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大落差长度比中介机匣气动性能试验及数值模拟

刘建明 郝晟淳 武卉 赵展 张雷 李昊

刘建明,郝晟淳,武卉,等.大落差长度比中介机匣气动性能试验及数值模拟[J].航空动力学报,2022,37(7):1560‑1568. doi: 10.13224/j.cnki.jasp.20210271
引用本文: 刘建明,郝晟淳,武卉,等.大落差长度比中介机匣气动性能试验及数值模拟[J].航空动力学报,2022,37(7):1560‑1568. doi: 10.13224/j.cnki.jasp.20210271
LIU Jianming,HAO Shengchun,WU Hui,et al.Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing[J].Journal of Aerospace Power,2022,37(7):1560‑1568. doi: 10.13224/j.cnki.jasp.20210271
Citation: LIU Jianming,HAO Shengchun,WU Hui,et al.Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing[J].Journal of Aerospace Power,2022,37(7):1560‑1568. doi: 10.13224/j.cnki.jasp.20210271

大落差长度比中介机匣气动性能试验及数值模拟

doi: 10.13224/j.cnki.jasp.20210271
详细信息
    作者简介:

    刘建明(1984-),男,工程师,硕士,研究方向为叶轮机平面叶栅试验和扇形叶栅试验、涡轮级性能试验及CFD。E⁃mail:liujianming_chn@126.com

  • 中图分类号: V231.3

Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing

  • 摘要:

    为了考察中介机匣气动性能水平并验证设计方法,对中介机匣进行了气动性能试验,同时采用NUMECA Fine软件进行了相应的数值模拟。为了准确测量流过中介机匣内涵的气流流量,设计了一种流量测量装置并进行了精度校核,结果表明:测量精度的相对偏差小于1.5%。针对高进口马赫数时在进口平直段上两侧的壁面静压比中间区域小,以及某些涵道比未能调节到目标进口马赫数的情况,进行了相应的数值模拟并提出了解决方案。用单点总压管对内、外涵出口进行了扇面测量,得到了内涵的总性能曲线、总压恢复系数径向变化曲线及内、外涵总压恢复系数云图,并与计算结果进行对比,结果表明:内涵总性能曲线及内、外涵总压恢复系数云图的计算结果与试验结果吻合较好,在设计状态下,内、外涵出口测量截面的总压恢复系数分别为0.992 1、0.986,两数值均高于设计指标,中介机匣具有较好的气动性能。

     

  • 图 1  试验件S1流面示意图

    Figure 1.  Schematic diagram of the experiment specimen S1 flow surface

    图 2  试验件结构图

    Figure 2.  Structure diagram of the experiment specimen

    图 3  试验件

    Figure 3.  Experiment specimen

    图 4  进口壁面静压测点和进口总压管分布

    Figure 4.  Distribution of the inlet wall static pressure measurement points and inlet total pressure probes

    图 5  内涵流量测量装置

    Figure 5.  Measurement device of the core mass flow

    图 6  总流量与内涵流量变化曲线

    Figure 6.  Change curves of the total and the core mass flow

    图 7  进口总压径向变化曲线

    Figure 7.  Radial change curves of inlet total pressure

    图 8  进口壁面静压周向变化曲线

    Figure 8.  Circumferential change curves of inlet wall static pressure

    图 9  中介机匣计算模型

    Figure 9.  Computational model of the intermediate casing

    图 10  外壁静压沿y向变化曲线

    Figure 10.  Static pressure change curves of the outer wall along the y direction

    图 11  50%通道高度马赫数沿y向变化曲线

    Figure 11.  Mach number change curves of the 50% channel height along the y direction

    图 12  内涵内壁壁面静压沿z向测点分布

    Figure 12.  Distribution of static pressure measurement points along the z direction on inner wall of the core

    图 13  内涵内壁等熵马赫数沿z向变化曲线

    Figure 13.  Isentropic Mach number along the z direction change curve of the core inner wall

    图 14  试验所用蝶阀

    Figure 14.  Butterfly valve used in the experiment

    图 15  内涵管道计算模型

    Figure 15.  Computational model of the core tube

    图 16  阀门横截面马赫数分布云图

    Figure 16.  Mach number distribution cloud image of the valve cross section

    图 17  总压恢复系数随进口马赫数变化曲线

    Figure 17.  Change curves of the total pressure recovery coefficient with the inlet Mach number

    图 18  总压恢复系数随涵道比变化曲线

    Figure 18.  Change curves of the total pressure recovery coefficient with the bypass ratio

    图 19  总压恢复系数径向变化曲线

    Figure 19.  Radial change curves of the total pressure recovery coefficient

    图 20  内涵出口总压恢复系数云图(计算结果)

    Figure 20.  Cloud image of the total pressure recovery coefficient at the core outlet (computational result)

    图 21  内涵出口总压恢复系数云图(试验结果)

    Figure 21.  Cloud image of the total pressure recovery coefficient at the core outlet (experimental result)

    图 22  外涵出口总压恢复系数云图(计算结果)

    Figure 22.  Cloud image of the total pressure recovery coefficient at the bypass outlet (computational result)

    图 23  外涵出口总压恢复系数云图(试验结果)

    Figure 23.  Cloud image of the total pressure recovery coefficient at the bypass outlet (experimental result)

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  • 收稿日期:  2021-05-31

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