高冷气温度下横向波纹隔热屏气膜冷却特性研究

推进技术 ›› 2019, Vol. 40 ›› Issue (4): 866-875.

高冷气温度下横向波纹隔热屏气膜冷却特性研究

曾文明¹,谭晓茗¹,张靖周¹,王健²,邓远灏²

南京航空航天大学能源与动力学院，航空发动机热环境与热结构工业和信息化部重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，航空发动机热环境与热结构工业和信息化部重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，航空发动机热环境与热结构工业和信息化部重点实验室，江苏南京 210016,中国航发四川燃气涡轮研究院，四川成都 610500,中国航发四川燃气涡轮研究院，四川成都 610500

发布日期:2021-08-15
作者简介:艾延廷，博士，教授，研究领域为航空发动机强度、振动及噪声。E-mail: ytai@163.com 通讯作者:田晶，博士生，工程师，研究领域为航空发动机强度、振动及可靠性。
基金资助:
国家自然科学基金(U1508212)。

关键词:加力燃烧室；高冷气温度；横向波纹隔热屏；气膜冷却；冷却效率

Key Laboratory of Aero-Engine Thermal Environment and Structure，Ministry of Industry and Information Technology，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Key Laboratory of Aero-Engine Thermal Environment and Structure，Ministry of Industry and Information Technology，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Key Laboratory of Aero-Engine Thermal Environment and Structure，Ministry of Industry and Information Technology，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,AECC Sichuan Gas Turbine Establishment，Chengdu 610500，China and AECC Sichuan Gas Turbine Establishment，Chengdu 610500，China

Published:2021-08-15

摘要/Abstract

摘要： 通过三维数值模拟的方法分别研究了高冷气温度下吹风比、开孔率以及孔排布等气动参数和结构参数对加力燃烧室横向波纹隔热屏气膜冷却效率和流动特性的影响规律。结果表明:吹风比改变时相同流向截面处波峰的温度总是高于波谷的温度，且壁面上温度呈现“锯齿状”；随着吹风比的增加，隔热屏壁面冷却效率提高，在吹风比M=2.0时冷却效率达到最大值；当吹风比M≥1.5，气膜冷却效率逐渐递增，最后趋于平缓，且吹风比越大趋于平缓的流向间距越短；单位面积冷却流量相同时，气膜孔开孔率[?]=3.14%对隔热屏壁面的冷却效率最高，其次开孔率为[?]=2.18%；当单位面积冷却流量[Gf]≥3.990kg/(m2·s)时，开孔率[?]=1.60%比开孔率[?]=4.90%时对隔热屏壁面的冷却效率高；相同单位面积冷却流量时，气膜孔流向间距增加，展向孔间距减小，气膜叠加效应积聚在壁面处形成有效的气膜层，使得冷却效率趋于一定值对应的流向间距短，气膜孔排布为展向间距p=4mm，流向间距s=6.25mm较其它气膜孔排布冷却效率要高。

关键词: 加力燃烧室；高冷气温度；横向波纹隔热屏；气膜冷却；冷却效率

Abstract: Three-dimensional numerical simulations were conducted to study film cooling characteristics of a transverse ripple shield cooled by high cold gas temperature. The film cooling effectiveness and the flow characteristics of transverse corrugated heat shield in afterburner were obtained on different blowing ratios， opening rates and hole arrangements. The result show that when the blowing ratio changes， the temperature of the wave peak is always higher than the temperature of the trough at the same longitudinal location， and the temperature is serrated on the wall. The film cooling effectiveness increase with the blowing ratio and reach to the maximum with the blowing ratio M=2.0. Besides， the film cooling effectiveness increase gradually and eventually flatten out as M≥1.5 and the greater the blow ratio， the shorter the flow spacing will be. Comparing different opening rates [?] of the ripple shield， the cooling efficiency with [?]=3.14% is bigger than [?]=2.18%. When the cooling flow rate per unit area [Gf]≥3.990kg/(m2·s)， the cooling efficiency with [?]=1.60% is better than [?]=4.90%. With the increase of the longitudinal space and the decrease of the transverse pitch， the cooling efficiency tends to a certain value and the corresponding streamwise spacing is short because of the film stacking effect in film formation. The cooling efficiency is the highest in the holes arrangement of transverse pitch p=4mm， longitudinal space s=6.25mm.

Key words: Afterburner；High cold gas temperature；Transverse ripple shield；Film cooling；Cooling efficiency

曾文明,谭晓茗,张靖周,王健,邓远灏. 高冷气温度下横向波纹隔热屏气膜冷却特性研究[J]. 推进技术, 2019, 40(4): 866-875.

ZENG Wen-ming¹,TAN Xiao-ming¹,ZHANG Jing-zhou¹,WANG Jian²,DENG Yuan-haO². 关键词:加力燃烧室；高冷气温度；横向波纹隔热屏；气膜冷却；冷却效率[J]. Journal of Propulsion Technology, 2019, 40(4): 866-875.

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