The design of an advanced cooled first stage for a full-scale utility size combustion turbine is discussed. The preliminary design work involved evaluating three candidate “skin/spar” concepts: the shell/spar, Lamilloy*/spar and hybrid configurations. A shell/spar concept at 1600°F (871°C) maximum metal temperature was selected for continued development because it ensures against transpiration hole plugging; temperature selection was based on performance and corrosion considerations. The detailed design of the shell/spar advanced cooled stage is featured in this presentation and includes heat transfer and mechanical designs, stress analyses and durability considerations, and material selection. The fabrication process and acceptance tests planned for the advanced cooling components are described along with the shop and field tests proposed for the demonstration engine.

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