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

Real-Time Transient Three Spool Turbofan Engine Simulation: A Hybrid Approach

[+] Author and Article Information
Naveed U. Rahman

Dynamics, Simulation and Controls Group, Cranfield University, Bedfordshire, MK43 OAL, UKn.ur-rahman@cranfield.ac.uk

James F. Whidborne

Dynamics, Simulation and Controls Group, Cranfield University, Bedfordshire, MK43 OAL, UKj.f.whidborne@cranfield.ac.uk

J. Eng. Gas Turbines Power 131(5), 051602 (Jun 09, 2009) (8 pages) doi:10.1115/1.3079611 History: Received October 03, 2008; Revised November 26, 2008; Published June 09, 2009

This paper presents a transient three-spool turbofan engine simulation model that uses a combination of intercomponent volume and iterative techniques. The engine model runs in real time and has been implemented in MATLAB /SIMULINK environment. The main advantage of this hybrid approach is that it preserves the accuracy of the iterative method while maintaining the simplicity of the intercomponent volume method. The iterative approach is applied at each engine subsystem to solve algebraic thermodynamic equations for exit enthalpy, entropy, and temperature, whereas the intercomponent volume method is used to calculate pressures derivatives and hence pressures at corresponding engine stations. This allows the engine state vector to be updated at each pass through the engine calculations. This technique was applied as a test case on the Rolls Royce Trent 500 three-spool turbofan engine, and the results were compared with an iterative method. As the engine state vector is updated during each cycle, the model lends itself for easy integration into nonlinear aircraft simulations, real-time engine diagnostics/prognostics, and jet engine control applications.

Copyright © 2009 by American Society of Mechanical Engineers
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Figure 1

Three-spool turbofan schematic

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Figure 2

Intercomponent volume (V2.1) between fan and IPC/bypass nozzle

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Figure 3

Intercomponent volumes, V2.2 and V3

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Figure 4

Intercomponent turbine volumes (V4.1,V4.2,V5)

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Figure 5

Thermodynamic conditions for the compressor

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Figure 6

Iterative solution for compressor/turbine thermodynamics

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Figure 7

Thermodynamic conditions for the turbine

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Figure 8

Percentage errors in pressures and temperatures at design point

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Figure 9

Transient on LPC/fan map—step reduction in fuel

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Figure 10

Transient on IPC map—step reduction in fuel

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Figure 11

Transient on HPC map—step reduction in fuel

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Figure 12

Pressure derivatives—step reduction in fuel

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Figure 13

Pressures, temperatures, and thrust—step reduction in fuel




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