翼冷却空気の削減によるガスタービンならびに複合サイクル発電の高性能化(熱工学,内燃機関,動力など)

概要

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Air cooling blade is usually applied to gas turbines as a basic specification. This blade cooling air is almost 20% of compressor suction air flow and it means that a great deal of compression load is not converted effectively to turbine power generation. This paper proposes the cascade cooling method of turbine blade and the consequent improvement of power generation, which is achieved by the reduction of cooling air consumption with effective use of recovered heat. By this technology, current gas turbines (turbine inlet temperature: 1 350℃) can be up-rated to have a potential high efficiency, equivalent to that of conventional high temperature gas turbine (turbine inlet temperature: 1 500℃).
一般社団法人日本機械学会の論文
2002-08-25