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[1]姚家旭,罗 丁,范 青,等.绝热气膜冷却效率的传热传质类比数值分析[J].火箭推进,2021,47(01):62-69.
　YAO Jiaxu,LUO Ding,FAN Qing,et al.Numerical analysis of heat-mass transfer analogy for adiabatic film-cooling effectiveness[J].Journal of Rocket Propulsion,2021,47(01):62-69.
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绝热气膜冷却效率的传热传质类比数值分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 47 期数: 2021年01期 页码: 62-69 栏目: 研究与设计 出版日期: 2021-02-28
Title:
Numerical analysis of heat-mass transfer analogy for adiabatic film-cooling effectiveness
文章编号:
1672-9374(2021)01-0062-08
作者:
姚家旭1; 罗 丁1; 范 青2; 张 科1; 雷 蒋1; 马 元2
(1.西安交通大学 航天航空学院 机械结构强度与振动国家重点实验室,陕西 西安 710049; 2.西安航天动力研究所,陕西 西安 710100)
Author(s):
YAO Jiaxu1;  LUO Ding1;  FAN Qing2;  ZHANG Ke1;  LEI Jiang1;  MA Yuan2
(1. State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace, Xi'an Jiaotong University, Xi'an 710049, China; 2. Xi'an Aerospace Propulsion Institute, Xi'an 710100, China)
关键词:
气膜冷却;  双射流;  绝热气膜冷却效率;  传热传质类比;  密度比
Keywords:
film-cooling;  double-jet;  adiabatic film-cooling effectiveness;  heat-mass transfer analogy;  density ratio
分类号:
V231.1
文献标志码:
A
摘要:
为验证不同温度条件下的传热传质类比是否有效,应用CFD模拟方法分析了密度比(Rd)为1.5和2.5、吹风比为0.5和1.5工况下的平板双射流气膜冷却结构。双射流孔间流向距离(Ds/d)为3.0,横向距离(Dp/d)为1.0。通过传热和传质方法分别得到了气膜冷却效率。分析结果表明:传质方法与传热方法所获得的气膜冷却效率结果差距较小,二者偏差的主要原因是流体的热导率。
Abstract:
CFD simulation methods were employed to analyze the double-jet film-cooling structure on a flat plate with the density ratio of 1.5 and 2.5, and the blowing ratio of 0.5 and 1.5, in order to check the validity of heat-mass transfer analogy at different temperature conditions. The streamwise distance(Ds/d)between the double-jet holes was 3.0 and the spanwise distance(Dp/d)was 1.0. The film-cooling effectiveness was acquired from heat-transfer and mass-transfer methods. The results show that, the difference in film-cooling effectiveness results from mass transfer and heat transfer methods is rather small. The main reason that leads to the difference between the two methods is the heat conductivity of the fluid.

参考文献/References:

[1] 任加万,谭永华.冲压发动机燃烧室热防护技术[J].火箭推进,2006,32(4):38-42.
REN J W,TAN Y H.Thermal protection techniques of ramjet combustor[J].Journal of Rocket Propulsion,2006,32(4):38-42.
[2] EKKAD S,HAN J C.A review of hole geometry and coolant density effect on film cooling[C]//Proceedings of ASME 2013 Heat Transfer Summer Conference.Minneapolis,Minnesota: ASME,2013.
[3] WATSON T B,NAHANG—TOUDESHKI S,WRIGHT L M,et al.Application of S—PIV for investigation of round and shaped film cooling holes at high density ratios[C]//Proceedings of ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition.Seoul,South Korea:ASME,2016.
[4] EBERLY M K,THOLE K A.Time—resolved film—cooling flows at high and low density ratios[J].Journal of Turbomachinery,2014,136(6):061003.
[5] WRIGHT L M,MCCLAIN S T,CLEMENSON M D.Effect of density ratio on flat plate film cooling with shaped holes using PSP[J].Journal of Turbomachinery,2011,133(4):041011.
[6] 陈大为,朱惠人,李华太,等.基于压力敏感漆技术的尾迹对涡轮动叶前缘气膜冷却影响研究[J].推进技术,2019,40(4):858-865.
[7] 李佳,任静,蒋洪德.密度比和吹风比对透平静叶气膜冷却的影响[J].工程热物理学报,2011,32(8):1295-1298.
[8] 姚家旭,雷蒋.不同横向距离下双射流孔流动与冷却特性实验研究[J].火箭推进,2018,44(1):36-43.
YAO J X,LEI J.Experimental study on flow and cooling characteristics of double—jet film—cooling holes at different spanwise distances[J].Journal of Rocket Propulsion,2018,44(1):36-43.
[9] YAO J X,XU J,ZHANG K,et al.Interaction of flow and film—cooling effectiveness between double—jet film—cooling holes with various spanwise distances[C]//Proceedings of ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition.Charlotte,North Carolina: ASME,2017.
[10] SHIAU C C,CHEN A F,HAN J C,et al.Full—scale turbine vane end—wall film—cooling effectiveness distribution using PSP technique[C]//Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition.Montreal,Quebec,Canada:ASME,2015.
[11] JONES T V.Theory for the use of foreign gas in simulating film cooling[J].International Journal of Heat and Fluid Flow,1999,20(3):349-354.
[12] SHADID J N,ECKERT E R G.The mass transfer analogy to heat transfer in fluids with temperature—dependent properties[J].Journal of Turbomachinery,1991,113(1):27-33.
[13] HAN J C,RALLABANDI A P.Turbine blade film cooling using psp technique[J].Frontiers in Heat and Mass Transfer,2010,1(1):1-16.
[14] KAYS W M.Convective heat and mass transfer[M].[S.l.]:Tata McGraw—Hill Education,2012.
[15] BOGARD D G,THOLE K A.Gas turbine film cooling[J].Journal of Propulsion and Power,2006,22(2):249-270.
[16] HAN J C,DUTTA S,EKKAD S.Gas turbine heat transfer and cooling technology[M].New York: CRC Press,2012.
[17] WRIGHT L M,GAO Z H,VARVEL T A,et al.Assessment of steady state PSP,TSP,and IR measurement techniques for flat plate film cooling[C]//Proceedings of ASME 2005 Summer Heat Transfer Conference.San Francisco,California,USA: ASME,2005.
[18] WIESE C J,RUTLEDGE J L,POLANKA M D.Experimental evaluation of thermal and mass transfer techniques to measure adiabatic effectiveness with various coolant to freestream property ratios[J].Journal of Turbomachinery,2018,140(2):021001.
[19] RUTLEDGE J L,POLANKA M D.Computational fluid dynamics evaluations of unconventional film cooling scaling parameters on a simulated turbine blade leading edge[J].Journal of Turbomachinery,2014,136(10):101006.
[20] RAVELLI S,BARIGOZZI G.Numerical evaluation of heat/mass transfer analogy for leading edge showerhead film cooling on a first—stage vane[J].International Journal of Heat and Mass Transfer,2019,129: 842-854.
[21] YAO J X,SU P F,HE J H,et al.Experimental and numerical investigations on double—jet film—cooling with different mainstream incidence angles[J].Applied Thermal Engineering,2020,166: 114737.
[22] WANG Z,LIU J J,AN B T,et al.Effects of axial row—spacing for double—jet film—cooling on the cooling effectiveness[C]//Proceedings of ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition.Vancouver,British Columbia,Canada: ASME,2012.

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备注/Memo

收稿日期:2020-06-30
基金项目:国家自然科学基金(5177615); 国家科技重大专项(2017-III-0009-0035); 西安市科技计划(201805034YD12CG18(3))
作者简介:姚家旭(1993—),男,博士生,研究领域为推进系统热端部件传热与冷却。

更新日期/Last Update: 2021-02-20