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封严腔泄漏流对压气机性能影响的试验研究

吴森林 赵正 王文琪 高杰 黄宇轩

吴森林, 赵正, 王文琪, 等. 封严腔泄漏流对压气机性能影响的试验研究[J]. 航空动力学报, 2025, 40(6):20230036 doi: 10.13224/j.cnki.jasp.20230036
引用本文: 吴森林, 赵正, 王文琪, 等. 封严腔泄漏流对压气机性能影响的试验研究[J]. 航空动力学报, 2025, 40(6):20230036 doi: 10.13224/j.cnki.jasp.20230036
WU Senlin, ZHAO Zheng, WANG Wenqi, et al. Experimental investigation of the influence of seal cavity leakage on a compressor performance[J]. Journal of Aerospace Power, 2025, 40(6):20230036 doi: 10.13224/j.cnki.jasp.20230036
Citation: WU Senlin, ZHAO Zheng, WANG Wenqi, et al. Experimental investigation of the influence of seal cavity leakage on a compressor performance[J]. Journal of Aerospace Power, 2025, 40(6):20230036 doi: 10.13224/j.cnki.jasp.20230036

封严腔泄漏流对压气机性能影响的试验研究

doi: 10.13224/j.cnki.jasp.20230036
基金项目: 四川省科技计划项目(2022JDRC0013)
详细信息
    作者简介:

    吴森林(1979-),男,研究员,硕士,主要从事压气机性能评定与试验技术研究。E-mail:40744118@qq.com

  • 中图分类号: V231.3

Experimental investigation of the influence of seal cavity leakage on a compressor performance

  • 摘要:

    以两台单级压气机为试验对象,分别采用调节压气机进口节流比和封严腔供气压力两种方式,开展了封严腔泄漏流对压气机性能影响的试验研究,获取了封严腔泄漏流对压气机性能影响规律。研究结果表明:随着压气机进口节流比的降低或封严腔压力的增加,封严空气泄漏量逐渐增大,但增幅变化逐渐变得缓慢;随着封严空气泄漏量的增加,压气机出口叶根区域主流压力逐渐降低、叶片尾迹区增大,压气机性能逐渐降低;当试验件存在多封严腔供气时,与前封严腔相比,后封严腔空气泄漏对压气机效率影响较大,且随着转速升高影响程度增大。

     

  • 图 1  试验件封严结构示意图

    Figure 1.  Schematic diagram of the seal cavity structure of compressor

    图 2  封严空气泄漏量随篦齿压差变化曲线

    Figure 2.  Curve of seal cavity leakage flow rate versus pressure difference of cavity

    图 3  封严空气泄漏量对流量压比特性影响

    Figure 3.  Influence of the seal cavity leakage flow rate on the compressor ratio characteristics

    图 4  封严空气泄漏量对效率特性影响

    Figure 4.  Influence of the seal cavity leakage flow rate on the compressor efficiency characteristics

    图 5  峰值效率随封严空气泄漏量的变化曲线

    Figure 5.  Curve of seal cavity leakage flow rate versus peak efficiency

    图 6  2#试验件叶片表面静压分布

    Figure 6.  Static pressure on blade of the 2# compressor

    图 7  封严空气泄漏量对出口总压分布影响

    Figure 7.  Influence of the seal cavity leakage flow rate on the total pressure distribution at the outlet

    图 8  泄漏量对叶排静压升的影响

    Figure 8.  Influence of the seal cavity leakage flow rate on the static pressure rise of blades rows

    表  1  封严篦齿参数

    Table  1.   Sealing grate parameters

    试验件 前齿数 前齿间隙/mm 后齿数 后齿间隙/mm
    1# 3 1.0 3 2.0
    2# 2 0.96 2 0.82
    下载: 导出CSV

    表  2  不同封严压差下的泄漏量

    Table  2.   Leakage under different sealing pressure difference

    试验件 n/% K Δp/kPa 相对泄漏量/%
    1# 95 0.931 p1=26.7 W1=0.5
    1# 95 0.658 p1=46.3 W1=0.6
    1# 95 0.660 p1=46.7 W1=1.9
    1# 95 0.506 p1=59.1 W1=2.8
    2# 90 0.985 p1=15.0 W1=0.8
    2# 90 0.985 p1=31.4 W1=1.4
    2# 90 0.985 p1=53.9 W1=2.4
    2# 90 0.985 p2=5.5 W2=0.2
    2# 90 0.985 p2=51.2 W2=2.3
    2# 90 0.985 p2=75.6 W2=3.2
    2# 90 0.985 p2=90.4 W2=3.6
    2# 60 0.995 p2=17.0 W2=0.8
    2# 60 0.995 p2=35.9 W2=2.2
    2# 60 0.995 p2=53.9 W2=3.7
    下载: 导出CSV
  • [1] 秦鹏译. 轴流压气机气动设计[M]. 北京: 国防工业出版社,1975: 37-40. QIN Peng. Axial flow compressor aerodynamic design [M]. Beijing: National Defense Industry Press,1975: 37-40. (in Chinese

    QIN Peng. Axial flow compressor aerodynamic design [M]. Beijing: National Defense Industry Press, 1975: 37-40. (in Chinese)
    [2] 陈光. 遄达1000发动机的设计特点[J]. 航空发动机,2009,35(4): 1-6. CHEN Guang. Design characteristics of Trent 1000[J]. Aeroengine,2009,35(4): 1-6. (in Chinese doi: 10.3969/j.issn.1672-3147.2009.04.001

    CHEN Guang. Design characteristics of Trent 1000[J]. Aeroengine, 2009, 35(4): 1-6. (in Chinese) doi: 10.3969/j.issn.1672-3147.2009.04.001
    [3] 王雄,王小珏,王恩天. 某型发动机轴承封严圈设计改进技术研究[J]. 装备制造技术,2013(4): 82-84. WANG Xiong,WANG Xiaojue,WANG Entian. Technical improvement of sealing ring design of certain type of engine bearing[J]. Equipment Manufacturing Technology,2013(4): 82-84. (in Chinese doi: 10.3969/j.issn.1672-545X.2013.04.031

    WANG Xiong, WANG Xiaojue, WANG Entian. Technical improvement of sealing ring design of certain type of engine bearing[J]. Equipment Manufacturing Technology, 2013(4): 82-84. (in Chinese) doi: 10.3969/j.issn.1672-545X.2013.04.031
    [4] 王永明,顾杨,向宏辉. 航空发动机风扇压气机试验[M]. 北京: 科学出版社,2022: 57-58. WANG Yongming,GU Yang,XIANG Honghui. Aeroengine fan compressor test[M]. Beijing: Science Press,2022: 57-58. (in Chinese

    WANG Yongming, GU Yang, XIANG Honghui. Aeroengine fan compressor test[M]. Beijing: Science Press, 2022: 57-58. (in Chinese)
    [5] MAILACH R,LEHMANN I,VOGELER K. Rotating instabilities in an axial compressor originating from the fluctuating blade tip vortex[J]. Journal of Turbomachinery,2001,123(3): 453-460.
    [6] 王昊,屠宝锋. 叶尖泄漏流对压气机稳定性影响的数值分析[J]. 航空动力学报,2021,36(2): 320-328. WANG Hao,TU Baofeng. Numerical analysis of tip leakage flow effect on compressor stability[J]. Journal of Aerospace Power,2021,36(2): 320-328. (in Chinese

    WANG Hao, TU Baofeng. Numerical analysis of tip leakage flow effect on compressor stability[J]. Journal of Aerospace Power, 2021, 36(2): 320-328. (in Chinese)
    [7] 王鹏飞,刘玉芳,郭文,等. 高转速对直通型篦齿封严特性影响的试验研究[J]. 燃气涡轮试验与研究,2007,20(2): 45-48. WANG Pengfei,LIU Yufang,GUO Wen,et al. Influence of high rotational speeds on the labyrinth sealing characteristics[J]. Gas Turbine Experiment and Research,2007,20(2): 45-48. (in Chinese doi: 10.3969/j.issn.1672-2620.2007.02.010

    WANG Pengfei, LIU Yufang, GUO Wen, et al. Influence of high rotational speeds on the labyrinth sealing characteristics[J]. Gas Turbine Experiment and Research, 2007, 20(2): 45-48. (in Chinese) doi: 10.3969/j.issn.1672-2620.2007.02.010
    [8] 王锁芳,吕海峰. 转静态封严篦齿流场的数值分析和封严特性的试验[J]. 航空动力学报,2005,20(3): 444-449. WANG Suofang,LÜ Haifeng. Numerical analysis of flow and experimental investigation of labyrinth sealing characteristicsat rotational and static states[J]. Journal of Aerospace Power,2005,20(3): 444-449. (in Chinese doi: 10.3969/j.issn.1000-8055.2005.03.020

    WANG Suofang, LÜ Haifeng. Numerical analysis of flow and experimental investigation of labyrinth sealing characteristicsat rotational and static states[J]. Journal of Aerospace Power, 2005, 20(3): 444-449. (in Chinese) doi: 10.3969/j.issn.1000-8055.2005.03.020
    [9] KONG Xiaozhi,LIU Gaowen,LIU Yuxin,et al. Experimental testing for the influences of rotation and tip clearance on the labyrinth seal in a compressor stator well[J]. Aerospace Science and Technology,2017,71: 556-567.
    [10] PONCET S,CHAUVE M P,SCHIESTEL R. Batchelor versus Stewartson flow structures in a rotor-stator cavity with throughflow[J]. Physics of Fluids,2005,17(7): 075110.
    [11] WELLBORN S R,OKIISHI T H. The influence of shrouded stator cavity flows on multistage compressor performance[J]. Journal of Turbomachinery,1999,121(3): 486-497.
    [12] KATO D,YAMAGAMI M,TSUCHIYA N,et al. The influence of shrouded stator cavity flows on the aerodynamic performance of a high-speed multistage axial-flow compressor: GT2011-46300 [R]. Vancouver: ASME,2011.
    [13] YAMAGAMI M,KODAMA H,KATO D,et al. Unsteady flow effects in a high-speed multistage axial compressor: GT2009-59583[R]. Orlando: ASME ,2009.
    [14] YAMAGAMI M,KODAMA H,KATO D,et al. CFD modeling effects on unsteady multistage simulation for a transonic axial compressor: GT2011-46198 [R]. Vancouver: ASME Paper ,2011.
    [15] KATO D,YAMAGAMI M,TSUCHIYA N,et al. The influence of shrouded stator cavity flows on the aerodynamic performance of a high-speed multistage axial-flow compressor: GT2011-46300 [R]. Vancouver,Canada: ASME Turbo Expo: Turbine Technical Conference and Exposition,2011.
    [16] 宁方飞,徐力平. 叶根间隙泄漏流对跨声压气机转子性能的影响[J]. 推进技术,2004,25(4): 325-328,342. NING Fangfei,XU Liping. Numerical investigation of the effect of hub leakage flow on transonic compressor rotor[J]. Journal of Propulsion Technology,2004,25(4): 325-328,342. (in Chinese doi: 10.3321/j.issn:1001-4055.2004.04.009

    NING Fangfei, XU Liping. Numerical investigation of the effect of hub leakage flow on transonic compressor rotor[J]. Journal of Propulsion Technology, 2004, 25(4): 325-328, 342. (in Chinese) doi: 10.3321/j.issn:1001-4055.2004.04.009
    [17] 马文生,禄堃,顾春伟. 压气机静叶气封几何优化与流动分析[J]. 工程热物理学报,2009,30(8): 1288-1290. MA Wensheng,LU Kun,GU Chunwei. Compressor stator seal cavity geometry optimization and flow analysis[J]. Journal of Engineering Thermophysics,2009,30(8): 1288-1290. (in Chinese doi: 10.3321/j.issn:0253-231X.2009.08.008

    MA Wensheng, LU Kun, GU Chunwei. Compressor stator seal cavity geometry optimization and flow analysis[J]. Journal of Engineering Thermophysics, 2009, 30(8): 1288-1290. (in Chinese) doi: 10.3321/j.issn:0253-231X.2009.08.008
    [18] 李想,顾春伟. 轴流压气机带冠静叶和不带冠静叶的比较研究[J]. 清华大学学报(自然科学版),2015,55(12): 1361-1366. LI Xiang,GU Chunwei. Comparison investigation of axial flow compressors with and without shrouded stators[J]. Journal of Tsinghua University (Science and Technology),2015,55(12): 1361-1366. (in Chinese

    LI Xiang, GU Chunwei. Comparison investigation of axial flow compressors with and without shrouded stators[J]. Journal of Tsinghua University (Science and Technology), 2015, 55(12): 1361-1366. (in Chinese)
    [19] 孟德君,邢雷,李坚. 篦齿封严流动及其对压气机静子性能的影响[J]. 航空发动机,2013,39(6): 31-35,42. MENG Dejun,XING Lei,LI Jian. Influence of shrouded stator cavity flow on compressor stator performance[J]. Aeroengine,2013,39(6): 31-35,42. (in Chinese doi: 10.3969/j.issn.1672-3147.2013.06.006

    MENG Dejun, XING Lei, LI Jian. Influence of shrouded stator cavity flow on compressor stator performance[J]. Aeroengine, 2013, 39(6): 31-35, 42. (in Chinese) doi: 10.3969/j.issn.1672-3147.2013.06.006
    [20] 傅鑫,王婉月,张衍,等. 轴流压气机主流在封严篦齿上游容腔内流动结构的数值研究[J]. 兵工自动化,2018,37(7): 83-88. FU Xin,WANG Wanyue,ZHANG Yan,et al. Numerical simulation research of flow structure of axial compressor mainstream in upstream cavity[J]. Ordnance Industry Automation,2018,37(7): 83-88. (in Chinese

    FU Xin, WANG Wanyue, ZHANG Yan, et al. Numerical simulation research of flow structure of axial compressor mainstream in upstream cavity[J]. Ordnance Industry Automation, 2018, 37(7): 83-88. (in Chinese)
    [21] 陈雷. 压气机静子叶根间隙泄漏特性研究[D]. 南京: 南京航空航天大学,2010. CHEN Lei. Study on leakage characteristics of compressor stator blade root clearance[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2010. (in Chinese

    CHEN Lei. Study on leakage characteristics of compressor stator blade root clearance[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010. (in Chinese)
    [22] 夏天,程荣辉,陈仰军. 轴流压气机静子容腔对性能影响的全三维数值模拟[J]. 燃气涡轮试验与研究,2011,24(3): 16-19. XIA Tian,CHENG Ronghui,CHEN Yangjun. Numerical investigation of stator cavity in axial compressor[J]. Gas Turbine Experiment and Research,2011,24(3): 16-19. (in Chinese doi: 10.3969/j.issn.1672-2620.2011.03.005

    XIA Tian, CHENG Ronghui, CHEN Yangjun. Numerical investigation of stator cavity in axial compressor[J]. Gas Turbine Experiment and Research, 2011, 24(3): 16-19. (in Chinese) doi: 10.3969/j.issn.1672-2620.2011.03.005
    [23] 陈美宁,谢伟亮,王红涛. 静子容腔泄漏对某压气机性能影响的数值研究[J]. 航空动力学报,2014,29(11): 2543-2549. CHEN Meining,XIE Weiliang,WANG Hongtao. Numerical investigation of stator cavity leakage influence to a compressor performance[J]. Journal of Aerospace Power,2014,29(11): 2543-2549. (in Chinese

    CHEN Meining, XIE Weiliang, WANG Hongtao. Numerical investigation of stator cavity leakage influence to a compressor performance[J]. Journal of Aerospace Power, 2014, 29(11): 2543-2549. (in Chinese)
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  • 收稿日期:  2023-01-16
  • 网络出版日期:  2025-04-04

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