Wang Feng, Xu Jinglei, Wang Yangsheng. Study of flow field characteristics of an over-under TBCC exhaust system during mode transition process[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(3): 68-75. DOI: 10.11729/syltlx20190037
Citation: Wang Feng, Xu Jinglei, Wang Yangsheng. Study of flow field characteristics of an over-under TBCC exhaust system during mode transition process[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(3): 68-75. DOI: 10.11729/syltlx20190037

Study of flow field characteristics of an over-under TBCC exhaust system during mode transition process

More Information
  • Received Date: January 30, 2019
  • Revised Date: April 08, 2019
  • To study the flow characteristics and aerodynamic performance of an over-under TBCC exhaust system during the mode transition process, the unsteady numerical simulation of the mode transition process is completed by using dynamic grid method. Moreover, a series of cold flow wind tunnel tests of the TBCC exhaust system are carried out under several working conditions during the mode transition process, and the results are compared with the numerical simulation results. The results show that the wave structure of the TBCC exhaust flow field is extremely complex during the mode transition process, and the shock generated at the trailing edge of the splitter plate has some effects on the aerodynamic performance of the exhaust system. The axial thrust coefficient keeps above 0.9, yet the lift varies greatly during the process. The static pressure distribution on the walls and schlieren images obtained by wind tunnel experiments are consistent well with the numerical simulation results, which proves the accuracy of the numerical simulation results in this paper.
  • [1]
    D'Oriano V, Savino R, Visone M. Aerothermodynamic study of a small hypersonic plane[J]. Aircraft Engineering and Aerospace Technology, 2018, 90(2):471-480. DOI: 10.1108/AEAT-06-2015-0151
    [2]
    Wang Z G, Wang Y, Zhang J Q, et al. Overview of the key technologies of combined cycle engine precooling systems and the advanced applications of micro-channel heat transfer[J]. Aerospace Science and Technology, 2014, 39:31-39. DOI: 10.1016/j.ast.2014.08.008
    [3]
    Walker S, Tang M, Mamplata C. TBCC propulsion for a Mach 6 hypersonic airplane[C]. The 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Bremen, Germany. 2013.
    [4]
    Xiang X H, Liu Y, Qian Z S. Aerodynamic design and numerical simulation of over-under turbine-based combined-cycle (TBCC) inlet mode transition[J]. Procedia Engineering, 2015, 99:129-136. DOI: 10.1016/j.proeng.2014.12.516
    [5]
    刘晓波, 罗月培, 曾慧, 等.国外TBCC关键技术及试验设备研究综述[J].燃气涡轮试验与研究, 2016, 29(4):51-56. DOI: 10.3969/j.issn.1672-2620.2016.04.011

    Liu X B, Luo Y P, Zeng H, et al. An overview of key technology and test facility for turbine-based combined cycle propulsion study oversea[J]. Gas Turbine Experiment and Research, 2016, 29(4):51-56. DOI: 10.3969/j.issn.1672-2620.2016.04.011
    [6]
    Edwards C L W, Small W J, Weidner J P, et al. Studies of scramjet/airframe integration techniques for hypersonic aircraft[C]//Proc of the 13th Aerospace Sciences Meeting. 1975.
    [7]
    Walker S, Tang M, Mamplata C. TBCC propulsion for a Mach 6 hypersonic airplane[C]//The 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2013: 7238.
    [8]
    Zhang M Y, Wang Z X, Liu Z W, et al. Analysis of mode transition performance for a tandem TBCC engine[C]. The 52nd AIAA/SAE/ASEE Joint Propulsion Conference. Salt Lake City, USA. 2016.
    [9]
    Liu J, Yuan H C, Guo R W. Unsteady flow characteristic analysis of turbine based combined cycle (TBCC) inlet mode transition[J]. Propulsion and Power Research, 2015, 4(3):141-149. DOI: 10.1016/j.jppr.2015.07.006
    [10]
    Guo S, Xu J L, Mo J W, et al. Fluid-structure interaction study of the splitter plate in a TBCC exhaust system during mode transition phase[J]. Acta Astronautica. 2015, 112:126-139. DOI: 10.1016/j.actaastro.2015.03.021
    [11]
    花文达, 徐惊雷.三维并联式TBCC发动机排气系统设计与实验[J].航空动力学报, 2018, 33(9):2268-2277. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201809025

    Hua W D, Xu J L.Design approach and experiment of three-dimensional over/under TBCC exhaust system[J]. Journal of Aerospace Power, 2018, 33(9):2268-2277. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201809025
    [12]
    牛彦沣, 徐惊雷, 许保成, 等.并联TBCC排气系统流场结构数值模拟及实验研究[J].推进技术, 2017, 38(12):2686-2691. http://d.old.wanfangdata.com.cn/Periodical/tjjs201712006

    Niu Y F, Xu J L, Xu B C, et al. Numerical and experimental study of over-under TBCC exhaust system flow structure[J]. Journal of Propulsion Technology, 2017, 38(12):2686-2691. http://d.old.wanfangdata.com.cn/Periodical/tjjs201712006
    [13]
    Lv Z, Xu J L, Mo J W. Study of the unsteady mode transition process for an over-under TBCC exhaust system[J]. Acta Astronautica, 2017, 136:259-272. DOI: 10.1016/j.actaastro.2017.03.020
    [14]
    Cai Y H, Zhang J D, Wang Z X. Exploring TBCC engine inlet design for Ma=5[J]. Jounal of Northwestern Polytechnical Univercity, 2007, 25(5):615-619.
    [15]
    Steelant J. LAPCAT:high-speed propulsion technology[J]. Advances on Propulsion Technology for High-Speed Aircraft, 2008, 12(1):1-38. http://d.old.wanfangdata.com.cn/NSTLHY/NSTL_HYCC0214754156/
    [16]
    隋洪涛.精通CFD动网格工程仿真与案例实战[M].北京:人民邮电出版社, 2013.
  • Related Articles

    [1]Zhou Bo, Gao Chuan, Yang Yang. Study on varying dynamic pressure control of flow field in 2m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(6): 72-77. DOI: 10.11729/syltlx20180133
    [2]HUANG Ming-qi, LAN Bo, YANG Yong-dong, PENG Xian-min. Φ5m[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(5): 94-97. DOI: 10.3969/j.issn.1672-9897.2013.05.018
    [3]CHU Wei-hua, TANG Geng-sheng, WANG fan. Research and realization on the control strategies of the 2m× 2m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(5): 98-102. DOI: 10.3969/j.issn.1672-9897.2012.05.021
    [4]LI Ping, RUI Wei, QIN Jian-hua, TANG Liang, ZHOU Bo. Development of measurement and operation management system in 2m×2m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(4): 96-100. DOI: 10.3969/j.issn.1672-9897.2012.04.020
    [5]ZHOU Ping, CHANG Tian-yi, WANG Fan, JIANG Tie-deng, GUO Shou-chun, SHENG Hong, YANG Xiao-song. The control system design of the high attack angle mechanism for the 8m × 6m wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(3): 78-81,96. DOI: 10.3969/j.issn.1672-9897.2011.03.017
    [6]RUI Wei, YI Fan, DU Ning, QIN Jian-hua. Design and realization of TPS measurement and control system for 2.4m transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2008, 22(4): 72-75. DOI: 10.3969/j.issn.1672-9897.2008.04.016
    [7]LIN Qi, LIANG Bin, ZHENG Ya-qing. Control on model attitude and oscillation by wire-driven parallel manipulator support system for low-speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2008, 22(3): 75-79. DOI: 10.3969/j.issn.1672-9897.2008.03.017
    [8]A new control system of CTS device and its application in 1.2m high speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2003, 17(1): 32-35. DOI: 10.3969/j.issn.1672-9897.2003.01.008
    [9]Rebuilding control and measurement system of CG-01 wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2002, 16(3): 57-62. DOI: 10.3969/j.issn.1672-9897.2002.03.010
    [10]LI Shang-chun, LI Ling, LI Rong-yu, QI Gang. The Choke finger control system of 1.2m×1.2m trans-supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2001, 15(1): 88-92. DOI: 10.3969/j.issn.1672-9897.2001.01.016
  • Cited by

    Periodical cited type(0)

    Other cited types(1)

Catalog

    Article Metrics

    Article views (330) PDF downloads (25) Cited by(1)
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return
    x Close Forever Close