This paper discusses the design of an advanced cooled 1st stage vane, including airfoil and endwalls, for a full-scale utility combustion turbine. Shell/spar cooling technology is used, in which cooling air flows through channels between a thin metal external sheet (shell) and a hollow-cast internal support member (spar), which are joined by diffusion bonding. Heat transfer and stress analyses of this design are featured; however, design criteria, fabrication considerations, material selection, flow analysis, and future program direction are also discussed.

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