss；Numerical simulation

侯伟涛,潘贤德,张洪,慕粉娟. 高压涡轮气冷叶片冷却掺混损失数值研究[J]. 推进技术, 2018, 39(2): 342-350.

HOU Wei-tao,PAN Xian-de,ZHANG Hong,MU Fen-juan. Numerical Investigation into Coolant Mixing Loss of High Pressure Turbine Air-Cooled Blade[J]. Journal of Propulsion Technology, 2018, 39(2): 342-350.

参考文献

[1] Rolls-Royce. The Jet Engine[M]. UK: Key Publishing Limited, 2005.
[2] Young J B, Wilcock R C. Modeling the Air-Cooled Gas Turbine: Part 1-General Thermodynamics[J]. ASME Journal of Turbomachinery, 2002, 124(2): 207-213.
[3] Lakshminarayana B. Fluid Dynamics and Heat Transfer of Turbomachinery[M]. New York: Wiley, 1995.
[4] Hartsel J E. Prediction of Effects of Mass-Transfer Cooling on the Blade-Row Efficiency of Turbine Airfoils[R].AIAA 72-11.
[5] Hartsel J E. An Experimental Investigation of the Effects of Massive Film-Cooling on the Aerodynamics of a Turbine Airfoil[D]. Ohio: The Ohio State University, 1970.
[6] Shapiro A. The Dynamics and Thermodynamics of Compressible Fluid Flow: Volume I[M]. New York: Ronald Press, 1953.
[7] MacArthur C D. Advanced Aero-Engine Turbine Technologies and Their Application to Industrial Gas Turbines[R]. ISABE 99-7151.
[8] Horlock J H, Watson D T, Jones T V. Limitations on Gas Turbine Performance Imposed by Large Turbine Cooling Flows[J]. Journal of Engineering for Gas Turbines & Power, 2000, 123(3): 487-494.
[9] Ito S, Eckert E R G, Goldstein R J. Aerodynamic Loss in a Gas Turbine Stage with Film Cooling[J]. Journal of Engineering for Power Transactions of the ASME, 1980, 102(4): 964-970.
[10] Day C R B, Oldfield M L G, Lock G D. Aerodynamics Performance of an Annular Cascade of Film Cooled Nozzle Guide Vanes Under Engine Representative Conditions[J]. Experiments in Fluids, 2000, 29(2): 117-129.
[11] Bohn D, Kim T S. Aerodynamic Loss Prediction of Axial Flow Turbine Blade Rows with Coolant Injection[J]. Journal of Power & Energy, 1999, 213(2): 93-101.
[12] Hong Y, Fu C, Cunzhong G, et al. Investigation of Cooling-Air Injection on the Flow Field within a Linear Turbine Cascade[R]. ASME 97-GT-520.
[13] 乔渭阳, 曾军, 曾文演, 等. 气膜孔喷气对涡轮气动性能影响的实验研究[J]. 推进技术, 2007, 28(1):14-19. (QIAO Wei-yang, ZENG Jun, ZENG Wen-yan, et al. Experimental Studies for the Aerodynamic Loss in Gas Turbine with Film Cooling[J]. Journal of Propulsion Technology, 2007, 28(1): 14-19.)
[14] 曾军, 乔渭阳, 孙大伟, 等. 带尾缘劈缝冷气喷射的涡轮叶栅性能实验及计算[J]. 推进技术 , 2008, 29(6): 710-715. (ZENG Jun, QIAO Wei-yang, SUN Da-wei, et al. Numerical Simulation and Experiment for Turbine Cascade with Trailing Edge Coolant Injection[J]. Journal of Propulsion Technology, 2008, 29(6): 710-715.)
[15] 孙大伟, 乔渭阳, 曾军, 等. 尾缘喷气方式对涡轮叶栅气动性能的影响[J]. 推进技术, 2007, 28(6):641-646. (SUN Da-wei, QIAO Wei-yang, ZENG Jun, et al. Aerodynamic Effect of Turbine Blade Trailing Edge Ejection on Turbine Cascade[J]. Journal of Propulsion Technology, 2007, 28(6): 641-646.)
[16] 侯伟涛, 乔渭阳, 罗华玲. 压力面气膜冷却数值模拟[J]. 推进技术, 2009, 30(3): 318-322. (HOU Wei-tao, QIAO Wei-yang, LUO Hua-ling. Numerical Simulation of the Pressure Side Film Cooling[J]. Journal of Propulsion Technology, 2009, 30(3): 318-322.)
[17] 侯伟涛. 跨声速涡轮非定常流动机理及设计技术研究[D]. 西安:西北工业大学, 2011.
[18] Lim C H, Pullan G, Northall J. Estimating the Loss Associated with Film Cooling for a Turbine Stage[J]. Journal of Turbomachinery, 2010, 134(2): 206-210.　　　　　　　　　　　　　*　收稿日期:2016-12-15；修订日期:2017-02-01。作者简介:侯伟涛,男,博士,工程师,研究领域为涡轮气动设计技术。E-mail: mailtohouweitao@qq.com(编辑:张荣莉)