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Journal of Engineering for Gas Turbines and Power | Volume 133 | Issue 8 | Research Paper
Research Papers: Gas Turbines: Microturbines and Small Turbomachinery

Experimental Investigations of Pressure Losses on the Performance of a Micro Gas Turbine System

[+] Author and Article Information
Jan Zanger

Institute of Combustion Technology, German Aerospace Center, Pfaffenwaldring 38-40, Stuttgart 70569, Germanyjan.zanger@dlr.de

Axel Widenhorn, Manfred Aigner

Institute of Combustion Technology, German Aerospace Center, Pfaffenwaldring 38-40, Stuttgart 70569, Germany

J. Eng. Gas Turbines Power 133(8), 082302 (Apr 11, 2011) (9 pages) doi:10.1115/1.4002866 History: Received May 31, 2010; Revised August 03, 2010; Published April 11, 2011; Online April 11, 2011
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Citing Articles

Pressure losses between the compressor outlet and the turbine inlet are a major issue of overall efficiency and system stability for a solid oxide fuel cell/micro gas turbine (MGT) hybrid power plant system. The goal of this work is the detailed analysis of the effects of additional pressure losses on MGT performance in terms of steady-state and transient conditions. The experiments were performed using the micro gas turbine test rig at the German Aerospace Centre in Stuttgart using a butterfly control valve to apply additional pressure loss. This paper reports electric power and pressure characteristics at steady-state conditions as well as a new surge limit for this Turbec T100 micro gas turbine test rig. Furthermore, the effects of additional pressure loss on the compressor surge margin are quantified and a linear relation between the relative surge margin and additional pressure loss is shown. For transient variation of pressure loss at constant turbine speed, time delays are presented and an instability issue of the commercial gas turbine controller is discussed. Finally, bleed-air blow-off and reduction of the turbine outlet temperature are introduced as methods of increasing the surge margin. It is quantified that both methods have a substantial effect on the compressor surge margin. Furthermore, a comparison between both methods is given in terms of electric power output.
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Copyright © 2011 by American Society of Mechanical Engineers
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References

1
Veyo, S. E., Schockling, L. A., Dederer, J. T., Gillett, J. E., and Lundberg, W. L., 2000, “Tubular Solid Oxide Fuel Cell/Gas Turbine Hybrid Cycle Power Systems-Status,” ASME Paper No. 200-GT 550.
2
Veyo, S. E., Lundberg, W. L., Vora, S. D., and Litzinger, K. P., 2003, “Tubular SOFC Hybrid Power System Status,” ASME Paper No. GT2003-38943.
3
Tucker, D., Liese, E., VanOsdol, J., Lawson, L., and Gemmen, R. S., 2005, “Fuel Cell Gas Turbine Hybrid Simulation Facility Design,” ASME Paper No. IMECE2002-33207.
4
Tucker, D., Lawson, L., VanOsdol, J., Kislear, J., and Akinbobuyi, A., 2006, “Examination of Ambient Pressure Effects on Hybrid Solid Oxide Fuel Cell Turbine System Operation Using Hardware Simulation,” ASME Paper No. GT2006-91291.
5
Pascenti, M., Ferrari, M. L., Magistri, L., and Massardo, A. F., 2007, “Micro Gas Turbine Based Test Rig for Hybrid System Emulation,” ASME Paper No. GT2007-27075.
6
Ferrari, M. L., Pascenti, M., Magistri, L., and Massardo, A. F., 2007, “A General Purpose Test Rig for Innovative Cycles Based on a 100 kWe Micro Gas Turbine,” IGTC2007 Tokyo , Paper No. TS-015.
7
Lim, T., Song, R., Shin, D., Yang, J., Jung, H., Vinke, I., and Yang, S., 2008, “Operating Characteristics of a 5 kW Class Anode-Supported Planar SOFC Stack for a Fuel Cell/Gas Turbine Hybrid System,” Int. J. Hydrogen Energy, 3 , pp. 1076–1083.
8
Hohloch, M., Widenhorn, A., Lebküchner, D., Panne, T., and Aigner, M., 2008, “Micro Gas Turbine Test Rig for Hybrid Power Plant Application,” ASME Paper No. GT2008-50443.
9
Panne, T., Widenhorn, A., and Aigner, M., 2008, “Steady State Analysis of a SOFC/GT Hybrid Power Plant Test Rig,” ASME Paper No. GT2008-50288.
10
Panne, T., Widenhorn, A., Boyde, J., Matha, D., Abel, V., and Aigner, M., 2007, “Thermodynamic Process Analyses of SOFC-GT Hybrid Systems,” AIAA Paper No. 2007-4833.
11
Kimijima, S., and Kasagi, N., 2002, “Performance Evaluation of Gas Turbine-Fuel Cell Hybrid Micro Generation System,” ASME Paper No. GT-2002-30111.
12
Kroll, F., Sandor, I., and Staudacher, S., 2009, “System Dynamics of a Hardware in the Loop Simulation of a Hybrid Power Plant,” ASME Paper No. GT2009-59859.
13
Kroll, F., Nielsen, A., and Staudacher, S., 2008, “Transient Performance and Control System Design of Solid Oxide Fuel Cell/Gas Turbine Hybrids,” ASME Paper No. GT2008-50232.
14
Ferrari, M., Liese, E., Tucker, D., Lawson, L., Traverso, A., and Massardo, A., 2007, “Transient Modeling of the NETL Hybrid Fuel Cell/Gas Turbine Facility and Experimental Validation,” ASME J. Eng. Gas Turbines Power, 129 , pp. 1012–1019.  [CrossRef]
15
Hohloch, M., Widenhorn, A., Zanger, J., and Aigner, M., 2010, “Experimental Characterization of a Micro Gas Turbine Test Rig,” ASME Paper No. GT2010-22799.
16
Hohloch, M., Sadanandan, R., Widenhorn, A., Meier, W., and Aigner, M., 2010, “OH∗ Chemiluminescence and OH PLIF Measurements in a Micro Gas Turbine Combustor,” ASME Paper No. GT2009-22800.
17
Hohloch, M., Widenhorn, A., Zanger, J., and Aigner, M., 2009, “OH Chemiluminescence Measurements in a Micro Gas Turbine Combustor,” "VDI, Proceedings of 24th German Flame Day, Combustion and Furnaces", Vol. 2056 , pp. 539–542.
18
Bronstein, I., and Semendjajew, K., 1969, "Taschenbuch der Mathematik", 6th ed., Verlag Harri Deutsch, Zürich and Frankfurt/Main.
19
Tucker, D., Lawson, L., and Gemmen, R. S., 2005, “Characterization of Air Flow Management and Control in a Fuel Cell Turbine Hybrid Power System Using Hardware Simulation,” ASME Paper No. PWR2005-50127.
20
Ferrari, M., Pascenti, M., Magistri, L., and Massardo, A., 2008, “Emulation of Hybrid System Start-Up and Shutdown Phases With a Micro Gas Turbine Based Test Rig,” ASME Paper No. GT2008-50617.

Figures

Grahic Jump Location
+Test rig description and instrumentation
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Test rig description and instrumentation
Figure 1

Test rig description and instrumentation

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+Flow path section between the compressor outlet and the airside recuperator inlet
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Flow path section between the compressor outlet and the airside recuperator inlet
Figure 2

Flow path section between the compressor outlet and the airside recuperator inlet

Grahic Jump Location
+Relative pressure loss between the compressor outlet and the recuperator inlet for 75%, 80%, and 90% turbine speed as a function of recuperator valve opening
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Relative pressure loss between the compressor outlet and the recuperator inlet for 75%, 80%, and 90% turbine speed as a function of recuperator valve opening
Figure 3

Relative pressure loss between the compressor outlet and the recuperator inlet for 75%, 80%, and 90% turbine speed as a function of recuperator valve opening

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+Total compressor outlet pressure and total airside recuperator inlet pressure for 75%, 80%, and 90% turbine speed as a function of additional relative pressure loss Δp0
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Total compressor outlet pressure and total airside recuperator inlet pressure for 75%, 80%, and 90% turbine speed as a function of additional relative pressure loss Δp0
Figure 4

Total compressor outlet pressure and total airside recuperator inlet pressure for 75%, 80%, and 90% turbine speed as a function of additional relative pressure loss Δp0

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+Electric power output for 75%, 80%, 87.5%, 90%, and maximum turbine speed as a function of additional relative pressure loss Δp0
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Electric power output for 75%, 80%, 87.5%, 90%, and maximum turbine speed as a function of additional relative pressure loss Δp0
Figure 5

Electric power output for 75%, 80%, 87.5%, 90%, and maximum turbine speed as a function of additional relative pressure loss Δp0

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+Points of surge and new surge limit on compressor map
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Points of surge and new surge limit on compressor map
Figure 6

Points of surge and new surge limit on compressor map

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+Operating points on compressor map for 75%, 80%, 87.5%, 90%, and maximum turbine speed as a function of pressure loss
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Operating points on compressor map for 75%, 80%, 87.5%, 90%, and maximum turbine speed as a function of pressure loss
Figure 7

Operating points on compressor map for 75%, 80%, 87.5%, 90%, and maximum turbine speed as a function of pressure loss

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+Schematic diagram of the coefficients in the Hesse normal form for the surge limit linear fit
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Schematic diagram of the coefficients in the Hesse normal form for the surge limit linear fit
Figure 8

Schematic diagram of the coefficients in the Hesse normal form for the surge limit linear fit

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+Relative distance Δdsurge to surge limit for 75%, 80%, 87.5%, and 90% turbine speed as a function of additional relative pressure loss
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Relative distance Δdsurge to surge limit for 75%, 80%, 87.5%, and 90% turbine speed as a function of additional relative pressure loss
Figure 9

Relative distance Δdsurge to surge limit for 75%, 80%, 87.5%, and 90% turbine speed as a function of additional relative pressure loss

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+Ramp-up of recuperator valve from 52.5% to 100% at different gradients %/s as a function of time
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Ramp-up of recuperator valve from 52.5% to 100% at different gradients %/s as a function of time
Figure 10

Ramp-up of recuperator valve from 52.5% to 100% at different gradients %/s as a function of time

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+Comparison of electric power output and the reciprocal pressure loss 1/Δpcr between the compressor outlet and the recuperator inlet as a function of time at valve opening settings from 52.5% to 100% (grad >80%/s at 75% turbine speed)
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Comparison of electric power output and the reciprocal pressure loss 1/Δpcr between the compressor outlet and the recuperator inlet as a function of time at valve opening settings from 52.5% to 100% (grad >80%/s at 75% turbine speed)
Figure 11

Comparison of electric power output and the reciprocal pressure loss 1/Δpcr between the compressor outlet and the recuperator inlet as a function of time at valve opening settings from 52.5% to 100% (grad >80%/s at 75% turbine speed)

Grahic Jump Location
+Controller instability issue of pressure loss increase at maximum turbine speed (grad 0.2%/s)
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Controller instability issue of pressure loss increase at maximum turbine speed (grad 0.2%/s)
Figure 12

Controller instability issue of pressure loss increase at maximum turbine speed (grad 0.2%/s)

Grahic Jump Location
+Relative distance Δdsurge to surge limit at 75% Ts as a function of bleed-air mass flow and turbine outlet temperature
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Relative distance Δdsurge to surge limit at 75% Ts as a function of bleed-air mass flow and turbine outlet temperature
Figure 13

Relative distance Δdsurge to surge limit at 75% Ts as a function of bleed-air mass flow and turbine outlet temperature

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+Electric power output at 75% Ts as a function of bleed-air mass flow and turbine outlet temperature
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Electric power output at 75% Ts as a function of bleed-air mass flow and turbine outlet temperature
Figure 14

Electric power output at 75% Ts as a function of bleed-air mass flow and turbine outlet temperature

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