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TECHNICAL PAPERS: Gas Turbines: Electric Power

Conceptual Design and Cooling Blade Development of 1700°C Class High-Temperature Gas Turbine

[+] Author and Article Information
Shoko Ito, Hiroshi Saeki, Asako Inomata, Fumio Ootomo, Katsuya Yamashita, Yoshitaka Fukuyama

Toshiba Corporation, Yokohama, Japan

Elichi Koda, Toru Takehashi, Mikio Sato

Central Research Institute of Electric Power Industry, Yokosuka, Japan

Miki Koyama, Toru Ninomiya

New Energy and Industrial Technology Development Organization, Tokyo, Japan

J. Eng. Gas Turbines Power 127(2), 358-368 (Apr 15, 2005) (11 pages) doi:10.1115/1.1806456 History: Received October 01, 2002; Revised March 01, 2003; Online April 15, 2005
Copyright © 2005 by ASME
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References

Koda,  E., Takahashi,  T., Uematsu,  K., and Yamashita,  K., 2002, “Study on the Highly Efficient Closed-Cycle Gas Turbine System for CO2 Collection,” J. Gas Turbine Soc. Jpn.,30, pp. 63–67 (in Japanese).
Jackson, J. B. A., Neto, A. C., Whellens, M., and Audus, 2000, “Gas Turbine Performance Using Carbon Dioxide as Working Fluid in Closed Cycle Operation,” ASME, 2000-GT-153.
Jeriche, H., and Gottlich, E., 2002, “Conceptual Design for An Industrial Prototype Graz Cycle Power Plant,” ASME, GT-2002-30118.
Okamura, T., Koga, A., Ito, S., and Kawagishi, H., 2000, “Evaluation of 1700°C Class Turbine Blades in Hydrogen Fueled Combustion Turbine System,” ASME, 2000-GT-0615.
Ito,  S., Koga,  A., Kawagishi,  H., Matsuda,  H., Suga,  T., and Okamura,  T., 2000, “Hydrogen Combustion Wind Tunnel Test of 1700°C Class Turbine Cooling Blades,” J. Gas Turbine Soc. Jpn.,28, pp. 23–28 (in Japanese).
Matsuda, H., Ikeda, K., Nakata, Y., Otomo, F., Suga, T., and Fukuyama, Y., 1999, “A New Thermochromic Liquid Crystal Temperature Identification Technique Using Color Space Interpolations and Its Application to Film Cooling Effectiveness Measurements,” Proceedings of PSFVIP-2, PF053.
Saeki, H., Ito, S., Matsuda, H., and Okamura, T., 1999, “Heat Transfer Measurements on Turbine Nozzle Using Liquid Crystals,” International Gas Turbine Congress ’99 Kobe, TS-47, pp. 607–613.
Saeki, H., and Fukuyama, Y., 2002, “Heat Transfer Measurements on a Gas Turbine Blade for ACRO-GT-2000,” ISROMAC-9, Paper HT-ABS-025.
Biswas, D., and Fukuyama, Y., 1993, “Calculation of Transitional Boundary Layer With an Improved Low Reynolds Number Version of the k-ε Turbulence Model,” ASME, 93-GT-73.
Fukuyama, Y., Otomo, F., Sato, M., Kobayashi, Y., and Matsuzaki, H., 1995, “Prediction of Vane Surface Film Cooling Effectiveness Using Compressible Navier–Stokes Procedure and k-Epsilon Turbulence Model With Wall Function,” ASME, 95-GT-25.
Kubo, R., Otomo, F., Fukuyama, Y., and Nakata, Y., 1998, “Aerodynamic Loss Increase Due to Individual Film Cooling Injections From Gas Turbine Nozzle Surface,” ASME, 98-GT-497.
Launder,  B. E., and Sharma,  B. I., 1979, “Application of the Energy-Dissipation Model of Turbulence to the Calculation of Flow Near a Spinning Disc,” Lett. Heat Mass Transfer, 1, pp. 131–138.
Kato, M., and Launder, B. E., 1993, “The Modeling of Turbulent Flow Around Stationary and Vibrating Square Cylinders,” 9th Symposium on Turbulent Shear Flows, Kyoto Japan, 10-4.
Han,  J. C., and Park,  J. S., 1988, “Developing Heat Transfer in Rectangular Channels With Rib Turbulators,” Int. J. Heat Mass Transfer, 31, pp. 183–195.
Han,  J. C., Zhang,  Y. M., and Lee,  C. P., 1991, “Augmented Heat Transfer in Square Channels With Parallel, Crossed, and V-Shaped Angled Ribs,” ASME J. Heat Transfer, 113, pp. 590–596.
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Figures

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Schematic diagram of CO2 recovery power generation system
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Structure of 1700°C class gas turbine
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Variation of adiabatic efficiency with rotational speed (HT1)
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Gas path configuration (HT1)
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Schematic of turbine cooling system
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Rotor cooling flow test section
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Photograph of rotor cooling flow test apparatus
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Pressure loss coefficient in rotor cooling passage
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Streamlines on the rotor cooling passage
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Photograph of heat transfer cascade test apparatus
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Distribution of Stanton number on nozzle surface (Re=1.6×106, Tu=2.1%)
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Distribution of Stanton number on blade surface (Re=8.1×105, Tu=1.4%)
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Distribution of Stanton number on blade surface (Re=8.1×105, Tu=12.4%)
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Computed Stanton number distribution on nozzle surface (Re=1.6×106, Tu=2.1%)
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Computed Stanton number distribution on blade surface (Re=8.1×105, Tu=12.4%)
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Numerical streamline visualization on two-dimensional bucket flow field with tip clearance
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Photograph of ribbed wall heat transfer test apparatus
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Heat transfer distribution on the floor equipped with broken rib (Re=8.4×104)
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Mean Nusselt number augmentation on the ribbed wall
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Friction factor of the ribbed wall
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Cooling configurations of first stage nozzle and blade
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Blade mean height temperatures distributions
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A comparison of the coolant flow rate for the first stage nozzle and blade
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Nozzle and blade surface stress distributions

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