高温强余旋非均匀来流生成规律数值研究

刘云鹏; 张举星; 李伟; 颜应文

doi:10.13224/j.cnki.jasp.20220138

高温强余旋非均匀来流生成规律数值研究

doi: 10.13224/j.cnki.jasp.20220138

南京航空航天大学能源与动力学院，南京 210016

基金项目: 国家科技重大专项（J2019-Ⅲ-0004-0047)

详细信息

作者简介:
刘云鹏（1992-），男，讲师、硕士生导师，博士，主要从事燃烧室燃烧技术相关研究。E-mail：ypliu@nuaa.edu.cn

通讯作者:
颜应文（1978-），男，教授、博士生导师，博士，主要从事航空发动机燃烧技术相关研究。E-mail：yanyw@nuaa.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2022-03-17
- 网络出版日期: 2023-06-01

Numerical simulation on generation law of non-uniform inflow under high temperature and strong cosine rotation condition

College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
对新一代一体化加力燃烧室高温强余旋的进口条件，开展了进口来流生成规律的研究。采用数值计算方法研究了非均匀流场发生装置在不同进口马赫数、余旋角和总温的非均匀流场特性。通过五孔探针的试验测量结果验证了数值模拟的准确性，采用数值模拟方法对流场不均匀指数进行了量化研究。结果表明：随着叶片扭转角度的提高，马赫数不均匀指数逐渐降低；余旋角不均匀指数随着轴向距离和进口马赫数的提高而降低；温度不均匀指数随着马赫数及主流进气温度的升高而升高。此外，发展的拟合公式能够很好地预测关键参数的变化规律，该计算结果可为流场不均匀发生装置的设计和优化提供理论和技术支持。
- 非均匀来流 /
- 高温强余旋 /
- 不均匀指数 /
- 流动数值计算 /
- 一体化加力燃烧室
Abstract:
For the non-uniform inlet conditions of high temperature and strong cosine rotation of the new generation integrated afterburner, the generation law of inlet flow was investigated. The non-uniform flow field characteristics of self-designed non-uniform generator under different inlet Mach numbers, cosine rotation angles and total temperature conditions were studied. The accuracy of the numerical simulation was verified by the experimental measurement results from the five-hole probe, and the numerical simulation method was used to quantify the nonuniformity index of the flow field. Results showed that the Mach number non-uniformity index decreased with the increase of blade torsion angle; the cosine rotation angle non-uniformity index decreased with the increase of axial distance and inlet Mach number; the temperature non-uniformity index increased with the increase of Mach number and mainstream inlet temperature. In addition, the fitting formula developed could well predict the variation of key parameters. At the same time, the simulation results can provide technical support for the design and optimization of non-uniformity flow generator.
- non-uniform inflow /
- high temperature and strong cosine rotation /
- non-uniformity index /
- flow numerical calculation /
- integrated afterburner

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图 1 耦合不均匀发生装置结构示意图

Figure 1. Structural diagram of coupling non-uniform generator

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图 2 不均匀发生器结构示意图

Figure 2. Structural diagram of non-uniform generator

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图 3 计算域模型示意图

Figure 3. Diagram of calculation domain model

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图 4 网格划分

Figure 4. Meshing scheme

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图 5 测量截面中心径向曲线的余旋角度分布比较

Figure 5. Comparison of the distribution of the cosine rotation angle of the radial curve of the measured section center

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图 6 余旋角定义

Figure 6. Definition of cosine rotation angle

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图 7 试验和数值计算径向余旋角和马赫数对比

Figure 7. Comparison of radial rotation angle and Mach number between experimental and numerical calculations

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图 8 组合不均匀流场发生装置耦合流场

Figure 8. Coupled flow field of combined non-uniform flow field generator

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图 9 相关变量对马赫数不均匀指数的影响规律

Figure 9. Influence of related variables on Mach number non-uniformity index

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图 10 马赫数不均匀指数经验公式和数值仿真对比

Figure 10. Comparison between empirical formula and numerical simulation of Mach number non-uniformity index

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图 11 相关变量对余旋角不均匀指数影响规律

Figure 11. Influence of related variables on the index of cosine rotation angle nonuniformity

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图 12 余旋角不均匀指数经验公式和数值仿真对比

Figure 12. Comparison of cosine rotation angle non-uniformity index between empirical formula and numerical simulation

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图 13 相关变量对温度不均匀指数影响规律

Figure 13. Influence of related variables on temperature non-uniformity index

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图 14 温度不均匀指数经验公式和数值仿真对比

Figure 14. Comparison of temperature non-uniform index between empirical formula and numerical simulation

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参考文献(18)

[1]	CLEMENTS T R, GRAVES C B. Augmentor burner: US08/087543 [P]. 1995-01-31.
[2]	邓洪伟,尚守堂,金海,等. 航空发动机隐身技术分析与论述[J]. 航空科学技术,2017,28(10): 1-7. DENG Hongwei,SHANG Shoutang,JIN Hai,et al. Analysis and discussion on stealth technology of aero engine[J]. Aeronautical Science and Technology,2017,28(10): 1-7. (in Chinese)
[3]	林爽,吴榕,郑睿书. 加力燃烧室一体化设计[J]. 航空动力,2020(6): 31-34. LIN Shuang,WU Rong,ZHENG Ruishu. Integrated design of afterburner[J]. Aerospace Power,2020(6): 31-34. (in Chinese)
[4]	夏姣辉,杨谦,王慧汝,等. 涡扇发动机加力燃烧技术发展分析[J]. 航空动力,2020(4): 17-21. XIA Jiaohui,YANG Qian,WANG Huiru,et al. Development analysis to afterburner combustion technology of turbofan[J]. Aerospace Power,2020(4): 17-21. (in Chinese)
[5]	张孝春,孙雨超,刘涛. 先进加力燃烧室设计技术综述[J]. 航空发动机,2014,40(2): 24-30, 60. ZHANG Xiaochun,SUN Yuchao,LIU Tao. Summary of advanced afterburner design technology[J]. Aeroengine,2014,40(2): 24-30, 60. (in Chinese)
[6]	蒋联友, 李江宁, 赵巍, 等. 余旋对加力燃烧室扩压器流场结构的影响研究[R]. 沈阳: 中国航空学会第8届动力年会, 2014.
[7]	LU H Y,RAMSAY J W,MILLER D L. Noise of swirling exhaust jets[J]. AIAA Journal,1976,16(5): 46-52.
[8]	KOZLOWSKI H, LARKIN M. Energy efficient engine-exhaust mixer model technology report[R]. NASA-CR-165459, 1982.
[9]	文清兰,张琪,舒庆. 进口气流角对加力燃烧室流场的影响分析[J]. 航空科学技术,2021,32(7): 32-38. WEN Qinglan,ZHANG Qi,SHU Qing. Influence analysis of inlet flow angle on the flow field of afterburner[J]. Aeronautical Science and Technolgy,2021,32(7): 32-38. (in Chinese)
[10]	SANDERS D D, NESSLER C, COPENHAVER W W, et al. Computational and experimental evaluation of a complex inlet swirl pattern generation system[R]. Salt Lake City, US: AIAA/SAE/ASEE Joint Propulsion Conference, 2015.
[11]	BUCALO T G, FROHNAPFEL D J, LOWE K T, et al. Streamwise development and turbulence characterization of a twin-vortex inlet distortion for turbofan applications[R]. Atlanta, US: the 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017.
[12]	O’BRIEN W F, BAILEY J. The influence of duct development distance on screen-generated total pressure distortion profiles[R]. San Jose, US: AIAA/SAE/ASEE Joint Propulsion Conference, 2013.
[13]	MACK E K, GILLESPIE J, FROHNAPFEL D J, et al. Pressure screen-steam vane interaction effects on downstream flow distortion pattern[R]. Cincinnati, US: Joint Propulsion Conference, 2018.
[14]	MUNK M,PRIM R. On the multiplicity of steady gas flows having the same streamline pattern[J]. Proceedings of the National Academy of Sciences of the United States of America,1947,33(5): 137-141. doi: 10.1073/pnas.33.5.137
[15]	林爽,吴榕,阮盛伟,等. 不同结构一体化加力燃烧室冷态流场与性能仿真[J]. 飞机设计,2021,41(5): 53-58. LIN Shuang,WU Rong,RUAN Shengwei,et al. Investigation on cold flow field and performance of afterburner with different structures[J]. Aircraft Design,2021,41(5): 53-58. (in Chinese)
[16]	贾翔中,单勇,徐兴平,等. 一体化加力燃烧室冷态流动特性数值研究[J]. 航空动力学报,2021,36(7): 1472-1480. doi: 10.13224/j.cnki.jasp.20200437 JIA Xiangzhong,SHAN Yong,XU Xingping,et al. Numerical study on cold flow characteristics of integrated afterburner[J]. Journal of Aerospace Power,2021,36(7): 1472-1480. (in Chinese) doi: 10.13224/j.cnki.jasp.20200437
[17]	吴榕,阮盛伟,姜琴. 典型结构一体化加力燃烧室性能数值仿真研究[J]. 信息记录材料,2020,21(3): 238-241. WU Rong,RUAN Shengwei,JIANG Qin. Numerical simulation study on performance of typical structure in tegrated after burner[J]. Information Recording Materials,2020,21(3): 238-241. (in Chinese)
[18]	尹成茗,张荣春,樊未军,等. 一种一体化加力燃烧室的数值模拟[J]. 航空动力学报,2018,33(2): 470-476. YIN Chengming,ZHANG Rongchun,FAN Weijun,et al. Numerical simulation on a type of the integrated afterburner[J]. Journal of Aerospace Power,2018,33(2): 470-476. (in Chinese)