The effects of three types of cooling systems on the calculated operating performances of a hydrogen-fueled thermal power plant with a 1,700°C-class gas turbine were studied with the goal of attaining a thermal efficiency of greater than 60 percent. The combination of a closed-circuit water cooling system for the nozzle blades and a steam cooling system for the rotor blades was found to be the most efficient, since it eliminated the penalties of a conventional open-circuit cooling system which ejects coolant into the main hot gas stream. Based on the results, the water cooled, first-stage nozzle blade and the steam cooled first-stage rotor blade were designed. The former features array of circular cooling holes close to the surface and uses a copper alloy taking advantage of recent coating technologies such as thermal barrier coatings (TBCs) and metal coatings to decrease the temperature and protect the blade core material. The later has cooling by serpentine cooling passages with V-shaped staggered turbulence promoter ribs which intensify the internal cooling.

Issue Section:
Gas Turbines: Cycle Innovations
Topics:
Combustion gases, Conceptual design, Cooling systems, Hydrogen fuels, Turbines, Blades, Cooling, Circuits, Coatings, Nozzles, Rotors, Steam, Water, Coolants, Copper alloys, Gas turbines, Metals, Temperature, Thermal barrier coatings, Thermal efficiency, Thermal power stations, Turbulence
1.
Alderson, E. D., Scheper, G. W., and Cohn, A., 1987, “Closed Circuit Steam Cooling in Gas Turbines,” ASME Paper 87-JPGC-GT-1.
2.
Anzai
S.
,
Kawaike
K.
,
Matsuzaki
H.
, and
Takehara
I.
,
1991
, “
Effect of Turbulence Promoter Rib Shape on Heat Transfer and Pressure Loss Characteristics
,”
J. of the Gas Turbine Society of Japan
, Vol.
20
, No.
75
, pp.
65
–
73
(in Japanese).
3.
Geiling, D. W., Klompas, N., and Zeman, K. P., 1983, “Water Cooled Gas Turbine Nozzle Technology Demonstration at Ultra-High Firing Temperature,” ASME Paper 83-GT-15.
4.
Han
J. C.
,
Park
J. S.
, and
Lei
C. K.
,
1985
,“
Heat Transfer Enhancement in Channels with Turbulence Promoters
,”
ASME JOURNAL OF ENGINEERING FOR GAS TURBINE AND POWERS
, Vol.
107
, pp.
629
–
635
.
5.
Ikeguchi, T., and Kawaike, K., 1994, “Effect of Closed-Circuit Gas Turbine Cooling Systems on Combined Cycle Performance,” ASME Paper 94-JPGC-GT-8.
6.
Jericha
H.
,
Starzer
O.
, and
Theissing
M.
,
1991
,“
Towards a Solar-Hydrogen System
,”
ASME Cogen-Turbo
, IGTI-Vol.
6
, pp.
435
–
442
.
7.
Kawaike
K.
,
Kobayashi
N.
, and
Ikeguchi
T.
,
1984
,“
Effects of New Blade Cooling System With Minimized Gas Temperature Dilution on Gas Turbine Performance
,”
ASME JOURNAL OF ENGINEERING FOR GAS TURBINE AND POWER
, Vol.
106
, No.
4
, pp.
756
–
764
.
8.
Kawaike, K., Anzai, S., and Sasada, T., 1992, “Integrated CAE System for Cooled Turbine Blade Design and Verification Tests of Analytical Codes,” Heat Transfer in Turbomachinery, R. J. Goldstein, et al., Proceedings of International Symposium Heat Transfer in Turbomachinery, International Center for Heat and Mass Transfer, eds., Begell House, Inc., New York, pp. 73–84.
9.
Kawaike, K., Anzai, S., Takehara, I., Sasada, T., and Matsuzaki, H., 1993, “Advanced Cooling Design of Turbine Blades With Serpentine Cooling Passages,” CIMAC, G12.
10.
Kukreja
R. T.
,
Lau
S. C.
, and
Mcmillin
R. D.
,
1991
, “
Effects of Length and Configuration of Transverse Discrete Ribson Heat Transfer and Friction for Turbulent Flow in a Square Channel
,”
ASME/JSME Thermal Engineering Proceeding
, Vol.
3
, pp.
213
–
218
.
11.
Taslim, M. E., Li, T., and Kercher, D. M., 1994, “Experimental Heat Transfer and Friction in Channels Roughened With Angled, V-Shaped and Discrete Ribson Two Opposite Walls,” ASME Paper 94-GT-163.
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