Real Time Linear Simulation and Control for the Small Aircraft Turbojet Engine PUBLIC ACCESS

[+] Author Affiliations
C. D. Kong, S. K. Kim

Chosun University, Kwangju, Republic of Korea

Paper No. 97-AA-114, pp. V001T01A003; 8 pages
  • ASME 1997 Turbo Asia Conference
  • ASME 1997 Turbo Asia Conference
  • Singapore, September 30–October 2, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7867-5
  • Copyright © 1997 by ASME


The performance of the aero gas turbine engine requires optimization because it is directly related to overall aircraft performance.

In this study, a modified DYNGEN, a dynamic simulation program with component maps of the small aircraft turbojet engine, was used. Nonlinear dynamic simulation was performed to predict overall engine performance.

Each response characteristic of various cases, such as the 6% rpm step model, the 5% rpm step model, the 3% rpm step model, and the real-time linear model of the interpolation scheme within the operating range were compared. Among them, the real time linear model was selected for the turbojet engine with nonlinear characteristics.

Finally control schemes such as the PI (Proportional-Integral Controller) and the LQR (Linear Quadratic Regulator) were applied to optimize engine performance.

As a result of comparison of the PI and the LQR controller, the overshoot of the turbine inlet temperature was effectively eliminated by the LQR controller with the proper control gain K.

Copyright © 1997 by ASME
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