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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
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References

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Figures

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Fig. 1

Three spool gas turbine arrangement

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Fig. 2

Structure of gas turbine model

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Fig. 3

Control volume module

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Fig. 5

Structure of gas turbine governor

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Fig. 7

Turbine-governor model (main loops in operation)

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Fig. 8

Steady-state performance line on LPC map

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Fig. 9

Steady-state performance HPC map

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Fig. 10

Temperature response of loading

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Fig. 11

Temperature response error

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Fig. 12

Speed response after load rejection

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Fig. 13

Valve position after 17 MW load rejection

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Fig. 14

Bleeding air model

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Fig. 15

Speed response after load rejection with bleed valves

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