IGTC-36 Advanced Internal Cooling of Turbine Nozzles and Blades for 1500℃-class Gas Turbines(Session B-3 BLADE COOLING)

概要

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The development is described of the first stage cooled turbine nozzle blades and rotor blades for fourth generation gas turbines operating at combustor outlet temperatures of 1500℃ class. The development required that cooling air consumption be minimized and good durability be provided. Intensified internal cooling scheme, not having much dependence on film cooling and well suitable to a thermal barrier coating (TBC), was developed on the basis of convective heat transfer enhancement technologies. The suitability of the scheme was demonstrated in the hot cascade test. Design philosophy, fundamental tests of heat transfer enhancement techniques, and hot cascade test results of the blades, including the effect of the TBC, are described.
公益社団法人日本ガスタービン学会の論文