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TECHNICAL PAPERS: Gas Turbines: Cycle Innovations

Analytical Blade Row Cooling Model for Innovative Gas Turbine Cycle Evaluations Supported by Semi-Empirical Air-Cooled Blade Data

[+] Author and Article Information
Leonardo Torbidoni, Aristide F. Massardo

Thermochemical Power Group, Dipartimento di Macchine Sistemi Energetici e Trasporti, Università di Genova, Via Montallegro 1, 16145 Genova, Italia

J. Eng. Gas Turbines Power 126(3), 498-506 (Aug 11, 2004) (9 pages) doi:10.1115/1.1707030 History: Received December 01, 2001; Revised March 01, 2002; Online August 11, 2004
Copyright © 2004 by ASME
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Figures

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Flow chart of the blade row cooling flow and pressure losses procedure (conventional and alternative fluid)
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Coolant mass flow, blade maximum temperature and corresponding values of Z, obtained through a variation of gas temperature Tg for the air film cooled blade row
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Coolant pressure losses, blade maximum temperature, and corresponding values of Z, obtained through a variation of gas temperature Tg for air film cooled blade row
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Coolant mass flow required by the blade row when film cooled with air (dotted lines) or carbon dioxide (solid line), for varying gas temperature Tg, maximum blade temperature Tbmx and technology level parameter Z
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Relative coolant pressure drop for the blade row when film cooled with air (dotted lines) or carbon dioxide (solid line), for varying gas temperature Tg, maximum blade temperature Tbmx and technology level parameter Z
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εc as a function of B, reproduced with data from Haselbacher (dotted lines), and Mukherjee (solid lines)
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εc as a function of B, reproduced with data from Haselbacher for film cooling (i.e., average curve)

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