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涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响

樊小倩 汪洋冰 刘一鸣 白杰

樊小倩, 汪洋冰, 刘一鸣, 等. 涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响[J]. 航空动力学报, 2024, 39(9):20230775 doi: 10.13224/j.cnki.jasp.20230775
引用本文: 樊小倩, 汪洋冰, 刘一鸣, 等. 涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响[J]. 航空动力学报, 2024, 39(9):20230775 doi: 10.13224/j.cnki.jasp.20230775
FAN Xiaoqian, WANG Yangbing, LIU Yiming, et al. Effect of throat size of turbine guide on performance of gas turbine starter[J]. Journal of Aerospace Power, 2024, 39(9):20230775 doi: 10.13224/j.cnki.jasp.20230775
Citation: FAN Xiaoqian, WANG Yangbing, LIU Yiming, et al. Effect of throat size of turbine guide on performance of gas turbine starter[J]. Journal of Aerospace Power, 2024, 39(9):20230775 doi: 10.13224/j.cnki.jasp.20230775

涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响

doi: 10.13224/j.cnki.jasp.20230775
基金项目: 集团创新专项(YY20012-02)
详细信息
    作者简介:

    樊小倩(1989-),女,工程师,硕士,研究领域为燃气涡轮起动机设计及涡轮气动热力学。E-mail:wsfxqsydx@163.com

  • 中图分类号: V231.3

Effect of throat size of turbine guide on performance of gas turbine starter

  • 摘要:

    以某燃气涡轮起动机的燃气涡轮导向器为研究对象,采用试验及数值模拟方法研究了燃气涡轮导向器喉道尺寸对燃气涡轮起动机整机及部件性能的影响。针对A、B、C型三种燃气涡轮导向器(喉道平均外径分别为ϕ111.27 mm、ϕ111.94 mm、ϕ112.34 mm)的试验研究结果表明:C'型燃气涡轮起动机较A'型燃气涡轮起动机,正常起动时间缩短14%,失效起动输出轴脱开转速升高7.1%,最大输出功率增加11.6%,起动机性能显著提高。数值结果表明:C''型较A''型涡轮级流量增加3.6%,动力涡轮最大输出功率增加12.2%,动力涡轮功率增加归因于流量增加、温度增加、温降增加的叠加效应。总之,燃气涡轮导向器喉道外径通过影响涡轮级性能改变了燃气涡轮起动机整机的匹配特性,使整机性能存在一定的分散性。

     

  • 图 1  燃气涡轮起动机结构

    Figure 1.  Structural diagram of gas turbine starter

    图 2  起动机核心机

    Figure 2.  Core engine of starter

    图 3  燃气涡轮导向器结构示意图

    Figure 3.  Schematic diagram of gas turbine guide

    图 4  燃气涡轮起动机试验台示意图

    Figure 4.  Schematic diagram of gas turbine starter experimental bench

    图 5  飞轮结构

    Figure 5.  Flywheel struture

    图 6  第一次正常起动输出性能

    Figure 6.  Output performance of the first normal start

    图 7  数值模拟几何模型

    Figure 7.  Numerical simulation geometry model

    图 8  网格S1图

    Figure 8.  grid S1 diagram

    图 9  动力涡轮输出性能

    Figure 9.  Output performance of power turbine

    图 10  沿流向各界面参数变化趋势

    Figure 10.  Trend of parameter changes at various interfaces along the flow direction

    表  1  外径尺寸计量结果

    Table  1.   Outer diameter measurement results

    导向器代号 计量尺寸/mm 设计尺寸/mm
    A ϕ111.18~ϕ111.36 $ {\phi }1{11.6}_{-0.35}^{+0.67} $
    ($ {\phi } $111.25~$ {\phi } $112.27)
    B ϕ111.89~ϕ111.99
    C ϕ112.22~ϕ112.46
    下载: 导出CSV

    表  2  第一次正常起动试验条件

    Table  2.   Conditions for the first normal start experiment

    起动机大气压力/hPa大气温度/K燃气涡轮转速/(r/min)
    A'型1016302.163605
    B'型1018304.663415
    C'型101630263371
    下载: 导出CSV

    表  3  整机性能数据及修正值

    Table  3.   Overall performance data and corrected value

    起动机 序号 起动类型 大气
    压力/hPa
    大气
    温度/K
    起动工作
    时间/s
    燃气涡轮
    转速/(r/min)
    压气机出口
    压力/ hPa
    输出轴脱开
    转速/(r/min)
    最大输出
    功率/kW
    实测 修正 实测 修正 实测 修正 实测 修正 实测 修正
    A'型1正常起动1016302.13330.6636056368019902120568039.8
    2失效起动1016302.758.86364963727198021103038324340.444.7
    3失效起动1015302.658.86367863755201021403062326840.945.3
    4正常起动1017303.133.631636056368519702110575541.8
    B'型1正常起动1018304.630.127.3634156350319202070565544.1
    2失效起动1016305.258.96348863579190020503176341743.348.6
    3失效起动1020304.5596351763604192020703213343344.149
    4正常起动1013307.930.927.5634446354918802060567343.7
    C'型1正常起动101630228.726.3633716344519202050566045.8
    2失效起动1014303.158.6635476362719102050325734734549.9
    3失效起动1015304.258.86351763603190020503245347444.850
    4正常起动1016303.628.225.5634156349818902040567346.6
    下载: 导出CSV

    表  4  试验结果对比

    Table  4.   Comparion of experimental results

    试验参数A'型起动机B'型起动机C'型起动机变化量/%
    正常起动工作时间/s30.627.326.3-14
    失效起动脱开转速/(r/min)3243341734737.1
    最大输出功率/kW44.748.649.911.6
    离心压气机压比3.093.043.02-2.3
    下载: 导出CSV

    表  5  数值计算条件

    Table  5.   Numerical calculation conditions

    参数数值
    环境温度/K288
    环境压力/hPa1013
    离心压气机压比3.2
    燃烧室总压恢复系数0.95
    燃烧室出口温度/K1100
    燃气涡轮转速/(r/min)64000
    下载: 导出CSV

    表  6  最大功率点性能对比

    Table  6.   Comparison of maximum power point performance

    计算参数 A''模型 B''模型 C''模型 变化量/%
    导向器喉道外径/mm $\phi $111.27 $\phi $111.94 $\phi $112.34
    流量$ {W}_{\mathrm{t}\mathrm{h}} $/(kg/s) 0.6425 0.6565 0.6657 3.6
    燃气涡轮出口温度$T_1^* $/K 960.4 964.5 967.3 0.73
    燃气涡轮出口压力$p_1^* $/hPa 1626.2 1661 1684.7 3.6
    燃气涡轮级膨胀比p*/$p_1^* $ 1.894 1.854 1.828 −3.5
    燃气涡轮级温降$ \nabla {T}_{1} $/K 139.6 135.5 132.7 −4.9
    燃气涡轮输出功率/kW 102.9 102.2 101.4 −1.5
    动力涡轮出口温度$T_2^* $/K 887.8 888.2 888.6 0.1
    动力涡轮出口压力$p_2^* $/hPa 1095.1 1097.7 1100 0.45
    动力涡轮级膨胀比$p_1^* $/$p_2^* $ 1.485 1.513 1.532 3.2
    动力涡轮级温降$ \nabla {T}_{2} $/K 72.6 76.3 78.7 8.4
    动力涡轮输出功率/kW 52.6 56.4 59 12.2
    出口总温$T_0^* $/K 887.8 888.2 888.7 0.1
    出口总压$p_0^* $/hPa 1083.5 1085.5 1087.5 0.37
    下载: 导出CSV
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  • 收稿日期:  2023-12-09
  • 网络出版日期:  2024-04-19

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