Volume 37 Issue 6
Dec.  2023
Turn off MathJax
Article Contents
LI Q F, LI M, GAO X, et al. Experimental study on characteristic calibration of separated exhaust system[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 61-69 doi: 10.11729/syltlx20220056
Citation: LI Q F, LI M, GAO X, et al. Experimental study on characteristic calibration of separated exhaust system[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 61-69 doi: 10.11729/syltlx20220056

Experimental study on characteristic calibration of separated exhaust system

doi: 10.11729/syltlx20220056
  • Received Date: 2022-06-27
  • Accepted Date: 2022-10-19
  • Rev Recd Date: 2022-10-12
  • Available Online: 2022-12-06
  • Publish Date: 2023-12-25
  • In flight testing, the aeroengine flight thrust is indirectly obtained by the gas generator method. In order to improve the calculation accuracy of the flight thrust, it is necessary to accurately obtain the characteristics of the exhaust system. The laboratory calibration test and numerical simulation research were carried out by using the large bypass ratio separated exhaust system scale model. The results show that: the core nozzle characteristics obtained by the two methods are consistent, and the values are close. When the maximum core nozzle pressure ratio is 1.44, the deviations of the mass flow and the thrust are 0.73% and 0.18%, respectively; the characteristics of the separated exhaust system obtained by the two methods have the same trend and close values. When the max bypass nozzle pressure ratio equals 1.46, the deviations of the mass flow and the thrust are 0.64% and 0.18%, respectively; when the physical model and geometric model of the large bypass ratio separated exhaust system are reasonably simplified, the characteristic deviations of the separated exhaust system obtained by the two methods are in good agreement.
  • loading
  • [1]
    李新建, 齐海帆, 潘鹏飞. 某型分排涡扇发动机尾喷管特性影响参数研究[J]. 工程与试验, 2016, 56(1): 36–40, 84. doi: 10.3969/j.issn.1674-3407.2016.01.010

    LI X J, QI H F, PAN P F. Research on influencing parameters of jet nozzle characteristic of a certain type of turbofan engine[J]. Engineering & Test, 2016, 56(1): 36–40, 84. doi: 10.3969/j.issn.1674-3407.2016.01.010
    [2]
    ASBURY S C, YETTER J A. Static performance of a wing-mounted thrust reverser concept[C]//Proc of the 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhi-bit. 1998: 3256. doi: 10.2514/6.1998-3256
    [3]
    高扬, 姜健, 屈霁云. 航空燃气涡轮发动机飞行推力确定[M]. 北京: 航空工业出版社, 2019.
    [4]
    刘晓波, 孙宗祥, 钟萍, 等. 国外航空发动机空气动力学研究概况[J]. 燃气涡轮试验与研究, 2013, 26(4): 58–62. doi: 10.3969/j.issn.1672-2620.2013.04.013

    LIU X B, SUN Z X, ZHONG P, et al. An overview of aero-engine aerodynamics overseas research[J]. Gas Turbine Experiment and Research, 2013, 26(4): 58–62. doi: 10.3969/j.issn.1672-2620.2013.04.013
    [5]
    HOLST K R. A method for performance analysis of a ramjet engine in a free-jet test facility and analysis of performance uncertainty contributors[D]. Knoxville: University of Tennes-see Knoxville, 2012.
    [6]
    ONERA. Annual report 2021[R/OL]. (2021) [2022-11-12]. https://www.onera.fr/sites/default/files/ressources_documentaires/RA-2021-VA.pdf.
    [7]
    MASSONNAT J-M, COTON T. Development in turbine testing at ONERA[C]//Proc of the 27th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. 2010.
    [8]
    MODANE-AVRIEUX CENTER OF ONERA. BD2 Nozzle Thrust Measurement Bench[R/OL]. (2018) [2022-11-12]. https://www.onera.fr/sites/default/files/windtunnel/pdf/BD2%20test%20bench%20version%202018.pdf.
    [9]
    MODANE-AVRIEUX CENTER OF ONERA. TPS and nozzle mass flow and thrust measurements [R/OL]. (2004) [2022-11-12]. https://www.onera.fr/sites/default/files/windtunnel/pdf/S4B.pdf.
    [10]
    BURCHAM F W Jr. An investigation of two variations of the gas generator method to calculate the thrust of the afterburning turbofan engines installed in an F-111A air-plane[R]. NASA TN D-6297, 1971.
    [11]
    KURTENBACH F J, BURCHAM F W Jr. Flight evalua-tion of a simplified gross thrust calculation technique using an F100 turbofan engine in an F-15 airplane[R]. NASA-TP-1782, 1981.
    [12]
    RAY R J, COBLEIGH B R, VACHON M J, et al. Flight test techniques used to evaluate performance benefits during formation flight[C]//Proc of the AIAA Atmospheric Flight Mechanics Conference and Exhibit. 2002: 4492. doi: 10.2514/6.2002-4492
    [13]
    何成军, 李建强, 黄江涛, 等. 非对称超声速喷管内流动分离非定常特性[J]. 航空学报, 2022, 43(1): 302–312. doi: 10.7527/S1000-6893.2020.24930

    HE C J, LI J Q, HUANG J T, et al. Unsteadiness of flow separation in an asymmetric supersonic nozzle[J]. Acta Aero-nautica et Astronautica Sinica, 2022, 43(1): 302–312. doi: 10.7527/S1000-6893.2020.24930
    [14]
    刘福海, 朱荣, 董凯, 等. 拉瓦尔喷管结构模式对超音速射流流动特性的影响[J]. 工程科学学报, 2020, 42(S1): 54–59. doi: 10.13374/j.issn2095-9389.2020.03.15.s15

    LIU F H, ZHU R, DONG K, et al. Effect of Laval nozzle structure on behaviors of supersonic oxygen jet flow field[J]. Chinese Journal of Engineering, 2020, 42(S1): 54–59. doi: 10.13374/j.issn2095-9389.2020.03.15.s15
    [15]
    孙鹏, 周莉, 王占学. 出口宽高比对双涵道S弯喷管流动特性的影响[J]. 推进技术, 2022, 43(6): 122–132. doi: 10.13675/j.cnki.tjjs.201033

    SUN P, ZHOU L, WANG Z X. Effects of aspect ratio on flow characteristic of serpentine nozzle for turbofan[J]. Journal of Propulsion Technology, 2022, 43(6): 122–132. doi: 10.13675/j.cnki.tjjs.201033
    [16]
    何成军, 李建强, 范召林, 等. 单边膨胀喷管内流动分离非定常特性[J]. 航空动力学报, 2019, 34(11): 2339–2346. doi: 10.13224/j.cnki.jasp.2019.11.005

    HE C J, LI J Q, FAN Z L, et al. Flow separation unsteadiness in single expansion ramp nozzle[J]. Journal of Aerospace Power, 2019, 34(11): 2339–2346. doi: 10.13224/j.cnki.jasp.2019.11.005
    [17]
    孙鹏, 周莉, 王占学, 等. 双S弯喷管的流固耦合特性研究[J]. 推进技术, 2022, 43(10): 158–167. doi: 10.13675/j.cnki.tjjs.210349

    SUN P, ZHOU L, WANG Z X, et al. Fluid-structure interaction characteristic of double serpentine nozzle[J]. Journal of Propulsion Technology, 2022, 43(10): 158–167. doi: 10.13675/j.cnki.tjjs.210349
    [18]
    周莉, 孟钰博, 王占学. S弯收扩喷管流动特性数值研究[J]. 推进技术, 2021, 42(1): 103–113,2. doi: 10.13675/j.cnki.tjjs.200271

    ZHOU L, MENG Y B, WANG Z X. Numerical study on flow characteristics of serpentine convergent-divergent nozzle[J]. Journal of Propulsion Technology, 2021, 42(1): 103–113,2. doi: 10.13675/j.cnki.tjjs.200271
    [19]
    汪文杰, 王占学, 周莉, 等. 大涵道比短舱/排气系统耦合影响的数值研究[J]. 工程热物理学报, 2019, 40(9): 1981–1987.

    WANG W J, WANG Z X, ZHOU L, et al. A numerical simulation on the coupled influence of the high bypass ratio nacelle and exhaust system[J]. Journal of Engineering Thermophysics, 2019, 40(9): 1981–1987.
    [20]
    张睿琳, 周莉, 王占学, 等. S弯喷管喷流噪声特性研究[J]. 推进技术, 2022, 43(7): 185–193. doi: 10.13675/j.cnki.tjjs.210049

    ZHANG R L, ZHOU L, WANG Z X, et al. Jet noise characteristics of S-shaped nozzle[J]. Journal of Propulsion Technology, 2022, 43(7): 185–193. doi: 10.13675/j.cnki.tjjs.210049
    [21]
    罗明东, 吉洪湖, 黄伟, 等. 无加力涡扇发动机二元喷管的红外辐射特性实验[J]. 航空动力学报, 2006, 21(4): 631–636. doi: 10.13224/j.cnki.jasp.2006.04.003

    LUO M D, JI H H, HUANG W, et al. An experimental investigation on infrared radiation characteristics of 2-D nozzles of turbofan engine afterburner[J]. Journal of Aero-space Power, 2006, 21(4): 631–636. doi: 10.13224/j.cnki.jasp.2006.04.003
    [22]
    额日其太, 王强, 陈渭鹏. 两种涡扇发动机排气系统红外辐射特性的比较[J]. 推进技术, 2003, 24(4): 334–336, 367. doi: 10.13675/j.cnki.tjjs.2003.04.013

    ERIQITAI, WANG Q, CHEN W P. Comparative investi-gation of the infrared characteristics for two exhaust systems of a turbofan engine[J]. Journal of Propulsion Technology, 2003, 24(4): 334–336, 367. doi: 10.13675/j.cnki.tjjs.2003.04.013
    [23]
    宫禹. 涡扇发动机排气系统红外隐身实验装置的总体设计及性能仿真研究[D]. 南京: 南京航空航天大学, 2007.

    GONG Y. Design and performance simulation of an experimental rig for infrared stealth research of exhaust system of a turbofan engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2007.
    [24]
    是介, 周莉, 史经纬, 等. 三轴承矢量喷管红外辐射特性[J]. 航空动力学报, 2022, 37(6): 1195–1205. doi: 10.13224/j.cnki.jasp.20210268

    SHI J, ZHOU L, SHI J W, et al. Infrared radiation signature of three bearing swivel nozzle[J]. Journal of Aerospace Power, 2022, 37(6): 1195–1205. doi: 10.13224/j.cnki.jasp.20210268
    [25]
    蒋建峰, 征建生. 锯齿矢量喷管气动和红外辐射特性研究[J]. 激光与红外, 2022, 52(2): 234–239. doi: 10.3969/j.issn.1001-5078.2022.02.014

    JIANG J F, ZHENG J S. Research on aerodynamic and infrared signature of vectoring nozzle with chevron[J]. Laser & Infrared, 2022, 52(2): 234–239. doi: 10.3969/j.issn.1001-5078.2022.02.014
    [26]
    宋宇, 杨青真, 高翔, 等. 介质涂覆位置对二元塞式喷管的电磁散射特性影响[J]. 推进技术, 2022, 43(11): 161–168. doi: 10.13675/j.cnki.tjjs.210509

    SONG Y, YANG Q Z, GAO X, et al. Electromagnetic scattering characteristics of binary plug nozzle with coating medium at different part[J]. Journal of Propulsion Techno-logy, 2022, 43(11): 161–168. doi: 10.13675/j.cnki.tjjs.210509
    [27]
    高翔, 高扬, 朱彦伟. 某型混合排气涡扇发动机喷管特性计算方法研究[J]. 机械研究与应用, 2017, 30(1): 1–4. doi: 10.16576/j.cnki.1007-4414.2017.01.001

    GAO X, GAO Y, ZHU Y W. Study on nozzle characteristics computation method of a mixed exhaust turbofan engine[J]. Mechanical Research & Application, 2017, 30(1): 1–4. doi: 10.16576/j.cnki.1007-4414.2017.01.001
    [28]
    高翔, 高扬, 李密. 基于响应面法的混合排气涡扇发动机喷管特性研究[J]. 航空科学技术, 2016, 27(11): 19–24. doi: 10.3969/j.issn.1007-5453.2016.11.004

    GAO X, GAO Y, LI M. Research on nozzle characteristics of a mixed exhaust turbofan engine based on response surface methodology[J]. Aeronautical Science & Technology, 2016, 27(11): 19–24. doi: 10.3969/j.issn.1007-5453.2016.11.004
    [29]
    邵万仁. 基于数值模拟的轴对称矢量喷管内流特性研究[J]. 航空动力学报, 2008, 23(5): 52–59. doi: 110.13224/j.cnki.jasp.2008.05.009

    SHAO W R. Study of internal performance for an axisym-metric vectoring exhaust nozzle using numerical simulation[J]. Journal of Aerospace Power, 2008, 23(5): 52–59. doi: 110.13224/j.cnki.jasp.2008.05.009
    [30]
    李秋锋, 李密, 王定奇. 测量耙对小尺寸发动机性能影响的研究[J]. 测控技术, 2022, 41(3): 38–43. doi: 10.19708/j.ckjs.2022.03.007

    LI Q F, LI M, WANG D Q. Research on the effect of measuring rake on performance of the small-size engine[J]. Measurement & Control Technology, 2022, 41(3): 38–43. doi: 10.19708/j.ckjs.2022.03.007
    [31]
    李宁. 二元矢量喷管气动特性数值模拟[C]//北京力学会第二十三届学术年会会议论文集. 2017: 147–150.
    [32]
    王殿磊, 叶留增, 汪东, 等. 不同宽高比的二元收–扩喷管内流特性数值研究[C]//探索 创新 交流(第7集)——第七届中国航空学会青年科技论坛文集(上册). 2016: 365–369.
    [33]
    白伟, 高为民, 任智博, 等. 喷管面积比对推力矢量发动机特性的影响[J]. 航空动力学报, 2021, 36(7): 1426–1433. doi: 10.13224/j.cnki.jasp.20210129

    BAI W, GAO W M, REN Z B, et al. Influences of nozzle area ratio on thrust vector engine characteristic[J]. Journal of Aerospace Power, 2021, 36(7): 1426–1433. doi: 10.13224/j.cnki.jasp.20210129
    [34]
    汤伟, 刘李涛, 陈洪, 等. 矢量喷管推力特性的风洞试验技术[J]. 航空动力学报, 2018, 33(4): 858–864. doi: 10.13224/j.cnki.jasp.2018.04.011

    TANG W, LIU L T, CHEN H, et al. Thrust characteristics test technique of vectoring nozzle in wind tunnel[J]. Journal of Aerospace Power, 2018, 33(4): 858–864. doi: 10.13224/j.cnki.jasp.2018.04.011
    [35]
    陈雪冬, 唐贵明, 王发民. 用于脉冲风洞的热喷流实验方法初步研究[C]//第八届全国实验流体力学学术会议论文集. 2010: 195–204.
    [36]
    B. A. 索苏诺夫, B. M. 切普金. 航空发动机和动力装置的原理、计算及设计[Z]. 莫斯科国立航空学院, 2003: 424–423.
    [37]
    史经纬. 固定几何气动矢量喷管流动机理及性能评估技术研究[D]. 西安: 西北工业大学, 2015.

    SHI J W. Investigation on flow mechanism and performance estimation of fixed-geometric thrust vectoring nozzle[D]. Xi'an: Northwestern Polytechnical University, 2015.
    [38]
    ABERNETHY R B, ADAMS G R, ASCOUGH J C, et al. In-flight thrust determination[R]. SAE AIR 1703, 1986: 48–54.
    [39]
    廉筱纯, 吴虎. 航空发动机原理[M]. 西安: 西北工业大学出版社, 2005: 16–17.
    [40]
    李秋锋, 李密, 高翔. 测量耙对尾喷管内流流场性能参数的影响[J]. 现代机械, 2017(6): 29–33. doi: 10.13667/j.cnki.52-1046/th.2017.06.008

    LI Q F, LI M, GAO X. Influence of measurement rake on performance parameters of internal flow field in nozzle[J]. Modern Machinery, 2017(6): 29–33. doi: 10.13667/j.cnki.52-1046/th.2017.06.008
    [41]
    高扬. ARJ21–700飞机飞行推力确定(IFTD)技术论文[G]. 中国飞行试验研究院, 2011.
    [42]
    战培国. 美国AIAA风洞试验不确定度评定标准研究[J]. 标准科学, 2014(1): 68–71.

    ZHAN P G. Research on American AIAA standard of assessment uncertainty for wind tunnel testing[J]. Standard Science, 2014(1): 68–71.
    [43]
    朱新新, 隆永胜, 赵顺洪, 等. 基于总温探针的高精度总焓测量方法优化研究[J]. 实验流体力学, doi: 10.11729/syltlx20210149.

    ZHU X X, LONG Y S, ZHAO S H, et al. Optimization of total enthalpy measurement method based on the total temperature probe[J]. Journal of Experiments in Fluid Mechanics, doi: 10.11729/syltlx20210149.
    [44]
    ABERNETHY R B, ADAMS G R, STEURER J W. Uncertainty of in-flight thrust determination[R]. SAE AIR 1678, 1986: 23–26.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Figures(15)  / Tables(4)

    Article Metrics

    Article views (207) PDF downloads(24) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return