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推力测量中进气冲量的误差分析与不确定度评定

杨桥 吴锋 王靖元 徐全勇 李红莉

杨桥, 吴锋, 王靖元, 等. 推力测量中进气冲量的误差分析与不确定度评定[J]. 航空动力学报, 2024, 39(10):20220846 doi: 10.13224/j.cnki.jasp.20220846
引用本文: 杨桥, 吴锋, 王靖元, 等. 推力测量中进气冲量的误差分析与不确定度评定[J]. 航空动力学报, 2024, 39(10):20220846 doi: 10.13224/j.cnki.jasp.20220846
YANG Qiao, WU Feng, WANG Jingyuan, et al. Error analysis and uncertainty assessment of intake momentum measurement in thrust test[J]. Journal of Aerospace Power, 2024, 39(10):20220846 doi: 10.13224/j.cnki.jasp.20220846
Citation: YANG Qiao, WU Feng, WANG Jingyuan, et al. Error analysis and uncertainty assessment of intake momentum measurement in thrust test[J]. Journal of Aerospace Power, 2024, 39(10):20220846 doi: 10.13224/j.cnki.jasp.20220846

推力测量中进气冲量的误差分析与不确定度评定

doi: 10.13224/j.cnki.jasp.20220846
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:

    杨桥(1990-),男,工程师,硕士,主要从事航空发动机气动热力学研究

  • 中图分类号: V263.4+5

Error analysis and uncertainty assessment of intake momentum measurement in thrust test

  • 摘要:

    介绍了高空模拟试验中,发动机推力统计需要的进气冲量的测量方法,以及不确定度构成因素。提出了进气冲量测量存在受雷诺数影响的流量系数测定误差和附面层速度损失造成的进气速度计算误差;并对这两项误差的不确定度进行了理论分析。以涡扇发动机飞行包线上的典型工况点为例,开展了数值仿真和试验测量,获得了相应的进气冲量测量不确定度。结果表明:推力测量中进气冲量的不确定度为1.2%~1.4%,由雷诺数偏差引起的流量系数误差以及进气速度的计算误差不可忽视,有必要在校准方法或修正方法中予以考虑。

     

  • 图 1  高空台试验推力计算控制体示意图

    Figure 1.  Thrust measurement diagram and control body

    图 2  三维数值计算模型

    Figure 2.  Three-dimensional numerical computational model

    图 3  流量系数与雷诺数指数的特性曲线

    Figure 3.  Relationship between flow coefficient and Reynolds number index

    图 4  试验舱配置示意图

    Figure 4.  Test chamber configuration

    图 5  流量管内流量测试布局示意图

    Figure 5.  Schematic diagram of flow test layout in flow tube

    图 6  总压测耙示意图

    Figure 6.  Total pressure measuring rake

    图 7  相同高度工况、不同飞行马赫数下气动截面内总压分布

    Figure 7.  Total pressure distribution corresponding to different Mach numbers at the same altitude

    图 8  相同飞行马赫下不同高度条件下的总压分布

    Figure 8.  Total pressure distribution at different altitudes with the same Mach number

    图 9  等飞行马赫数条件下流量系数与雷诺数指数的特性曲线

    Figure 9.  Relationship between flow coefficient and Reynolds number index under constant Mach number conditions

    图 10  某型涡扇发动机包线图

    Figure 10.  Flight envelope of a turbofan engine

    图 11  进气冲量占总推力的百分比(最大状态)

    Figure 11.  Relative contribution of inlet momentum to gross thrust (maximum power)

    图 12  各参数的相对标准不确定度

    Figure 12.  Relative standard uncertainty of each parameter

    表  1  进气流量试验气流参数表

    Table  1.   Test parameters of intake mass flow test

    Ma pt/kPa Tt/K Re/106 IRe
    0.3 80 280 4.98 0.82
    65 280 4.04 0.67
    50 280 3.11 0.51
    35 280 2.18 0.36
    20 280 1.24 0.20
    15 280 0.93 0.15
    12 280 0.75 0.12
    0.4 80 280 6.44 0.82
    65 280 5.23 0.67
    50 280 4.02 0.51
    35 280 2.82 0.36
    20 280 1.61 0.20
    15 280 1.21 0.15
    12 280 0.97 0.12
    下载: 导出CSV
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出版历程
  • 收稿日期:  2022-11-04
  • 网络出版日期:  2024-02-18

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