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过浓系数与对置活塞发动机的燃烧效率

王苏飞 章振宇 张付军

王苏飞, 章振宇, 张付军. 过浓系数与对置活塞发动机的燃烧效率[J]. 航空动力学报, 2024, 39(1):20220147 doi: 10.13224/j.cnki.jasp.20220147
引用本文: 王苏飞, 章振宇, 张付军. 过浓系数与对置活塞发动机的燃烧效率[J]. 航空动力学报, 2024, 39(1):20220147 doi: 10.13224/j.cnki.jasp.20220147
WANG Sufei, ZHANG Zhenyu, ZHANG Fujun. Coefficient of richness and combustion efficiency in opposed-piston engines[J]. Journal of Aerospace Power, 2024, 39(1):20220147 doi: 10.13224/j.cnki.jasp.20220147
Citation: WANG Sufei, ZHANG Zhenyu, ZHANG Fujun. Coefficient of richness and combustion efficiency in opposed-piston engines[J]. Journal of Aerospace Power, 2024, 39(1):20220147 doi: 10.13224/j.cnki.jasp.20220147

过浓系数与对置活塞发动机的燃烧效率

doi: 10.13224/j.cnki.jasp.20220147
详细信息
    作者简介:

    王苏飞(1990-),男,博士生,主要从事内燃机进排气及燃烧方面的研究。E-mail:327633899@qq.com

    通讯作者:

    张付军(1966-),男,教授、博士生导师,博士,主要从事内燃机电控及新概念动力系统相关研究。E-mail:zfj123@bit.edu.cn

  • 中图分类号: V234;TK421

Coefficient of richness and combustion efficiency in opposed-piston engines

  • 摘要:

    针对空气利用率用于描述对置活塞(OP2S)二冲程压燃式发动机油气相互作用规律时局限性较大的问题,给出过浓系数的定义并以之作为对置活塞二冲程压燃式发动机缸内油气混合效果的评价指标。在此基础上通过基于CONVERGE软件的数值模拟研究了初始涡流比和喷油器倾角对OP2S燃烧效率的影响规律。结果表明:过浓系数可以排除平均当量比的影响并有效反映喷油参数对油气混合效果的影响。提高涡流比可以强化喷油过程中的油气混合,同时改变喷油过程形成的燃油径向分布。过小或过大的涡流比使燃油过度集中于气缸轴线附近或气缸壁附近,造成局部过浓,喷油结束后的燃烧效率下降。整个循环的燃烧效率由喷油过程中及喷油结束后的燃烧放热过程共同决定。在所研究的范围内,涡流比对燃油径向分布的影响可以使燃烧效率在0.6~1.0的范围内变化。喷油器倾角同样可以改变燃油径向分布位置及燃烧效率,且这一影响可以与涡流对燃油径向分布规律的影响相叠加。

     

  • 图 1  OP2S气缸结构

    Figure 1.  Cylinder structure of OP2S

    图 2  单元尺寸为1.4~4 mm的计算结果对比

    Figure 2.  Comparison of calculation results from cell size 1.4−4 mm

    图 3  模型验证

    Figure 3.  Model validation

    图 4  计算结束时刻总过浓系数、空气利用率与燃烧效率的关系

    Figure 4.  Correlation between total coefficient of richness, air utilization and combustion efficiency at end of simulation

    图 5  喷油器布置对总过浓系数变化规律的影响

    Figure 5.  Effect of nozzle layout on trend of total coefficient of richness

    图 6  喷油器布置对空气利用率变化规律的影响

    Figure 6.  Effect of nozzle layout on trend of air utilization

    图 7  喷油器倾角为0°时的喷孔布局

    Figure 7.  Nozzle layout when injector yaw is 0°

    图 8  涡流比对总过浓系数变化规律的影响

    Figure 8.  Effect of swirl ratio on trend of total coefficient of richness

    图 9  涡流比对瞬时放热率及燃烧效率变化规律的影响

    Figure 9.  Effect of swirl ratio on trend of heat release rate and combustion efficiency

    图 10  涡流比对曲轴转角为8°(上止点后)时缸内y方向速度分布的影响

    Figure 10.  Effect of swirl ratio on y-velocity distribution at 8° crank angle after TDC (ATDC)

    图 11  涡流比对曲轴转角为16°(上止点后)时缸内当量比分布的影响

    Figure 11.  Effect of swirl ratio on equivalence ratio distribution at 16° crank angle (ATDC)

    图 12  涡流比对曲轴转角为100°(上止点后)时缸内过浓系数的径向分布的影响

    Figure 12.  Effect of swirl ratio on radial distribution of coefficient of richness at 100° crank angle (ATDC)

    图 13  涡流比对燃烧效率的影响机理

    Figure 13.  Mechanism of swirl ratio’s effect on combustion efficiency

    图 14  22.5°喷油器倾角下的喷孔布局

    Figure 14.  Nozzle layout when injector yaw is 22.5°

    图 15  22.5°喷油器倾角下涡流比对总过浓系数变化规律的影响

    Figure 15.  Effect of swirl ratio on trend of total coefficient of richness at injector yaw is 22.5°

    图 16  22.5°喷油器倾角下涡流比对曲轴转角为8°(上止点后)时缸内y方向速度分布的影响

    Figure 16.  Effect of swirl ratio on y-velocity distribution at 8° crank angle (ATDC) and injector yaw is 22.5°

    图 17  22.5°喷油器倾角下涡流比对曲轴转角为16°(上止点后)时缸内当量比分布的影响

    Figure 17.  Effect of swirl ratio on equivalence ratio distribution at 16° crank angle (ATDC) and injector yaw is 22.5°

    图 18  22.5°喷油器倾角下涡流比对曲轴转角为100°(上止点后)时缸内过浓系数的径向分布的影响

    Figure 18.  Effect of swirl ratio on radial distribution of coefficient of richness at 100° crank angle (ATDC) and injector yaw is 22.5°

    表  1  仿真的初始条件及其他参数

    Table  1.   Initiation condition and other parameters of simulation

    参数数值及说明
    上止点后曲轴转角
    (计算起止点)/(°)
    −110~100
    初始压力/MPa0.37
    初始温度/K400
    循环充气量/mg4320
    初始成分质量分数/%21(O2
    79(N2
    喷油压力/MPa177
    喷孔直径/mm0.142
    曲轴转角(喷油持续期)/(°)31.5
    上止点后曲轴转角
    (喷油起始时刻)/(°)
    −15
    燃油模型DIESEL2
    气缸壁温度/K400
    进、排气活塞顶温度/K450
    下载: 导出CSV
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  • 收稿日期:  2022-03-22
  • 网络出版日期:  2023-09-08

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