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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

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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