Technical Brief

A Detailed Modular Governor-Turbine Model for Multiple-Spool Gas Turbine With Scrutiny of Bleeding Effect

[+] Author and Article Information
Hossein Balaghi Enalou

Faculty of Engineering,
University of Nottingham,
Aerospace Technology Centre,
Nottingham NG8 1BB, UK
e-mail: Hossein.BalaghiEnalou@nottingham.ac.uk

Eshagh Abbasi Soreshjani

Engineering Department,
MAPNA Turbine Engineering & Manufacturing
Company (TUGA),
Karaj 3167643594, Iran
e-mail: abbasi.eshagh@mapnaturbine.com

Mohamed Rashed

Faculty of Engineering,
University of Nottingham,
Nottingham NG8 1BB, UK
e-mail: Mohamed.Rashed@nottingham.ac.uk

Seang Shen Yeoh

University of Nottingham,
Nottingham NG8 1BB, UK
e-mail: eexssye@nottingham.ac.uk

Serhiy Bozhko

Faculty of Engineering,
University of Nottingham,
Nottingham NG8 1BB, UK
e-mail: Serhiy.Bozhko@nottingham.ac.uk

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received September 12, 2016; final manuscript received April 25, 2017; published online June 27, 2017. Assoc. Editor: Liang Tang.

J. Eng. Gas Turbines Power 139(11), 114501 (Jun 27, 2017) (6 pages) Paper No: GTP-16-1446; doi: 10.1115/1.4036947 History: Received September 12, 2016; Revised April 25, 2017

Multiple-spool gas turbines are usually utilized for power supply in aircrafts, ships, and terrestrial electric utility plants. As a result, having a reliable model of them can aid with the control design process and stability analysis. Since several interconnected components are coupled both thermodynamically and through shafts, these engines cannot be modeled linearly as single shaft gas turbines. In this paper, intercomponent volume method (ICV) has been implemented for turbine modeling. A switched feedback control system incorporating bump-less transfer and antiwindup functionality is employed as governor for the engine. Validation with test results from a three spool gas turbine highlights high accuracy of turbine-governor model in various maneuvers. Results show that over-speed after load rejection is considerable due to the fact that in this arrangement, the power turbine (PT) is not coupled with the compressor which acts like a damper for single shaft gas turbines. To address this problem, bleed valves (mainly before combustion chamber) are used to arrest the over-speed by 20%. In addition, a switch is employed into the governor system to rapidly shift fuel to permissible minimum flow.

Copyright © 2017 by ASME
Your Session has timed out. Please sign back in to continue.


Hannett, L. N. , Jee, G. , and Fardanesh, B. , 1995, “ A Governor/Turbine Model for a Twin-Shaft Combustion Turbine,” IEEE Trans. Power Syst., 10(1), pp. 133–140. [CrossRef]
Yee, S. K. , Milanović, J. V. , and Hughes, F. M. , 2011, “ Validated Models for Gas Turbines Based on Thermodynamic Relationships,” IEEE Trans. Power Syst., 26(1), pp. 270–281. [CrossRef]
Sellers, J. F. , and Daniele, C. J. , 1975, “ DYNGEN: A Program for Calculating Steady State and Transient Performance of Turbojet and Turbofan Engines,” NASA Lewis Research Center, Cleveland, OH, Technical Report No. NASA TN D-7901. https://ntrs.nasa.gov/search.jsp?R=19750017548
Parker, K. , and Guo, T. H. , 2003, “ Development of a Turbofan Engine Simulation in a Graphical Simulation Environment,” NASA Glenn Research Center, Cleveland, OH, Technical Report No. NASA TM 2003-212543. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20030093721.pdf
De Castro, J. A. , Litt, J. S. , and Frederick, D. K. , 2008, “ A Modular Aero-Propulsion System Simulation of a Large Commercial Aircraft Engine,” NASA Glenn Research Center, Cleveland, OH, Technical Report No. NASA TM 2008-215303. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20080043619.pdf
Zhou, W. X. , Huang, J. Q. , and Duo, J. P. , 2006, “ Development of Component Level Model for a Turbofan Engine,” J. Aerosp. Power, 21(2), pp. 248–253.
Rahman, N. U. , and Whidborne, J. F. , 2008, “ A Numerical Investigation Into the Effect of Engine Bleed on Performance of a Single-Spool Turbojet Engine,” J. Aerosp. Eng., Part G, 222(7), pp. 939–949. [CrossRef]
Balaghi Enalou, H. , and Abbasi Soreshjani, E. , 2015, “ A Detailed Governor-Turbine Model for Heavy-Duty Gas Turbines With a Careful Scrutiny of Governor Features,” IEEE Trans. Power Syst., 30(3), pp. 1435–1441. [CrossRef]
MATLAB, 2015, “ The Language of Technical Computing, Version R2015b, SIMULINK, Dynamic System Simulation for MATLAB, Version R2015b,” The Mathworks, Inc., Natick, MA.
Walsh, P. P. , and Fletcher, P. , 2004, Gas Turbine Performance, Wiley, Oxford, UK.
Nagpal, M. , Moshref, A. , Morison, G. K. , and Kundur, P. , 2001, “ Experience With Testing and Modeling of Gas Turbines,” IEEE Power Engineering Society Winter Meeting (PESW), Columbus, OH, Jan. 28–Feb. 1, Vol. 2, pp. 652–656.


Grahic Jump Location
Fig. 1

Three spool gas turbine arrangement

Grahic Jump Location
Fig. 2

Structure of gas turbine model

Grahic Jump Location
Fig. 3

Control volume module

Grahic Jump Location
Fig. 5

Structure of gas turbine governor

Grahic Jump Location
Fig. 7

Turbine-governor model (main loops in operation)

Grahic Jump Location
Fig. 8

Steady-state performance line on LPC map

Grahic Jump Location
Fig. 9

Steady-state performance HPC map

Grahic Jump Location
Fig. 10

Temperature response of loading

Grahic Jump Location
Fig. 11

Temperature response error

Grahic Jump Location
Fig. 12

Speed response after load rejection

Grahic Jump Location
Fig. 13

Valve position after 17 MW load rejection

Grahic Jump Location
Fig. 14

Bleeding air model

Grahic Jump Location
Fig. 15

Speed response after load rejection with bleed valves



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