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Research Papers: Gas Turbines: Controls, Diagnostics, and Instrumentation

Development and Validation of a Civil Aircraft Engine Simulation Model for Advanced Controller Design

[+] Author and Article Information
Sonny Martin

Control and Instrumentation Research Group, Department of Engineering, University of Leicester, LE1 7RH Leicester, UKsm342@le.ac.uk

Iain Wallace

 Alstom Aerospace, Cambridge Road, LE8 6LH Whetstone, UK

Declan G. Bates

Control and Instrumentation Research Group, Department of Engineering, University of Leicester, LE1 7RH Leicester, UKdgb3@le.ac.uk

J. Eng. Gas Turbines Power 130(5), 051601 (Jun 23, 2008) (15 pages) doi:10.1115/1.2939015 History: Received November 15, 2007; Revised April 15, 2008; Published June 23, 2008

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Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

The main components of a turbofan engine

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Figure 2

Diagram of the current model’s closed-loop system

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Figure 3

Selection logic architecture

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Figure 4

Active regulators’ output during acceleration

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Figure 5

Active regulators’ output during deceleration

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Figure 6

Controller fuel demand

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Figure 7

The ordinate gives the number of the active regulator: 1 is the fan speed (LP shaft) regulator, 4 is the HP shaft rate of the acceleration regulator, 8 is the fuel flow increase rate regulator, 7 is the maximum fuel flow regulator, 15 is the fuel flow decrease rate regulator, 12 is the HP shaft rate of deceleration regulator, and 13 is the minimum fuel regulator

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Figure 8

Thrust response to large throttle demand

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Figure 9

PI controller structure with integrator antiwindup

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Figure 10

Thrust response to large throttle demand. Case 2 (top): from 50% to 98% of the maximum thrust, 15,000ft(≈4500m), and Mach number of 0.45. Case 3 (bottom): from 60% to 96% of the maximum thrust, 35,000ft(≈10,000m), and Mach number of 0.8.

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Figure 11

Mass flow through the engine core

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Figure 12

HP compressor discharge pressure

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Figure 13

HPT inlet temperature

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