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燃机总体性能与二次空气系统耦合的过渡态仿真

杨学森 程显达 王天赤 简梦华 董威

杨学森, 程显达, 王天赤, 等. 燃机总体性能与二次空气系统耦合的过渡态仿真[J]. 航空动力学报, 2023, 38(11):2618-2628 doi: 10.13224/j.cnki.jasp.20210376
引用本文: 杨学森, 程显达, 王天赤, 等. 燃机总体性能与二次空气系统耦合的过渡态仿真[J]. 航空动力学报, 2023, 38(11):2618-2628 doi: 10.13224/j.cnki.jasp.20210376
YANG Xuesen, CHENG Xianda, WANG Tianchi, et al. Transient simulation for gas turbine overall performance coupled with secondary air system[J]. Journal of Aerospace Power, 2023, 38(11):2618-2628 doi: 10.13224/j.cnki.jasp.20210376
Citation: YANG Xuesen, CHENG Xianda, WANG Tianchi, et al. Transient simulation for gas turbine overall performance coupled with secondary air system[J]. Journal of Aerospace Power, 2023, 38(11):2618-2628 doi: 10.13224/j.cnki.jasp.20210376

燃机总体性能与二次空气系统耦合的过渡态仿真

doi: 10.13224/j.cnki.jasp.20210376
详细信息
    作者简介:

    杨学森(1992-),男,博士生,主要从事航空发动机性能评估与预测技术研究

    通讯作者:

    董威(1970-),男,教授、博士生导师,博士,主要从事飞机及发动机结冰与防冰研究。E-mail:wdong@sjtu.edu.cn

  • 中图分类号: V231.1

Transient simulation for gas turbine overall performance coupled with secondary air system

  • 摘要:

    为提高燃机过渡态总体性能仿真精度,采用模块化思想建立和完善了二次空气系统精细化模型,提出了燃机总体性能与二次空气系统(SAS)耦合的过渡态仿真方法。以双轴燃机为研究对象建立了仿真算例,模拟并分析了突增、突卸和突甩负荷时二次空气系统各支路引气和汇流的动态变化对总体性能参数的影响。结果表明:通过耦合仿真可以评估燃机运行工况的变化对引气比的作用效果,在突增、突卸负荷时,二次空气系统引气比变化量为0.18%,而对于突甩负荷这种极端工况,引气比的变化量增大至0.55%;燃机主流道与二次空气系统之间的动态交互作用不会显著影响过渡态总体性能参数,但对二次空气系统各支路非均衡响应过程有较大影响,这是现代燃机精细化仿真中不可忽略的因素。

     

  • 图 1  旋转盘腔示意图

    Figure 1.  Schematic of a rotating cavity

    图 2  轮缘封严建模过程

    Figure 2.  Modeling process of rim seal

    图 3  旋转盘腔平均静压响应对比

    Figure 3.  Average static pressure response of the rotating cavity

    图 4  节流孔模型参数化研究

    Figure 4.  Parametric study of the flow restriction orifice model

    图 5  不同压比下的封严流量

    Figure 5.  Seal leakage flow under differernt pressure ratios

    图 6  涡轮叶片冷却模型参数化研究

    Figure 6.  Parametric study of the turbine blade cooling model

    图 7  燃机及其二次空气系统耦合仿真模型

    Figure 7.  Coupled simulation model for a gas turbine and its SAS

    图 8  改进的PID控制器

    Figure 8.  Improved PID controller

    图 9  燃机突增、突卸负荷时引气比变化

    Figure 9.  Variation of mass fractions of cooling air for the gas turbine during sudden load increases and decreases

    图 10  盖板腔静压及油气比变化

    Figure 10.  Static pressure response of the cover-plate cavity and variation of fuel-air ratio

    图 11  叶片壁面温度

    Figure 11.  Blade wall temperature

    图 12  通风支路温升

    Figure 12.  Temperature rise of the ventilation branch

    图 13  动力涡轮转速变化曲线

    Figure 13.  Variation of power turbine speed

    图 14  燃机突增、突卸负荷时压气机共同工作线

    Figure 14.  Operating line of the compressor for the gas turbine during sudden load increases and decreases

    图 15  燃机突甩负荷时引气比变化

    Figure 15.  Varation of mass fractions of cooling air for the gas turbine with a sudden load shedding

    图 16  动力涡轮转速变化曲线

    Figure 16.  Variation of power turbine speed

    图 17  放气阀开度

    Figure 17.  Opening of vent valve

    图 18  燃机突甩负荷时压气机工作线

    Figure 18.  Operating line of the compressor for the gas turbine with a sudden load shedding

    表  1  设计点参数

    Table  1.   Performance parameters at design point

    参数数值
    $ {\dot{m}}_{\mathrm{i}\mathrm{n}\mathrm{l}\mathrm{e}\mathrm{t}} $/(kg/s)36
    ${\varPi }_{\mathrm{c} }$13.6
    ${\varPi }_{\mathrm{t} }$3.9
    ${\varPi }_{\mathrm{p}\mathrm{t} }$3.2
    $ {N}_{\mathrm{h}\mathrm{p}\mathrm{s}} $/(r/min)38143
    $ {N}_{\mathrm{p}\mathrm{t}\mathrm{s}} $/(r/min)20000
    $ P $/kW10000
    $ {v}_{1} $/%2.45
    $ {v}_{2} $/%2.17
    注:${\varPi }_{\mathrm{c} }$为压气机压比,${\varPi }_{\mathrm{t} }$为涡轮落压比,${\varPi }_{\mathrm{p}\mathrm{t} }$为动力涡轮落压比,$ N $为转速,$ P $为燃机输出功率,$ v $为引气比,下标$ \mathrm{h}\mathrm{p}\mathrm{s} $表示高压轴,下标$ \mathrm{p}\mathrm{t}\mathrm{s} $表示动力涡轮轴。
    下载: 导出CSV
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  • 收稿日期:  2021-07-17
  • 网络出版日期:  2023-08-18

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