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航空发动机地面试验激光燃烧诊断技术研究进展

胡志云 叶景峰 张振荣 王晟 李国华 邵珺 陶波 赵新艳 方波浪

胡志云, 叶景峰, 张振荣, 等. 航空发动机地面试验激光燃烧诊断技术研究进展[J]. 实验流体力学, 2018, 32(1): 33-42. doi: 10.11729/syltlx20170135
引用本文: 胡志云, 叶景峰, 张振荣, 等. 航空发动机地面试验激光燃烧诊断技术研究进展[J]. 实验流体力学, 2018, 32(1): 33-42. doi: 10.11729/syltlx20170135
Hu Zhiyun, Ye Jingfeng, Zhang Zhenrong, et al. Development of laser combustion diagnostic techniques for ground aero-engine testing[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(1): 33-42. doi: 10.11729/syltlx20170135
Citation: Hu Zhiyun, Ye Jingfeng, Zhang Zhenrong, et al. Development of laser combustion diagnostic techniques for ground aero-engine testing[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(1): 33-42. doi: 10.11729/syltlx20170135

航空发动机地面试验激光燃烧诊断技术研究进展

doi: 10.11729/syltlx20170135
基金项目: 

国家自然科学基金项目 91541203

国家自然科学基金项目 91641112

详细信息
    作者简介:

    胡志云(1969-), 男, 河南浚县人, 高级工程师。研究方向:燃烧流场激光诊断技术及应用研究。通信地址:陕西西安西北核技术研究所激光与物质相互作用国家重点实验室(710024)。E-mail:huzhiyun@nint.ac.cn

    通讯作者:

    胡志云, E-mail:huzhiyun@nint.ac.cn

  • 中图分类号: O433

Development of laser combustion diagnostic techniques for ground aero-engine testing

  • 摘要: 为了研究湍流燃烧基础问题和改进实际燃烧装置性能,基于激光的燃烧诊断技术已发展成为当前发动机湍流燃烧实验研究的主要测量工具。在已发展的激光燃烧诊断技术中,每种技术都有其局限性和适用范围,需要根据发动机模型燃烧室内部流场测量的要求和特点,选择合适的激光诊断技术。在温度测量中,相干反斯托克斯拉曼散射(CARS)技术主要用于单点温度测量,单脉冲CARS谱测温不确定度优于5%;高时空分辨温度场的测量需要采用双色平面激光诱导荧光(PLIF)测温方法,但其测温精度通常也会相应降低。在速度测量中,粒子成像测速(PIV)技术适用于低速流场速度的精细测量,羟基分子标记测速(HTV)技术适用于高温超声速甚至高超声速流场的速度测量,HTV测速不确定度可优于4%。在组分浓度测量中,主要采用自发拉曼散射(Spontaneous Raman Scattering,SRS)和PLIF技术进行主要组分和中间反应物的浓度分布测量。本文对航空发动机湍流燃烧温度、速度、组分浓度等参量的高时空分辨测量所涉及的激光燃烧诊断技术的基本原理、研究现状和发展趋势进行综述。
  • 图  1  RQL涡轮燃烧室中CARS测温结果[8]

    Figure  1.  The average temperature measurement results of a RQL model combustor stabilized at pressure of 0.70 and 1.03MPa[8]

    图  2  自行研制的高集成度可移动式CARS测温系统示意图

    Figure  2.  Schematic setup for the self-developed, high-integrated and mobile CARS system

    图  3  航空发动机模型燃烧室内部流场平均温度测量结果[3]

    Figure  3.  The average temperature measurement results of an aero-engine model combustor[3]

    图  4  超燃冲压发动机模型燃烧室出口流场温度测量结果[14]

    Figure  4.  The measured temperature versus time at the exit of scramjet engine[14]

    图  5  0.6MPa条件下发动机燃烧室温度场测量结果(a)和CFD计算结果(b)[21]

    Figure  5.  The measured temperature (a) and CFD computation results (b) in the 0.6MPa engine combustor[21]

    图  6  超燃冲压发动机模型燃烧室HTV速度测量方案

    Figure  6.  The schematic setup for the velocity measurement of scramjet model combustor based on HTV technique

    图  7  超燃冲压发动机隔离段(line1)、燃烧室(line2)及出口(line3) 3个马赫数下的速度分布测量结果

    Figure  7.  The measured velocity distribution at three different Mach numbers in the scramjet model combustor

    图  8  航空发动机典型拉曼散射谱(a)及主要组分浓度一维分布结果(b)

    Figure  8.  Typical measured Raman spectrum (a) and measured one-dimensional distribution of major compositions (b) in the aero-engine combustor

    图  9  超燃发动机燃烧室H2燃料燃烧不同剖面温度(a)和O2浓度(b)分布结果[37]

    Figure  9.  The measured temperature (a) and O2 concentration (b) distribution in the hydrogen fueled scramjet combustor[37]

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出版历程
  • 收稿日期:  2017-10-13
  • 修回日期:  2017-12-14
  • 刊出日期:  2018-02-25

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