International Journal of Vehicle Structures and Systems

Open Access Open Access  Restricted Access Subscription Access

Performance Analysis of Adaptive Control Technique for Aircraft Gas Turbine Engine


Affiliations
1 Dept. of Aeronautical Engg., Veltech Dr. RR and Dr. S.R. University, Chennai, India
2 Dept. of Electrical and Electronics Engg., Vel Tech Multi Tech Dr .RR and Dr. S.R. Engg. College, Chennai, India
 

   Subscribe/Renew Journal


This paper presents an adaptive control technique to compensate the thrust variation in an aircraft engine whose performance has been disturbed due to atmospheric conditions. The course of dysfunction appears when a large throttle transient is performed such that the engine switched from low to high speed mode. A relationship is observed between engine disturbance and the overshoot in engine shaft rpm or compressor discharge pressure or turbine temperature, which is determined to cause the thrust variation. This relationship is used to adapt a control. This method works very well up to the operability limit of an engine. Additionally, the type of disturbance identified from sensors data will be useful to implement the adaptive control in real time operation.

Keywords

Gas Turbine Engine, Full Authority Digital Engine (or Electronics) Control, Adaptive Control, Matlab.
User
Subscription Login to verify subscription
Notifications
Font Size

  • G.P. Sallee. 1978. Performance Deterioration based on Existing (Historical) Data; JT9D Jet Engine Diagnostics Program, NASA Contractor Report 135448.

  • J.D. Mattingly, W.H. Heiser and D.T. Pratt. 2002. Aircraft Engine Design, 2nd Edition, AIAA.

  • K.I. Parker and T.H. Guo. 2002. Development of a turbofan engine simulation in a graphical simulation environment, JANNAF 26th Aero-Propulsion Subcommittee, 2nd Modeling and Simulation Subcommittee Joint Meeting, Destin, FL.

  • T. Kobayashi and D.L. Simon. 2001. A hybrid neural network-genetic algorithm technique for aircraft engine performance diagnostics, 37th Joint Propulsion Conf. and Exhibit, Salt Lake City, UT. https://doi.org/10.2514/6.2001-3763.

  • H.H. Lambert. 1991. A Simulation Study of Turbofan Engine Deterioration Estimation using Kalman Filtering Techniques, NASA Technical Memorandum 104233.

  • D.L. Simon. 2003. Aircraft turbofan engine health estimation using constrained Kalman filtering, Proc. Int. Gas Turbine and Aero engine Congress and Exposition, Atlanta, GA.

  • S. Ganesan and G.M. Priyadharshini. 2016. Theoretical analysis on aircraft gas turbine engine's control unit, IOSR-JMCE, 13(6). https://doi.org/10.9790/1684-1306050105.

  • F. Lu, J. Huang and Y. Xing. 2012. Fault diagnostics for turbo shaft engine sensors based on a simplified on-board model, Sensors, 12(8), 11061-11076. https://doi.org/10.3390/s120811061.

  • M.G. Ballin. 1988. A High Fidelity Real Time Simulation of a Small Turboshaft Engine, NASA Technical Memorandum 100991.


Abstract Views: 351

PDF Views: 142




  • Performance Analysis of Adaptive Control Technique for Aircraft Gas Turbine Engine

Abstract Views: 351  |  PDF Views: 142

Authors

S. Ganesan
Dept. of Aeronautical Engg., Veltech Dr. RR and Dr. S.R. University, Chennai, India
R. Jaganraj
Dept. of Aeronautical Engg., Veltech Dr. RR and Dr. S.R. University, Chennai, India
G. Monisha Priyadharshini
Dept. of Electrical and Electronics Engg., Vel Tech Multi Tech Dr .RR and Dr. S.R. Engg. College, Chennai, India

Abstract


This paper presents an adaptive control technique to compensate the thrust variation in an aircraft engine whose performance has been disturbed due to atmospheric conditions. The course of dysfunction appears when a large throttle transient is performed such that the engine switched from low to high speed mode. A relationship is observed between engine disturbance and the overshoot in engine shaft rpm or compressor discharge pressure or turbine temperature, which is determined to cause the thrust variation. This relationship is used to adapt a control. This method works very well up to the operability limit of an engine. Additionally, the type of disturbance identified from sensors data will be useful to implement the adaptive control in real time operation.

Keywords


Gas Turbine Engine, Full Authority Digital Engine (or Electronics) Control, Adaptive Control, Matlab.

References





DOI: https://doi.org/10.4273/ijvss.9.4.13