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可调收敛喷管发动机高空台冲压校准和测量性能近似修正方法

吴锋 刘涛 邓燃 王靖元 徐全勇

吴锋, 刘涛, 邓燃, 等. 可调收敛喷管发动机高空台冲压校准和测量性能近似修正方法[J]. 航空动力学报, 2024, 39(10):20220862 doi: 10.13224/j.cnki.jasp.20220862
引用本文: 吴锋, 刘涛, 邓燃, 等. 可调收敛喷管发动机高空台冲压校准和测量性能近似修正方法[J]. 航空动力学报, 2024, 39(10):20220862 doi: 10.13224/j.cnki.jasp.20220862
WU Feng, LIU Tao, DENG Ran, et al. Investigation of performance approximate revision methods for engine with adjustable convergence nozzle in ram pressure calibration of altitude simulated test[J]. Journal of Aerospace Power, 2024, 39(10):20220862 doi: 10.13224/j.cnki.jasp.20220862
Citation: WU Feng, LIU Tao, DENG Ran, et al. Investigation of performance approximate revision methods for engine with adjustable convergence nozzle in ram pressure calibration of altitude simulated test[J]. Journal of Aerospace Power, 2024, 39(10):20220862 doi: 10.13224/j.cnki.jasp.20220862

可调收敛喷管发动机高空台冲压校准和测量性能近似修正方法

doi: 10.13224/j.cnki.jasp.20220862
基金项目: 中国航发四川燃气涡轮研究院外委课题
详细信息
    作者简介:

    吴锋(1982-),男,研究员,博士生,主要从事航空发动机高空模拟试验技术研究。E-mail:wufeng_my@mail.nwpu.edu.cn

  • 中图分类号: V235.1

Investigation of performance approximate revision methods for engine with adjustable convergence nozzle in ram pressure calibration of altitude simulated test

  • 摘要:

    针对控制规律与海拔高度相关带可调收敛喷管发动机,提出了在冲压条件下进行校准试验的方法。该方法通过冲压与等冲压试验结果比较获得修正系数,实现冲压条件下校准试验结果的近似修正。针对某型涡扇发动机,进行了高空台试验和总体性能仿真,获得了喷管控制偏差时发动机性能变化比例,基于冲压条件下试验结果修正得到了标准海平面条件下发动机性能。该方法表明,冲压条件下进行校准试验的方法是可行的,获取的发动机推力等主要性能参数与出厂试车结果相差小于2.0%。

     

  • 图 1  高空舱冷却次流示意图

    Figure 1.  Secondary cooling air flow in altitude test chamber

    图 2  直连式高空台发动机推力测量控制体示意图

    Figure 2.  Schematic diagram of the control volume of direct connected altitude engine thrust measurement.

    图 3  尾喷管落压比与流量系数的对应关系

    Figure 3.  Relationship of $ {\pi _{\text{n}}} $vs. $ q\left( \lambda \right) $

    图 4  发动机主要性能参数相对低压转速变化量

    Figure 4.  Variety of main parameter about engine performance vary with respect to the rotation speed of the low pressure shaft

    图 5  涡扇发动机混合室模型

    Figure 5.  Exhaust mixer model for turbofan engine

    图 6  发动机共同工作点变化示意图

    Figure 6.  Schematic diagram of the working point of engine

    $ {W_{\text{a}}} $ 空气质量流量(kg/s) Ma 马赫数
    $ {W_{\text{f}}} $ 燃油质量流量(kg/h) $ {F_{\text{g}}} $ 总推力(N)
    A 面积(m2 $ {F_{\text{m}}} $ 测量推力(N)
    p 气体压力(Pa) V 气流速度(m/s)
    T 气体温度(K) 下标
    R 气体常数(J/(kg·K)) t 滞止的,总的
    $ \lambda $ 速度系数 c 规定的飞行状态下
    $ q (\lambda ) $ 流量函数 r 环面的
    H 飞行高度(km) sch 高空舱内的
    下载: 导出CSV

    表  1  发动机主要性能参数差异(nlc=103.86%)

    Table  1.   Main parameters deviation for engine performance (nlc=103.86%)

    参数 相对变化量/%
    $ {n_{{\text{lc}}}} $
    $ {n_{{\text{hc}}}} $ −0.07
    $ {W_{{\text{ac}}}} $ −0.19
    $ {W_{{\text{fc}}}} $ −2.81
    $ {T_{{\text{5c}}}} $ −1.32
    $ {F_{{\text{gc}}}} $ −2.26
    $ {\pi _{\text{f}}} $ −1.61
    下载: 导出CSV

    表  2  A8面积变化发动机仿真计算结果

    Table  2.   Simulate results for engine caused by A8 deviation

    参数 相对变化量/%
    $ {A_8} $ 2.01
    $ {\pi _{\text{f}}} $ −1.45
    $ {n_{\text{h}}} $ −0.37
    $ {T_{\text{5}}} $ −1.05
    $ {W_{\text{f}}} $ −2.78
    $ {F_{\text{g}}} $ −2.09
    下载: 导出CSV

    表  4  修正后的校准试验结果与出厂数据比较

    Table  4.   Revised calibration test results vs. producer data

    参数 相对变化量/%
    $ {n_{{\text{lc}}}} $
    $ {n_{{\text{hc}}}} $ −0.15
    $ {W_{{\text{fc}}}} $ 1.90
    $ {T_{{\text{5c}}}} $ 0.78
    $ {F_{{\text{gc}}}} $ −0.53
    下载: 导出CSV
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出版历程
  • 收稿日期:  2022-11-13
  • 网络出版日期:  2024-05-06

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