高压涡轮导叶吸力面异型孔的对比研究  

A Comparative Analysis of Shaped Holes on the Suction Surface of High Pressure Turbine Guide Vanes

作　　者：江艳 李海旺[1,3] 陶智[1,2] 周志宇 Yan Jiang;Hai-wang Li;Zhi Tao;Zhi-yu Zhou(Research Institute of Aero-engine,Beihang University;School of Energy and Power Engineering,Beihang University;National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics,Beihang University)

机构地区：[1]北京航空航天大学航空发动机研究院 [2]北京航空航天大学能源与动力工程学院 [3]北京航空航天大学航空发动机气动热力国家级重点实验室

出　　处：《风机技术》2024年第3期8-16,共9页Chinese Journal of Turbomachinery

摘　　要：本文研究了高压涡轮导叶吸力面4种类型气膜孔在4组吹风比下的流动和换热特征,采用了数值模拟的方法获得了吸力面研究区域中4种气膜孔的绝热气膜冷却效率η、换热系数比hr/h0和净热通量减少量(NHFR),且分别进行对比分析。结果显示,簸箕孔因同时具有展向扩张角(β)增大冷气展向覆盖面积和流向扩张角(δ)提高射流贴壁性的优势,呈现出最大的绝热气膜冷却效率η和净热通量减少量(NHFR),但同时其增强了换热,使簸箕孔比其它3种气膜孔拥有最大的净热通量减少量(NHFR)的优势相较于其拥有最大的气膜冷效η的优势有所降低。而水滴孔相较于圆柱孔的优势不明显,故展向扩张角对气膜孔流动和换热特征的影响比流向扩张角大。In this paper,the flow and heat transfer characteristics of four types of film holes on suction surface of high pressure turbine guide vanes were studied at four blowing ratios.Numerical simulation method was employed to obtain the adiabatic film cooling effectivenessη,heat transfer coefficient ratio hr/h0 and net heat flux reduction NHFR of four types of film holes for comparative analysis.Results showed that the laidback fan-shaped hole showed maximum film cooling effectivenessηand net heat flux reduction NHFR.This was because the laidback fan-shaped hole equipped with a lateral divergence angle(β)and a forward divergence angle(δ),which increased the exit cross section area of coolant and let the injected coolant closer to the surface,respectively.Whereas,the enhanced heat transfer eventually caused that advantages of laidback fan-shaped hole has maximum NHFR were less compared with its advantages in maximum film cooling effectivenessη.Moreover,compared with the cylindrical hole,the laidback hole had not obvious advantages.Therefore,the influence of the lateral divergence angle on the flow and heat transfer characteristics of film holes were greater than that of the forward divergence angle.

关 键 词：气膜冷却效率 换热系数 净热通量减少量(NHFR) 异型孔 吸力面 涡轮导叶 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程] TK12[动力工程及工程热物理—工程热物理]