0
TECHNICAL PAPERS: Gas Turbines: Aircraft Engines

Jet Engine Model for Control and Real-Time Simulations

[+] Author and Article Information
Michael Lichtsinder

Faculty of Aerospace Engineering,  Technion-Israel Institute of Technology, 32000 Haifa, Israel

Yeshayahou Levy

Faculty of Aerospace Engineering,  Technion-Israel Institute of Technology, 32000 Haifa, Israellevy@aerodyne.technion.ac.il

J. Eng. Gas Turbines Power 128(4), 745-753 (May 03, 2004) (9 pages) doi:10.1115/1.1915391 History: Received August 29, 2003; Revised May 03, 2004

The main objective of this paper is development of a simple real-time transient performance model for jet engine control. A jet engine arrives to its most dangerous condition during transient operation that may be triggered by fast changes of the input fuel command signal. Thus, the control system specifications are formulated to specify the maximal variance of the fuel flow command (from idle to maximum power level) during transient maneuver. Linear and piecewise-linear techniques are not always convenient and appropriate for turbine engine controller design. An alternative quasilinear simple/fast engine model is discussed in this paper. This model has maximum accuracy for maximal variance of the fuel flow input command in accordance to the jet engine control system specifications. The fast model is obtained using the Novel Generalized Describing Function, proposed for investigation of nonlinear control systems. The paper presents the Novel Generalized Describing Function definition and then discusses the application of this technique for the development a fast turbine engine simulation suitable for control and real-time applications. Simulation results are compared between the conventional and fast models and found to provide good agreement.

FIGURES IN THIS ARTICLE
<>
Copyright © 2006 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Engine stations (the drawing refers to the AMT Netherlands B.V. Olympus Design)

Grahic Jump Location
Figure 2

Generalized describing function definition

Grahic Jump Location
Figure 3

SIMULINK block diagram for generalized describing function calculations

Grahic Jump Location
Figure 4

Real-time model flow chart

Grahic Jump Location
Figure 5

SIMULINK block diagram for real-time simulation of the open-loop engine

Grahic Jump Location
Figure 6

(a) Comparison of fuel flow (input), corrected rotational speed (output), stall margin, and equivalence ratio of the conventional/fast engine models at H=152m, M=0.5. (b) Comparison of air flow, compressor pressure ratio, turbine output temperature, and engine thrust for the conventional/fast models at H=1524m, M=0.5. (c) Comparison of transient operating lines in the compressor map for the conventional/fast engine models at H=1524m, M=0.5.

Grahic Jump Location
Figure 7

(a) Comparison of fuel flow (input), corrected rotational speed (output), stall margin, and equivalence ratio of the conventional/fast engine models at sea level and M=0.5. (b) Comparison of air flow, compressor pressure ratio, turbine output temperature, and engine thrust for the conventional/fast models and M=0.5. (c) Comparison of transient operating lines in the compressor map for the conventional/fast engine models (sea level, M=0.5).

Grahic Jump Location
Figure 8

(a) Comparison of fuel flow (input), corrected rotational speed (output), stall margin, and equivalence ratio of the conventional/fast engine models at H=912m, M=0. (b) Comparison of air flow, compressor pressure ratio, turbine output temperature, and engine thrust for the conventional/fast models at H=912m, M=0. (c) Comparisons of transient operating lines in the compressor map for the conventional/fast engine models at H=912m and M=0.

Grahic Jump Location
Figure 9

(a) Comparison of fuel flow (input), corrected rotational speed (output), stall margin, and equivalence ratio of the conventional/fast engine models at H=3040m and M=0.7. (b) Comparison of air flow, compressor pressure ratio, turbine output temperature, and engine thrust for the conventional/fast models at H=3040m and M=0.7. (c) Comparison of transient operating lines in the compressor map for the conventional/fast engine models at H=3040m and M=0.7.

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In