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.

References

References
1.
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
.
2.
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
.
3.
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
4.
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
5.
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
6.
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
.
7.
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
.
8.
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
.
9.
MATLAB
,
2015
, “
The Language of Technical Computing, Version R2015b, SIMULINK, Dynamic System Simulation for MATLAB, Version R2015b
,” The Mathworks, Inc., Natick, MA.
10.
Walsh
,
P. P.
, and
Fletcher
,
P.
,
2004
,
Gas Turbine Performance
,
Wiley
,
Oxford, UK
.
11.
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.
You do not currently have access to this content.