Research on the layout scheme for the axial compressor in the 0.6 m continuous transonic wind tunnel

CHEN Jiming; LEI Pengfei; LIAO Daxiong; ZHENG Juan; CONG Chenghua; WANG Yitian

doi:10.11729/syltlx20190034

Volume 34 Issue 4

Aug. 2020

Turn off MathJax

Article Contents

Abstract

References

Journal of Experiments in Fluid Mechanics > 2020 > 34(4): 68-73. > DOI: 10.11729/syltlx20190034

CHEN Jiming, LEI Pengfei, LIAO Daxiong, ZHENG Juan, CONG Chenghua, WANG Yitian. Research on the layout scheme for the axial compressor in the 0.6 m continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(4): 68-73. DOI: 10.11729/syltlx20190034

Citation:

PDF (4603 KB)

Research on the layout scheme for the axial compressor in the 0.6 m continuous transonic wind tunnel

1.
Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Facility Design and Instrumentation Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
3.
Xi'an Shangu Power Co. Ltd., Xi'an 710075, China

More Information

Received Date: January 07, 2019
Revised Date: April 10, 2019

Graphical Abstract

Abstract

Abstract

As the driving system of continuous transonic wind tunnel, compressor's matching design, which considered its operating performance and the general performance of wind tunnel, is one of the key technologies in wind tunnel design. With the development of large continuous transonic and supersonic wind tunnel, the compressor trends to have larger power, higher energy efficiency, wider range, higher precision and so on. The layout scheme of the axial compressor in the 0.6 m continuous transonic wind tunnel, which is a pilot wind tunnel for large transonic wind tunnel, is studied. The location and the scheme of the main compressor are analyzed from the aspects of aerodynamic performance, structural design and control. Also, the integrated design of the wind tunnel and compressor is important for the sake of efficiency. By performance test of compressor in the 0.6 m continuous transonic wind tunnel, while the compressor arranged between the first and the second corner, the feasibility of the layout scheme of external motors and two-end drive, the synchronous control of multi motors and the rectification technology of the compressor's internal flow path is validated. All the compressor's operating performance indicators can fulfill the design-technology requirements well. The studies provide technical support for the construction of large scale continuous transonic wind tunnel.
- continuous wind tunnel,
- axial compressor,
- transonic wind tunnel,
- layout scheme,
- integrated design

FullText(HTML)

References (15)

References

[1]	GUNN J A, MARTINDALE W R, WAGNER D R. Performance evaluation of a transonic wind tunnel compressor[R]. AIAA-92-3927, 1992.
[2]	MABEY D G. Some remarks on the design of transonic tunnels with low levels of flow unsteadiness[R]. NASA CR-2722, 1976.
[3]	WOLF T. State of the art in circuit loss analysis of transonic wind tunnels[C]//Proc of the 20th AIAA Advanced Measurement and Ground Testing Technology Conference. 1998.
[4]	廖达雄, 陈吉明, 郑娟, 等. 0.6 m连续式跨声速风洞总体性能[J].实验流体力学, 2018, 32(6):88-93 http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=ltlxsyycl201806012 LIAO D X, CHEN J M, ZHENG J, et al. General performance of 0.6 m continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(6):88-93 http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=ltlxsyycl201806012
[5]	廖达雄, 陈吉明, 彭强, 等.连续式跨声速风洞设计关键技术[J].实验流体力学, 2011, 25(4):74-78. http://www.syltlx.com/CN/abstract/abstract10640.shtml LIAO D X, CHEN J M, PENG Q, et al. Key design techniques of the low noise continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(4):74-78. http://www.syltlx.com/CN/abstract/abstract10640.shtml
[6]	周恩民, 程松, 许靖, 等. 0.6 m连续式跨声速风洞AV90-3轴流压缩机喘振边界测试研究[J].实验流体力学, 2014, 28(5):81-85. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=ltlxsyycl201405014 ZHOU E M, CHENG S, XU J, et al. Surge margin test and research of AV90-3 axial compressor in 0.6 m continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2014, 28(5):81-85. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=ltlxsyycl201405014
[7]	熊波, 周恩民, 程松, 等. 0.6 m连续式风洞调试运行关键技术研究.实验流体力学, 2016, 30(4):81-86. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=ltlxsyycl201604014 XIONG B, ZHOU E M, CHENG S, et al. Research on key technologies of debugging and operating in 0.6 m×0.6 m continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(4):81-86. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=ltlxsyycl201604014
[8]	李红喆, 廖达雄, 丛成华.连续式跨声速风洞大开角段整流装置设计数值模拟[J].空气动力学学报, 2015, 33(2):198-203. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb201502009 LI H Z, LIAO D X, CONG C H. Numerical simulation of flow conditioning device design in wide angle diffuser of continuous transonic wind tunnels[J]. Acta Aerodynamica Sinica, 2015, 33(2):198-203. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb201502009
[9]	周恩民, 张文, 刘恺, 等. E71-3离心压缩机热力性能试验研究[J].风机技术, 2015, 57(6):39-43, 48. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=fjjs201506007 ZHOU E M, ZHANG W, LIU K, et al. Thermodynamic performance test and research of E71-3 centrifugal compressor[J]. Compressor, Blower & Fan Technology, 2015, 57(6):39-43, 48. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=fjjs201506007
[10]	刘恺, 周恩民, 张文, 等.连续式高速风洞压缩机转速测量装置研制与应用[J].电气传动, 2017, 47(2):60-64. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=dqcd201702013 LIU K, ZHOU E M, ZHANG W, et al. Development and application of compressor speed measurement device in continuous high speed wind tunnel[J]. Electric Drive, 2017, 47(2):60-64. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=dqcd201702013
[11]	李一滨, 乔志德.增压连续式跨声速风洞防喘振措施:旁路调节的研究[J].流体力学实验与测量, 2001, 15(4):53-58. http://www.cnki.com.cn/Article/CJFDTotal-LTLC200104010.htm LI Y B, QIAO Z D. The study of application of by-pass to prevent surging in pressurized continuous wind tunnel[J]. Experiments and Measurements in Fluid Mechanics, 2001, 15(4):53-58. http://www.cnki.com.cn/Article/CJFDTotal-LTLC200104010.htm
[12]	波普, 戈因.高速风洞试验[M].邓振瀛, 李廷林, 译.北京: 科学出版社, 1980. POPE A, GOIN K L. High-speed wind tunnel testing[M]. DENG Z Y, LI T L, translated. Beijing: Science Press, 1980.
[13]	陈天君.浅谈轴流压缩机和离心压缩机的喘振试验[J].化学工业与工程技术, 2007, 28(S1):120-122. http://www.cnki.com.cn/Article/CJFDTotal-HXGJ2007S1039.htm
[14]	雷剑宇, 廖明夫, 杨伸记.预测风机喘振边界的新方法[J].风机技术, 2005, 47(4):52-53, 57. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=fjjs200504019 LEI J Y, LIAO M F, YANG S J. New method of predicting surge lines of fan[J]. Compressor, Blower & Fan Technology, 2005, 47(4):52-53, 57. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=fjjs200504019
[15]	中国人民解放军总装备部.低速风洞和高速风洞流场品质要求: GJB 1179A-2012[S].北京: 总装备部军标出版发行部, 2012.

[1]	ZHANG Xuhui, WANG Zhaowei, YAO Ran. The aerodynamic heating consistency study between CFD and experiment for air-breathing integrated vehicle[J]. Journal of Experiments in Fluid Mechanics, 2025, 39(1): 45-53. DOI: 10.11729/syltlx20220041
[2]	CHEN Zhenhua, LIU Zongzheng, CHEN Jiming, GUO Shouchun, YAN Xiqiang, PEI Haitao. Characteristics and key technology analysis of large continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(1): 62-68. DOI: 10.11729/syltlx20210092
[3]	LONG Bingxiang, LIU Zongzheng, CHEN Zhenhua, CHEN Jiming, LEI Pengfei. Aerodynamic and aero-acoustic design of continuous transonic wind tunnel compressor[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(1): 27-36. DOI: 10.11729/syltlx20210079
[4]	Zheng Xiaogang, Li Zhonglong, Li Yiqing, Zhang Xu, Zhu Chengxiang, You Yancheng. Integrated design and experimental research for curved fore-body and 3D inward turning inlet[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 28-35, 48. DOI: 10.11729/syltlx20190019
[5]	Qiao Wenyou, Yu Anyuan. Overview on integrated design of inward-turning inlet with aircraft forebody[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(3): 43-59. DOI: 10.11729/syltlx20190028
[6]	Ding Feng, Liu Jun, Shen Chibing, Liu Zhen, Chen Shaohua, Huang Wei. An overview of waverider design concept in airframe-inlet integration methodology for air-breathing hypersonic vehicles[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(6): 16-26. DOI: 10.11729/syltlx20180080
[7]	Deng Fan, Ye Youda, Jiao Zihan, Liu Hui. Research on HIFiRE project's hypersonic vehicle integrated design of aerodynamic and scramjet propulsion[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(2): 73-80. DOI: 10.11729/syltlx20160125
[8]	HE Wei, YU Shi-en, LI Hong-Bing. Experimental investigation on thrust-drag performance of hypersonic integrative vehicle[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(2): 65-68. DOI: 10.3969/j.issn.1672-9897.2010.02.014
[9]	CHE Jing, TANG Shuo. Research of airframe/scramjet integrated design of hypersonic vehicle[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(2): 41-44,49. DOI: 10.3969/j.issn.1672-9897.2006.02.008
[10]	Integrative design of supersonic inlet and missile body[J]. Journal of Experiments in Fluid Mechanics, 2004, 18(4): 28-33. DOI: 10.3969/j.issn.1672-9897.2004.04.007

Cited By

Cited by

Periodical cited type(5)

1.	时文，田野，郭明明，刘源，张辰琳，钟富宇，乐嘉陵. 乙烯燃料超燃燃烧室流动特性与燃烧稳定性研究. 力学学报. 2022(03): 612-621 .
2.	钟富宇，冉伟，田野，于欣，彭江波，乐嘉陵. 超燃冲压发动机自点火条件下波系演化规律试验研究. 推进技术. 2022(12): 191-199 .
3.	钟富宇，乐嘉陵，田野，岳茂雄. 乙烯燃料超燃冲压发动机燃烧过程研究. 实验流体力学. 2021(01): 34-43 . 本站查看
4.	李素芬，林姿含，东明. 凹腔结构对氢气超声速燃烧影响数值模拟. 热科学与技术. 2021(04): 395-402 .
5.	刘冰，何国强，秦飞. 乙烯高速射流点火过程试验研究. 实验流体力学. 2018(02): 24-27 . 本站查看

Other cited types(1)

Get Citation

PDF

XML

Article Metrics

Article views (208) PDF downloads (18) Cited by(6)

Research on the layout scheme for the axial compressor in the 0.6 m continuous transonic wind tunnel

Abstract

References

Related Articles

Cited by

Periodical cited type(5)

Other cited types(1)

Catalog

Article Metrics

Related

Research on the layout scheme for the axial compressor in the 0.6 m continuous transonic wind tunnel

Abstract

References

Related Articles

Cited by

Periodical cited type(5)

Other cited types(1)

Catalog

Article Metrics

Related

Export File

Citation

Format

Content