Volume 36 Issue 5
May  2021
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LIU Tantao, GAO Limin, FENG Xudong. Laws and prediction of axial compressor performance map based on data-driven[J]. Journal of Aerospace Power, 2021, 36(5): 1072-1082. doi: 10.13224/j.cnki.jasp.2021.05.018
Citation: LIU Tantao, GAO Limin, FENG Xudong. Laws and prediction of axial compressor performance map based on data-driven[J]. Journal of Aerospace Power, 2021, 36(5): 1072-1082. doi: 10.13224/j.cnki.jasp.2021.05.018

Laws and prediction of axial compressor performance map based on data-driven

doi: 10.13224/j.cnki.jasp.2021.05.018
  • Received Date: 2021-01-12
  • Publish Date: 2021-05-28
  • To explore the inherent laws of axial compressors’ performance maps, more than 50 axial compressors’ characteristic data were studied based on data analysis and thermodynamic principle. By introducing a variety of thermodynamic parameters into the performance curves and novel performance parameters, the research of laws between physics quantities of compressors was performed from three aspects which were peak efficiency lines, near-surge zones and near-stall zones. The relationship between compressor characteristic parameters and design indicators was found and the prediction algorithm was developed to predict the performance of compressors based on design indicators and performance parameters. It showed that there was a linear relationship between thermodynamics parameters within working speed range. The performance parameters of compressors were obviously correlated with design total pressure ratio and little correlated with design efficiency. The prediction algorithm can predict the performance map of compressors (total pressure ratio less than 8) well just relying on the design indicators and performance parameters without blades geometry information.

     

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  • [1]
    DIXON S L,HALL C A.Fluid mechanics and thermodynamics of turbomachinery[M].7th ed.Oxford,UK:Butterworth-Heinemann,2014.
    [2]
    王占学,王永杰,乔渭阳,等.涡扇发动机低转速部件特性扩展和风车状态性能模拟[J].推进技术,2006,27(2):146-149,181. WANG Zhanxue,WANG Yongjie,QIAO Weiyang,et al.Extrapolating component maps into the low speed and simulation of windmilling performance of turbofan engine[J].Journal of Propulsion Technology,2006,27(2):146-149,181.(in Chinese)
    [3]
    TSOUTSANIS E,LI Y G,PILIDIS P,et al.Part-load performance of gas turbines:Part Ⅰ a novel compressor map generation approach suitable for adaptive simulation[R].Mumbai,Maharashtra,India:ASME Gas Turbine India Conference,2012.
    [4]
    郑洪涛,潘福敏,杨仁.基于面向对象方法的压气机性能计算[J].航空动力学报,2014,29(1):140-145. ZHENG Hongtao,PAN Fumin,YANG Ren.Performance calculation of compressor based on object-oriented method[J].Journal of Aerospace Power,2014,29(1):140-145.(in Chinese)
    [5]
    施洋,屠秋野,严红明,等.一种航空发动机全状态性能模型[J].航空动力学报,2017,32(2):373-381. SHI Yang,TU Qiuye,YAN Hongming,et al.A full states performance model for aero engine[J].Journal of Aerospace Power,2017,32(2):373-381.(in Chinese)
    [6]
    李枚媛,曾德堂,张永军,等.压气机低转速特性外推法改进研究[J].燃气轮机技术,2016,29(3):11-16. LI Meiyuan,ZENG Detang,ZHANG Yongjun,et al.Research on improvement of extrapolating low speed characteristics of compressor[J].Gas Turbine Technology,2016,29(3):11-16.(in Chinese)
    [7]
    KURZKE J.Correlations hidden in compressor maps[R].ASME Paper GT2011-45519,2011.
    [8]
    KURZKE J.Component map extension theoretical considerations and practical advices[R].GPPS (Global Power and Propulsion Society)-CH-2020-0005,2020.
    [9]
    房友龙,刘东风,贺星武,等.压气机特性曲线精确分步拟合方法研究[J].燃气涡轮试验与研究,2019,32(2):21-27. FANG Youlong,LIU Dongfeng,HE Xingwu,et al.Research on the precise step fitting method of compressor characteristic map[J].Gas Turbine Experiment and Research,2019,32(2):21-27.(in Chinese)
    [10]
    TSOUTSANIS E,MESKIN N,BENAMMAR M,et al.A component map tuning method for performance prediction and diagnostics of gas turbine compressors[J].Applied Energy,2014,135(12):572-585.
    [11]
    ZAGOROWSKA M,THORNHILL N.Compressor map approximation using Chebyshev polynomials[R].Valletta,Malta:the 25th Mediterranean Conference on Control and Automation (MED),2017.
    [12]
    黄伟,常俊,孙智滨.基于 MEA-BP 神经网络的压气机特性曲线预测[J].重庆理工大学学报(自然科学),2019,33(2):67-74. HUANG Wei,CHANG Jun,SUN Zhibin.Characteristic curve prediction of compressor based on MEA-BP neural network[J].Journal of Chongqing University of Technology (Natural Science),2019,33(2):67-74.(in Chinese)
    [13]
    蒋爱武,谢寿生.基于支持向量机和粒子群算法的压气机特性计算[J].航空动力学报,2010,25(11):2571-2577. JIANG Aiwu,XIE Shousheng.Method to achieving compressor characteristics based on support vector machine (SVM) and particle swarm optimization (PSO)[J].Journal of Aerospace Power,2010,25(11):2571-2577.(in Chinese)
    [14]
    饶高,苏三买,翟向博.指数外推法和支持向量机相结合的压气机特性扩展方法[J].航空动力学报,2017,32(3):749-755. RAO Gao,SU Sanmai,ZHAI Xiangbo.Method of compressor characteristic extension combining exponent extrapolation method with support vector machine[J].Journal of Aerospace Power,2017,32(3):749-755.(in Chinese)
    [15]
    MIKHAILOVA A B,AKHMEDZYANOV D A,AKHMETOV Y M,et al.Joint prediction of aircraft gas turbine engine axial flow compressor off-design performance and surge line based on the expanded method of generalized functions[J].Russian Aeronautics,2014,57(3):291-296.
    [16]
    AGRAWAL R K,YUNIS M.A generalized mathematical model to estimate gas turbine starting characteristics[R].ASME Paper 81-GT-202,1981.
    [17]
    STEVENSON J D,SARAVANAMUTTOO H I H.Simulating indirect thrust measurement methods for high-bypass turbofans[J].Journal of Engineering for Gas Turbines and Power,1995,117(1):38-46.
    [18]
    GOSTELOW J P,KRABACHER K W,SMITH L H.Performance comparisons of high Mach number compressor rotor blading[R].NASA-CR-1256,1968.
    [19]
    BLANCO R E,HALL C A,CRICHTON D.Challenges in the silent aircraft engine design[R].AIAA 2007-454,2007.
    [20]
    SULAM D H,KEENAN M J,FLYNN J T.Single-stage evaluation of highly-loaded high-Mach-number compressor stages:Ⅱ data and performance,multiple-circular-arc rotor[R].NASA-CR-72694,1970.
    [21]
    CONVERSE G L.Extended parametric representation of compressor fans and turbines:Volume Ⅲ MODFAN user’s manual[R].NASA-CR-174647,1984.
    [22]
    CHENG R,ULTICH W,LAN F,et al.Design and test demonstration of the JET01 six-stage high-pressure compressor[R].ISABE(International Society for Air Breathing Engines) 2007-1184,2007.
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