高热负荷加力燃烧室隔热屏壁温分析改进算法

凌文辉

doi:10.13224/j.cnki.jasp.20240661

高热负荷加力燃烧室隔热屏壁温分析改进算法

doi: 10.13224/j.cnki.jasp.20240661

凌文辉

北京动力机械研究所，北京 100074

详细信息

作者简介:
凌文辉（1968-），男，研究员，博士，研究方向为发动机设计。E-mail：lingwenhui2008@sina.com

中图分类号: V233.1
计量
- 文章访问数: 352
- HTML浏览量: 142
- PDF量: 43
- 被引次数: 0
出版历程
- 收稿日期: 2024-09-26
- 网络出版日期: 2025-02-09

Improvement algorithm of wall temperature analysis for high heat load afterburner liner

LING Wenhui

Beijing Power Machinery Institute，Beijing 100074，China

摘要

摘要:
随着加力燃烧室热负荷水平逐步提高，在有限冷气量的强约束下隔热屏冷却需开展精细化设计，现有的隔热屏壁温分析算法精度无法满足高热负荷加力燃烧室设计需求。本文针对影响加力燃烧室隔热屏壁温计算精确性的关键参数，开展了算法改进，基于改进算法，计算加力燃烧室隔热屏壁温，并与试验结果进行对比分析。改进算法的计算结果与试验结果误差不大于7%，较改进前减小8%，有效提升了高热负荷加力燃烧室隔热屏壁温的计算精度。
- 加力燃烧室 /
- 隔热屏 /
- 壁温 /
- 气动特性 /
- 传热
Abstract:
As the heat load of afterburner increased, the cooling of liner required for refined design under the strong constraint of effective cold air volume. The accuracy of the liner wall temperature analysis algorithm cannot meet the development requirements of high heat load afterburner. Engineering algorithm optimization for critical parameters was carried out, which affected the accuracy of the high heat load afterburner liner wall temperature. Based on the optimized method, calculations were carried out for the wall temperature of the afterburner liner, and compared with the test values. The error between engineering design method and test results was less than 7%, and the error between evaluation results of the revised engineering algorithm and the test results decreased by 8% compared with those before the correction. The optimization method can effectively improve computation accuracy of. wall temperature for high heat load afterburner liner.
- afterburner /
- liner /
- wall temperature /
- aerodynamic characteristic /
- heat transfer

HTML

图 1 加力燃烧室隔热屏简图

Figure 1. Diagram of afterburner liner

下载: 全尺寸图片幻灯片

图 2 加力燃烧室隔热屏传热示意图

Figure 2. Sketch map of heat transfer for afterburner liner

下载: 全尺寸图片幻灯片

图 3 程序流程图

Figure 3. Program flow chart

下载: 全尺寸图片幻灯片

图 4 冷却结构试验件

Figure 4. Photo of cooling structure test piceces

下载: 全尺寸图片幻灯片

图 5 冷却结构冷却特性试验

Figure 5. Experimental study on cooling characteristic of cooling structures

下载: 全尺寸图片幻灯片

图 6 单管燃烧室

Figure 6. Single tube combustion chamber

下载: 全尺寸图片幻灯片

图 7 燃烧室辐射传热标校元件级试验系统

Figure 7. Schematic diagram and real picture of test system for combustor radiation characters

下载: 全尺寸图片幻灯片

图 8 工程计算值与试验结果对比

Figure 8. Comparison between engineering calculation values and test results

下载: 全尺寸图片幻灯片

参考文献(22)

[1]	LI Yang,LIU Tao,TAO Jianjun,et al. Heat transfer characteristics in a narrow confined channel with discrete impingement cooling[J]. Chinese Journal of Aeronautics,2022,35(4): 220-229. doi: 10.1016/j.cja.2021.08.022
[2]	YANG Weihua,XUE Shulin,HE Yihong,et al. Experimental study on the heat transfer characteristics of high blockage ribs channel[J]. Experimental Thermal and Fluid Science,2017,83: 248-259. doi: 10.1016/j.expthermflusci.2017.01.016
[3]	葛绍岩,刘登瀛,徐靖中,等. 气膜冷却[M]. 北京: 科学出版社,1985. GE Shaoyan,LIU Dengying,XU Jingzhong,et al. Film cooling[M]. Beijing: Science Press,1985. (in Chinese GE Shaoyan, LIU Dengying, XU Jingzhong, et al. Film cooling[M]. Beijing: Science Press, 1985. (in Chinese)
[4]	程明,扈鹏飞,万斌,等. 基于Gambit前处理的气膜冷却火焰筒壁温分析[J]. 航空发动机,2017,43(2): 6-9. CHENG Ming,HU Pengfei,WAN Bin,et al. Wall temperature analysis of film cooling flame tube based on gambit[J]. Aeroengine,2017,43(2): 6-9. (in Chinese CHENG Ming, HU Pengfei, WAN Bin, et al. Wall temperature analysis of film cooling flame tube based on gambit[J]. Aeroengine, 2017, 43(2): 6-9. (in Chinese)
[5]	赵玉文. 发散冷却结构流动与传热特性研究[D]. 南京: 南京航空航天大学,2012. ZHAO Yuwen. Study on flow and heat transfer characteristics of divergent cooling structure[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2012. (in Chinese ZHAO Yuwen. Study on flow and heat transfer characteristics of divergent cooling structure[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese)
[6]	伍楠. 发散冷却关键问题的实验和数值研究[D]. 合肥: 中国科学技术大学,2019. WU Nan. Experimental and numerical study on key problems of divergent cooling[D]. Hefei: University of Science and Technology of China,2019. (in Chinese WU Nan. Experimental and numerical study on key problems of divergent cooling[D]. Hefei: University of Science and Technology of China, 2019. (in Chinese)
[7]	杨卫华,王立,宋双文,等. 冲击发散冷却流场结构PIV测量[J]. 航空动力学报,2010,25(3): 483-487. YANG Weihua,WANG Li,SONG Shuangwen,et al. PIV measurement of flow field for impingement-effusion cooling[J]. Journal of Aerospace Power,2010,25(3): 483-487. (in Chinese YANG Weihua, WANG Li, SONG Shuangwen, et al. PIV measurement of flow field for impingement-effusion cooling[J]. Journal of Aerospace Power, 2010, 25(3): 483-487. (in Chinese)
[8]	徐国强,谢毅,丁水汀,等. “冲击-气膜”复合式结构冷却效果数值研究[J]. 热科学与技术,2009,8(1): 1-7. XU Guoqiang,XIE Yi,DING Shuiting,et al. Numerical simulation on cooling effectiveness of combined impingement and film Cooling[J]. Journal of Thermal Science and Technology,2009,8(1): 1-7. (in Chinese doi: 10.3969/j.issn.1671-8097.2009.01.001 XU Guoqiang, XIE Yi, DING Shuiting, et al. Numerical simulation on cooling effectiveness of combined impingement and film Cooling[J]. Journal of Thermal Science and Technology, 2009, 8(1): 1-7. (in Chinese) doi: 10.3969/j.issn.1671-8097.2009.01.001
[9]	张鹏,付经伦,刘建军. 气膜和冲击复合冷却结构耦合传热数值研究[J]. 工程热物理学报,2015,36(11): 2352-2355. ZHANG Peng,FU Jinglun,LIU Jianjun. Numerical investigation of conjugate heat transfer for combined film and impingement cooling[J]. Journal of Engineering Thermophysics,2015,36(11): 2352-2355. (in Chinese ZHANG Peng, FU Jinglun, LIU Jianjun. Numerical investigation of conjugate heat transfer for combined film and impingement cooling[J]. Journal of Engineering Thermophysics, 2015, 36(11): 2352-2355. (in Chinese)
[10]	BUNKER R S. A review of shaped hole turbine film-cooling technology[J]. Journal of Heat Transfer,2005,127(4): 441-453. doi: 10.1115/1.1860562
[11]	BERNHARD GUSTAFSSON K M,JOHANSSON T G. An experimental study of surface temperature distribution on effusion-cooled plates[J]. Journal of Engineering for Gas Turbines and Power,2001,123(2): 308-316. doi: 10.1115/1.1364496
[12]	Bunker R S. Turbine heat transfer and cooling : an overview: GT 2013-94174 [R]. San Diego,US: ASME,2013.
[13]	凌文辉,王以飞,裘云,等. 冲压发动机气膜冷却分析模型[J]. 推进技术,2011,32(5): 713-716. LING Wenhui,WANG Yifei,QIU Yun,et al. A model to analyze the film cooling characteristics of a ramjet combustor[J]. Journal of Propulsion Technology,2011,32(5): 713-716. (in Chinese LING Wenhui, WANG Yifei, QIU Yun, et al. A model to analyze the film cooling characteristics of a ramjet combustor[J]. Journal of Propulsion Technology, 2011, 32(5): 713-716. (in Chinese)
[14]	张晶. 火焰筒多斜孔壁传热特性研究及一维壁温设计程序开发[D]. 南京: 南京航空航天大学,2010. ZHANG Jing. Study on heat transfer characteristics of multi-inclined hole wall of flame tube and development of one-dimensional wall temperature design program[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2010. (in Chinese ZHANG Jing. Study on heat transfer characteristics of multi-inclined hole wall of flame tube and development of one-dimensional wall temperature design program[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010. (in Chinese)
[15]	张效伟,朱惠人,张霞,等. 小尺度孔的流量系数试验[J]. 航空动力学报,2010,25(11): 2479-2485. ZHANG Xiaowei,ZHU Huiren,ZHANG Xia,et al. Experiment of discharge coefficients for small scale cylindrical holes[J]. Journal of Aerospace Power,2010,25(11): 2479-2485. (in Chinese ZHANG Xiaowei, ZHU Huiren, ZHANG Xia, et al. Experiment of discharge coefficients for small scale cylindrical holes[J]. Journal of Aerospace Power, 2010, 25(11): 2479-2485. (in Chinese)
[16]	曹玉璋. 航空发动机传热学[M]. 北京: 北京航空航天大学出版社,2004. CAO Yuzhang. Aeroengine heat transfer[M]. Beijing: Beijing University of Aeronautics & Astronautics Press,2004. (in Chinese CAO Yuzhang. Aeroengine heat transfer[M]. Beijing: Beijing University of Aeronautics & Astronautics Press, 2004. (in Chinese)
[17]	HARRINGTON M K,MCWATERS M A,BOGARD D,et al. Full-coverage film cooling with short normal injection holes[J]. Journal of Turbomachinery,2003,123: 798-805.
[18]	KELLY G B,BOGARD D G. An investigation of the heat transfer for full coverage film cooling: GT 2003-38716[R]. Atlanta,Georgia,US: ASME,2003.
[19]	杨卫华. 某发动机冲击发散复合冷却结构冷却特性试验研究[R]. 北京: 北京动力机械研究所,2018 : 120-122. YANG Weihua. Experimental study on characteristics of combined film and impingement cooling for a certain engine [R]. Beijing,Beijing Power Machinery Institut,2018: 120-122. (in Chinese YANG Weihua. Experimental study on characteristics of combined film and impingement cooling for a certain engine [R]. Beijing, Beijing Power Machinery Institut, 2018: 120-122. (in Chinese)
[20]	胡娅萍,吉洪湖. 孔阵排列疏密度对致密多孔壁冷却效果的影响[J]. 推进技术,2005,26(1): 28-33. HU Yaping,JI Honghu. Effect of porosity of holes array on cooling effectiveness of effusion cooling[J]. Journal of Propulsion Technology,2005,26(1): 28-33. (in Chinese doi: 10.3321/j.issn:1001-4055.2005.01.007 HU Yaping, JI Honghu. Effect of porosity of holes array on cooling effectiveness of effusion cooling[J]. Journal of Propulsion Technology, 2005, 26(1): 28-33. (in Chinese) doi: 10.3321/j.issn:1001-4055.2005.01.007
[21]	李彬,胡正义,林宇震,等. 多斜孔壁整体冷却效率实验研究[J]. 航空动力学报,1999,14(2): 157-160. LI Bin,HU Zhengyi,LIN Yuzhen,et al. An experimental study on overall cooling effectiveness of inclined multihole plates[J]. Journal of Aerospace Power,1999,14(2) : 157-160. (in Chinese LI Bin, HU Zhengyi, LIN Yuzhen, et al. An experimental study on overall cooling effectiveness of inclined multihole plates[J]. Journal of Aerospace Power, 1999, 14(2) : 157-160. (in Chinese)
[22]	金如山,索建秦. 先进燃气轮机燃烧室[M]. 北京: 航空工业出版社,2016. JIN Rushan,SUO Jianqin. Advanced gas turbine combustor[M]. Beijing: Aviation Industry Press,2016. (in Chinese JIN Rushan, SUO Jianqin. Advanced gas turbine combustor[M]. Beijing: Aviation Industry Press, 2016. (in Chinese)