Volume 37 Issue 4
Apr.  2022
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2022  >  37(4): 815-825
JIN Yun, GENG Shaojuan, WANG Wentao, ZHANG Xiaoyu, ZHANG Hongwu. Design optimization of exit stage rotor with diffuser passage in multi-stage axial compressor[J]. Journal of Aerospace Power, 2022, 37(4): 815-825. doi: 10.13224/j.cnki.jasp.20210175
Citation: JIN Yun, GENG Shaojuan, WANG Wentao, ZHANG Xiaoyu, ZHANG Hongwu. Design optimization of exit stage rotor with diffuser passage in multi-stage axial compressor[J]. Journal of Aerospace Power, 2022, 37(4): 815-825. doi: 10.13224/j.cnki.jasp.20210175
shu

Design optimization of exit stage rotor with diffuser passage in multi-stage axial compressor

doi: 10.13224/j.cnki.jasp.20210175
  • 1.

    Advanced Gas Turbine Laboratory，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

  • 2.

    Innovation Academy for Light-duty Gas Turbine，Chinese Academy of Sciences，Beijing 100190，China

  • 3.

    Key Laboratory of Advanced Energy and Power，Chinese Academy of Sciences，Beijing 100190，China

  • 4.

    School of Engineering Science，University of Chinese Academy of Sciences，Beijing 100049，China

  • Received Date: 2021-04-15
  • Publish Date: 2022-04-28
    Abstract
  • In order to improve the aerodynamic performance of the rear stages of multi-stage axial compressor，an in-house optimization design platform for diffuser passage compressors based on genetic algorithm and neural network surrogate model was built and applied into the optimization design of an exit rotor with diffuser passage.Impacts of the design parameters on efficiency and stability improvement were analyzed based on optimization database.Two optimized diffuser passage designs were selected from the optimization solution set and their influencing rules and mechanisms on efficiency and stability were further studied.Results showed that application of diffuser passage design can improve the load coefficient by 12.1% and efficiency by 1.28% at design mass flow rate，the improvement of stall margin by 12.50% can also be obtained.According to the local entropy generation rate model，the loss of the upper and lower endwalls of the diffuser passage rotor was increased compared with the origin rotor，whereas the loss of profile was reduced. The main reason for stall margin increase of the diffuser passage rotor was the decrease of blockage coefficient near the stall point.

     

    • FullText(HTML)
  • loading
    • References(23)
  • [1]
    WISLER D C.E Advanced compressor and fan systems[M].New York,USA:GE （General Electric） Aircraft Engine Business Group,1985.
    [2]
    BAGHDADI S,Modeling tip clearance effects in multistage axial compressors[J].Journal of Turbomachinery,1996,118（4）:613-843.
    [3]
    WISLER D C.Core compressor exit stage study：VolumeⅠ data and performance report for the best configuration[R].NASA CR-165357,R81AEG314,1981.
    [4]
    WISLER D C.Core compressor exit stage study:Volume Ⅵ final report[R].NASA CR-16555,R81AEG288,1981.
    [5]
    桂幸民.航空压气机气动热力学理论与应用[M].上海:上海交通大学出版社,2014.
    [6]
    FUNATOGAWA O.Research and technology development in Japanese environmentally compatible engine for small aircraft project[R].Munich,Germany:the 17th International Society for Air Breathing Engines Conference,2005.
    [7]
    阳诚武.高负荷轴流压气机叶顶端区流动及调控方法研究[D].北京:中国科学院,2015.
    [8]
    KATO D,GOTO S,MUROOKA T,et al.Development of diffuser passage compressor for improved performance robustness against tip clearance flows[R].Tokyo,Japan:the 9th International Gas Turbine Congress,2007.
    [9]
    KATO D,PALLOT G,SATO D,et al.Development of a highly loaded axial flow compressor for small core size aircraft engines[R].Osaka,Japan:the 10th International Gas Turbine Congress,2011.
    [10]
    YANG Chengwu,HAN Ge,ZHAO Shengfeng,et al.Design and test of a novel highly-loaded compressor[R].ASME Paper GT2019-91181,2019.
    [11]
    赵清伟,潘若痴.一种高负荷叶型优化设计方法[J].航空动力学报,2016,31（12）:3017-3025.
    [12]
    罗明,左志涛,李弘扬,等.基于BP人工神经网络的离心压气机叶轮多目标优化设计方法[J].航空动力学报,2016,31（10）:2424-2431.
    [13]
    周创鑫,成金鑫,黄松,等.基于贝塞尔曲面参数化方法的1.5级高负荷轴流压气机气动优化[J].航空动力学报,2021,36（4）:673-686.
    [14]
    DENTON J D.Loss mechanisms in turbomachines[J].Journal of Turbomachinery,1993,115（4）:621-656.
    [15]
    KOCH C C,SMITH L H.Loss sources and magnitudes in axial-flow compressors[J].Journal of Engineering for Power,1976,98（3）:411-424.
    [16]
    KOCK F,HERWIG H.Local entropy production in turbulent shear flows:a high-Reynolds number model with wall functions[J].International Journal of Heat and Mass Transfer,2004,47（10/11）:2205-2215.
    [17]
    KOCK F,HERWIG H.Entropy production calculation for turbulent shear flows and their implementation in CFD codes[J].International Journal of Heat and Mass Transfer,2005,26（4）:672-680.
    [18]
    李志远.RANS-LES混合方法轴流压气机数值模拟及熵产损失模型构建[D].北京:中国科学院,2017.
    [19]
    LI Zhiyuan,DU Juan,JEMCOY A,et al.A study of loss mechanism in a linear compressor cascade at the corner stall condition[R].ASME Paper GT2017-65192,2017.
    [20]
    MOORE J,MOORE J G.Entropy generation rates from viscous flow calculation:Part 1 a turbulent boundary layer[R].ASME Paper 1983-GT-70,1983.
    [21]
    张千丰.高负荷斜流压气机叶顶间隙流动与轴向缝处理机匣的非定常作用机理研究[D].北京:中国科学院,2020.
    [22]
    KHALID S A,KHALSA A S,WAITZ I A,et al.Endwall blockage in axial compressors[J].Journal of Turbomachinery,1999,121（3）:499-509.
    [23]
    SUDER K L.Blockage development in a transonic axial compressor rotor[J].Journal of Turbomachinery,1998,120（3）:465-476.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(2259.0KB)
    XML

    Article Metrics

    Article views (443) PDF downloads(135) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return