Volume 31 Issue 12
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ZHAO Yong, LI Ben-wei, SONG Han-qiang, SUN Tao. Assembled method for estimation of turbofan engine high pressure turbine inlet temperature[J]. Journal of Aerospace Power, 2016, 31(12): 3026-3033. doi: 10.13224/j.cnki.jasp.2016.12.027
Citation: ZHAO Yong, LI Ben-wei, SONG Han-qiang, SUN Tao. Assembled method for estimation of turbofan engine high pressure turbine inlet temperature[J]. Journal of Aerospace Power, 2016, 31(12): 3026-3033. doi: 10.13224/j.cnki.jasp.2016.12.027
shu

Assembled method for estimation of turbofan engine high pressure turbine inlet temperature

doi: 10.13224/j.cnki.jasp.2016.12.027

  • 1. Department of Airborne Vehicle Engineering, Naval Aeronautical and Astronautical University, Yantai Shandong 264001, China;

  • 2. Unit 91331, the Chinese People's Liberation Army, Xingcheng Liaoning 125100, China

  • Received Date: 2015-03-30
  • Publish Date: 2016-12-28
    Abstract
  • Considering that direct and reliable measurement of high pressure turbine inlet temperature on board is not feasible at present, a new assembled method for estimation of turbofan engine high pressure turbine inlet temperature was proposed. Based on the energy conservation principles of a turbofan engine, thermodynamic equations between high pressure turbine inlet temperature and other gas path parameters were presented, thus six estimation models of high pressure turbine inlet temperature were derived. Unmeasured parameters of these models were defined as temperature model coefficients as a whole, which were fitted with measured engine power setting parameters using an engine performance model. Validation results show that assembled estimation models have good precision for both health and deteriorative engines, and the mean squared error of its best performance model is not above 1%. Moreover, by comparison with linear and neural network fitting methods, the assembled estimation method has a clear advantage in precision and stability.

     

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    • References(25)
  • [1]
    SAE Committee E-32.AIR 1872B-1998 guide to life usage monitoring and parts management for aircraft gas turbine engines[S].USA:SAE Iternational,2011:1-56.
    [2]
    李洪伟,叶斌,蔡娜.基于概率的航空发动机飞行换算率改进算法[J].航空动力学报,2014,29(5):1184-1190. LI Hongwei,YE Bin,CAI Na.Improved algorithm flight conversion ratio for aero-engine based on probability[J].Journal of Aerospace Power,2014,29(5):1184-1190.(in Chinese)
    [3]
    尉询楷,杨立,刘芳,等.航空发动机预测与健康管理[M].北京:国防工业出版社,2014.
    [4]
    洪杰,张大均,韩继斌.航空发动机关键件使用寿命监视系统设计[J].北京航空航天大学学报,2000,26(1):45-48. HONG Jie,ZHANG Dajun,HAN Jibin.Design of life usage monitoring system of aeroengine critical part[J].Journal of Beijing University of Aeronautics and Astronautics,2000,26(1):45-48.(in Chinese)
    [5]
    Jaw L C.Recent advancements in aircraft engine health management (EHM) technologies and recommendations for the next step[C]//Proceedings of AMSE Turbo Expo 2005:Power for Land,Sea and Air.Nevada,USA:ASME,2005:683-695.
    [6]
    Paquet M D,Gatlin P K,Cote S M.Usage monitoring:a milestone in engine life management[R].Monterey,CA,USA:AIAA/SAE /ASME/ASEE 21st Joint Propulsion Conference,1985.
    [7]
    Broede J.Design and service experience of engine life usage monitoring systems[R].Torum Pisa:5th European Propulsion,1995.
    [8]
    Pfoertner H,Rob C.Preparing life usage monitoring for the next decade[C]//Proceeding of the 17th Symposium on Aircraft Integrated Monitoring Systems.Stuttgart:Motoren und Turbinen Union GmbH,1995:1-21.
    [9]
    陈卫,程礼,李全通,等.航空发动机监控技术[M].北京:国防工业出版社,2011.
    [10]
    王永旗,徐可君,夏毅锐.基于飞行参数的双发飞机发动机疲劳损伤差异分析[J].推进技术,2014,35(1):101-106. WANG Yongqi,XU Kejun,XIA Yirui.Fatigue damage analysis of aeroengine in twin-engine aircraft based on flight parameters[J].Journal of Propulsion Technology,2014,35(1):101-106.(in Chinese)
    [11]
    王永华,李本威.航空发动机关键件循环寿命耗损实时监视软件设计[J].航空计算技术,2004,34(1):56-58. WANG Yonghua,LI Benwei.The real-time monitoring software design for engine parts cycle life consuming[J].Aeronautical Computer Technique,2004,34(1):56-58.(in Chinese)
    [12]
    陈永刚,倪世宏,黄志宇.基于飞行数据的航空发动机寿命监视系统设计[J].航空发动机,2002(4):12-15. CHEN Yonggang,NI Shihong,HUANG Zhiyu.Design of aeroengine life monitoring system based on flight data[J].Aeroengine,2004(4):12-15.(in Chinese)
    [13]
    Hörl F,Richter K.Monitoring the EJ200 Engine[C]//Proceedings of the 18th Symposium on Aircraft Integrated Monitoring Systems.Stuttgart:Motoren und Turbinen Union GmbH,1996:1-20.
    [14]
    Broede J,Pfoertner H.OLMOS in GAF MRCA Tornado:10 years of experience with on-board life usage monitoring[R].AIAA 97-2905,1997.
    [15]
    陈小磊,郭迎清,张书刚.航空发动机寿命延长控制综述[J].航空发动机,2013,39(1):17-22. CHEN Xiaolei,GUO Yingqing,ZHANG Shugang.Summary of life extending control for an aeroengine[J].Aeroengine,2013,39(1):17-22.(in Chinese)
    [16]
    Chen C L P,Guo T H.Design of intelligent acceleration schedules for extending the life of aircraft engines[J].IEEE Transactions on Systems,Man,and Cybernetics,Part C:Applications and Reviews,2007,37(5):1005-1015.
    [17]
    Tinga T,Visser W P J,de Wolf W B,et al.Integrated lifing analysis tool for gas turbine components[C]//Proceedings of ASME Turbo Expo 2000.Munich Germany:ASME,2000:1-8.
    [18]
    刘葆华,黄金泉.基于高压涡轮叶片寿命损耗的航空发动机功率控制[J].航空动力学报,2013,28(12):2836-2841. LIU Baohua,HUANG Jinquan.Aero-engine power control based on life consumption of high pressure turbine blade[J].Journal of Aerospace Power,2013,28(12):2836-2841.(in Chinese)
    [19]
    Benvenuti E.Innovative gas turbine performance diagnostics and hot parts life assessment techniques[C]//Proceedings of the 30th Turbomachinery Symposium.Houston,USA:ASME,2001:23-31.
    [20]
    Carcasci C,Facchini B,Grillo F,et al.Development of diagnostic tools for real time assessment of gas turbine hot gas path componnent temperatures:a preliminary study[C]//Proceedings of ASME Turbo Expo 2002.Netherlands Amsterdam:ASME,2002:1-8.
    [21]
    富丽新,张宝诚,赵春伟.航空发动机燃烧室和涡轮出口滞止温度相关的研究[J].航空动力学报,1996,11(2):202-204. FU Lixin,ZHANG Baocheng,ZHAO Chunwei.Stagnation temperature relative research of combustion and turbine exhaust for aeroengine[J].Journal of Aerospace Power,1996,11(2):202-204.(in Chinese)
    [22]
    夏毅锐.某型发动机高压二级涡轮转子叶片疲劳/持久寿命研究[D].山东烟台:海军航空工程学院,2006. XIA Yirui.Fatigue and creep life research of the second high pressure turbine blade for a engien[D].Yantai Shandong:Naval Aeronautical and Astronautical University,2006.(in Chinese)
    [23]
    Roemer M.Testing of a real-time health monitoring and diagnositic system for gas turbine engines[R].Cleveland,OH:34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit,1998.
    [24]
    Ghafir M F A,Li Y G,Wang L.Creep life prediction for aero gas turbine hot section component using artificial neural networks[J].Journal of Engineering for Gas Turbines and Power,2014,136(3):031504.1-031504.9.
    [25]
    Herrera C M,Yepifanov S,Loboda I.A comparative analysis of turbine rotor inlet temperature models[R].British Columbia,Canada:ASME 2011 Turbo Expo:Turbine Technical Conference and Exposition,2011.
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