In order to capture the behavior of the oxyfuel cycle operating with high combustor-outlet temperature, the impact of blade and vane cooling on cycle performance must be included in the thermodynamic model. As a basis for a future transient model, three thermodynamic models for the cooled gas turbine are described and compared. The first model, known previously from the literature, models expansion as a continuous process with simultaneous heat and work extraction. The second model is a simple stage-by-stage model and the third is a more detailed stage-by-stage model that includes velocity triangles and enables the use of advanced loss correlations. An airbreathing aeroderivative gas turbine is modeled, and the same gas turbine operating in an oxyfuel cycle is studied. The two simple models show very similar performance trends in terms of variation of pressure ratio and turbine inlet temperature in both cases. With the more detailed model, it was found that, without any change of geometry, the turbine rotational speed increases significantly and performance drops for the maintained geometry and pressure ratio. A tentative increase of blade angles or compressor pressure ratio is found to increase turbine performance and decrease rotational speed. This indicates that a turbine will require redesign for operation in the oxyfuel cycle.

Issue Section:
Gas Turbines: Cycle Innovations
Keywords:
gas turbines, fossil fuels, thermodynamics, compressors
Topics:
Blades, Carbon dioxide, Compressors, Coolants, Cooling, Cycles, Flow (Dynamics), Gas turbines, Heat, Pressure, Temperature, Turbines, Geometry, Diffusers, Simulation, Design, Combustion chambers, Modeling
1.
Bolland
,
O.
, and
Mathieu
,
Ph.
,
1998
, “
Comparison of Two Removal Options in Combined Cycle Power Plants
,”
Energy Convers. Manage.
,
39
, pp.
1653
–
1663
.
2.
Bolland
,
O.
, and
Saether
,
S.
,
1992
, “
New Concepts for Natural Gas Fired Power Plants Which Simplify the Recovery of Carbon Dioxide, in Energy Conversion and Management
,”
Energy Convers. Manage.
,
33
(
5–8
), pp.
467
–
475
.
3.
Ulizar, I., and Pilidis, P., 1997, “Design of a Semiclosed Gas Turbine With Carbon Dioxide-Argon as Working Fluid,” ASME Paper No. 97-GT-125.
4.
Jackson, A. J. B., Codeceira Neto, A., Whellens, M. W., and Audus, H., 2000, “Gas Turbine Performance Using Carbon Dioxide as Working Fluid in Closed Cycle Operation,” ASME Paper No. 2000-GT-153.
5.
Carcasci, C., Zecchi, S., and Oteri, G., 2002, “Comparison of Blade Cooling Performance Using Alternative Fluids,” ASME Paper No. GT-2002-30551.
6.
Ulfsnes, R., Jordal, K., Bolland, O., and Kvamsdal, H. M., 2003, “Modeling and Simulation of Transient Performance of the Semi-Closed O2/CO2 Gas Turbine Cycle for CO2 Capture,” ASME Paper No. GT-2003-38068.
7.
Bolland
,
O.
, and
Stadaas
,
J. F.
,
1995
, “
Comparative Evaluation of Combined Cycles and Gas Turbines With Water Injection, Steam Injection and Recuperation
,” ASME J. Eng. Gas Turbines Power, 117.
8.
Jordal, K., 2001, “Modeling and Performance of Gas Turbine Cycles With Various Means of Blade Cooling,” Ph.D. thesis, Lund University, Sweden.
9.
Traupel, W., 1988, Termische Turbomaschinen, 3rd Ed., Springer-Verlag, Berlin.
10.
Holland
,
M. J.
, and
Thake
,
T. F.
,
1980
, “
Rotor Blade Cooling in High Pressure Turbines
,”
J. Aircr.
,
17
, pp.
412
–
418
.
11.
El-Masri
,
M. A.
,
1986
, “
On Thermodynamics of Gas Turbine Cycles: Part 2—A Model for Expansion in Cooled Turbines
,”
ASME J. Eng. Gas Turbines Power
,
108
, pp.
151
–
159
.
12.
Louis, J. F., 1977, “Systematic Studies of Heat Transfer and Film Cooling Effectiveness,” AGARD CP 2291.
13.
Geipel, H., Keppel, W., and Weyer, H. B., 1998, “Verbundsforschung zur Hoctemperatur-Gasturbine,” VGB-Konferenz Forschung fu¨r die Kraftwerkstechnik.
14.
El-Masri, M. A., and Pourkey, 1986, “Prediction of Cooling Flow Requirements for Advanced Utility Gas Turbines—Part 1: Analysis and Sealing of the Effectiveness Curve,” ASME Paper No. 86-WA/HT-43.
15.
Halls, 1969, “Air Cooling of Turbine Blades and Vanes,” Supersonic Turbojet Propulsion Systems and Components, AGARDograph 120.
16.
Cordes, G., 1963, Stro¨mungstechnik der Gasbeaufschlagten Axialturbine, Springer-Verlag, Berlin.
17.
Wei, N., 2000, “Significance of Loss Models in Aerothermodynamic Simulation for Axial Turbines,” PhD thesis, Royal Institute of Technology, Sweden.
18.
Ha˚nde, B. M., 1992, “Simulation of Steam Injected Gas Turbines,” PhD thesis, Norwegian Institute of Technology, University of Trondheim, Norway.
19.
Horlock
,
J. H.
,
1960
, “
Losses and Efficiencies in Axial-Flow Turbines (Review)
,” Int. Metall. Rev., 2.
20.
Horlock, J. H., 1966, Axial Flow Turbine, Butterworth, London, pp. 86-87.
21.
Dixon, S. L., 1989, Thermodynamics of Turbomachinery, Pergamon Press, London.
22.
Kacker, S. C., and Okapuu, U., 1981, “A Mean Line Prediction Method for Axial Flow Turbine Efficiency,” ASME Paper No. 81-GT-58.
23.
Anon., 1991–2000, IPSEpro User Documentation, Simtech Simulation Technology, Graz, Austria.
24.
Louis, J. F., Hiaroka, K., and Elmasri, M. A., 1983, “A Comparative Study of the Influence of Different Means of Turbine Cooling on Gas Turbine Performance,” ASME Paper No. 83-GT-180.
25.
Coppinger, M., Cox, G., Hannis, J., and Cox, N., 2002, “Cycle Optimization Using an Advanced, Real Engine Performance Prediction Model,” ASME Paper No. GT-2002-30515.
Copyright © 2004
 by ASME
You do not currently have access to this content.