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不同燃料RBCC发动机飞/发一体化性能对比分析

杜金峰 贾琳渊 陈玉春 郑思行 郑尚喆

杜金峰, 贾琳渊, 陈玉春, 等. 不同燃料RBCC发动机飞/发一体化性能对比分析[J]. 航空动力学报, 2024, 39(8):20230310 doi: 10.13224/j.cnki.jasp.20230310
引用本文: 杜金峰, 贾琳渊, 陈玉春, 等. 不同燃料RBCC发动机飞/发一体化性能对比分析[J]. 航空动力学报, 2024, 39(8):20230310 doi: 10.13224/j.cnki.jasp.20230310
DU Jinfeng, JIA Linyuan, CHEN Yuchun, et al. Comparative analysis on aircraft and engine integration performance of RBCC engines with different fuels[J]. Journal of Aerospace Power, 2024, 39(8):20230310 doi: 10.13224/j.cnki.jasp.20230310
Citation: DU Jinfeng, JIA Linyuan, CHEN Yuchun, et al. Comparative analysis on aircraft and engine integration performance of RBCC engines with different fuels[J]. Journal of Aerospace Power, 2024, 39(8):20230310 doi: 10.13224/j.cnki.jasp.20230310

不同燃料RBCC发动机飞/发一体化性能对比分析

doi: 10.13224/j.cnki.jasp.20230310
详细信息
    作者简介:

    杜金峰(1991-),男,博士生,主要从事组合发动机总体设计。E-mail:nwpujin@mail.nwpu.edu.cn

    通讯作者:

    贾琳渊(1989-),男,副教授,博士,研究领域为航空发动机总体设计。E-mail:jialinyuan@nwpu.edu.cn

  • 中图分类号: V438

Comparative analysis on aircraft and engine integration performance of RBCC engines with different fuels

  • 摘要:

    为了研究不同燃料火箭基组合循环(rocket based combined cycle,RBCC)发动机总体性能的影响,建立了RBCC发动机准一维总体性能仿真模型,分别研究了以液氧煤油、过氧化氢煤油、液氧甲烷和液氧液氢为燃料的RBCC发动机推力和比冲性能。结合飞/发一体化性能分析模型,研究了不同燃料发动机性能对完成飞行任务能力的影响。结果表明:氢燃料RBCC发动机引射模态推力是煤油燃料RBCC发动机的1.3倍;氢燃料RBCC动力飞行器巡航距离最远,为4470 km;相同的飞行器参数下,过氧化氢煤油燃料RBCC动力飞行器机动性最大。本方法可为RBCC发动机总体性能方案设计和燃料选取提供参考。

     

  • 图 1  RBCC发动机部件示意图

    Figure 1.  RBCC engine component diagram

    图 2  引射掺混控制体

    Figure 2.  Ejection mixing control volume

    图 3  飞行器受力分析

    Figure 3.  Force analysis of aircraft

    图 4  约束分析流程图

    Figure 4.  Constraint analysis process

    图 5  任务分析流程图

    Figure 5.  Task analysis flowchart

    图 6  飞行器升阻特性

    Figure 6.  Lift and drag characteristics of vehicle

    图 7  隔离段与燃烧室参数分布趋势

    Figure 7.  Distribution trend of parameters in isolation section and combustion chamber

    图 8  RBCC发动机飞行轨迹

    Figure 8.  RBCC engine flight trajectory

    图 9  不同燃料RBCC发动机性能

    Figure 9.  RBCC engine performance with different fuels

    图 10  约束分析图

    Figure 10.  Constraint analysis diagram

    图 11  飞行高度与马赫数的关系

    Figure 11.  Relationship between flight altitude and Mach number

    图 12  重量比沿飞行马赫数的变化

    Figure 12.  Variation of weight ratio along the flight Mach number

    图 13  机动性沿飞行马赫数的变化

    Figure 13.  Variation of maneuverability along the flight Mach number

    表  1  发动机设计点参数

    Table  1.   Engine design point parameters

    参 数 数值
    整机参数 空气流量Wa0/(kg/s) 2.0
    整机宽度/m 0.12
    飞行条件 飞行高度H/km 26.5
    飞行马赫数Ma0 6.0
    进气道 出口马赫数Ma2 3.0
    修正马赫数 4.0
    隔离段 高度His/m 0.044
    长度/m 0.30
    火箭 流量/(kg/s) 1
    火箭室压/MPa 3
    燃烧室 扩张段扩张比 1.5/2.0
    当量油气比Φ 1.0
    燃烧效率ηb 0.85
    两段供油比例Φ1/Φ2 1∶4
    尾喷管 底板长度 1.0
    A9/A0 1.5
    扩张角/(°) 15
    下载: 导出CSV

    表  2  不同燃料燃烧特性

    Table  2.   Combustion characteristics of different fuels

    燃料空燃比燃烧热/
    (MJ/kg)
    燃烧单位质量
    空气放热/MJ
    甲烷17.1650.022.91
    煤油14.7043.112.93
    34.48143.03.13
    下载: 导出CSV

    表  3  约束条件

    Table  3.   Constraint conditions

    航段 航段 马赫数Ma 质量比
    1 起飞 0~0.3 0.9
    2 加速爬升 0.3~0.8 0.7
    3 等动压爬升 1.5~6 0.4
    4 巡航 6 0.4
    5 降落 0~0.3 0.3
    下载: 导出CSV

    表  4  高超声速飞行器参数

    Table  4.   Hypersonic vehicle parameters

    参数 ABLV-GT Argus Lazarus GTX RBCC
    起飞质量/t 613.3 270.9 81.6 108.2 325
    结构质量/t 104.4 34.2 18.9 23.4 76.48
    推进剂质量/t 481 223.69 57.6 84.67 248.5
    有效载荷/t 11.34 5.03 2.27 0.136
    空重比 0.197 0.156 0.266 0.216 0.235
    下载: 导出CSV

    表  5  不同RBCC发动机飞/发一体化分析结果

    Table  5.   Analysis results of flight/engine integration for different RBCC engines

    火箭燃料/
    冲压燃料
    煤油+O2/
    煤油
    煤油+H2O2/
    煤油
    CH4+O2/
    CH4
    H2+O2/
    H2
    起飞总重/t 80 80 80 80
    推质比 0.65 0.65 0.65 0.65
    翼载/(N/m2 5000 5000 5000 5000
    机翼面积/m2 156.96 156.96 156.96 156.96
    空重比 0.25 0.25 0.25 0.25
    转场距离/km 1401.58 1936.51 2096.02 5698.68
    总转场时间/min 23.50 27.63 30.08 63.36
    爬升段时间/min 11.55 9.20 12.05 11.92
    总耗油量/t 57.01 57.00 57.00 57.03
    燃料体积/m3 61.51 56.52 95.70 492.40
    巡航距离/km 200 900 860 4470.0
    下载: 导出CSV
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  • 收稿日期:  2023-05-12
  • 网络出版日期:  2024-03-13

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