During Phase II of the Department of Energy (DOE) funded High Temperature Turbine Technology (HTTT) Program, critical technology development and component verification testing related to the design of an advanced water-cooled gas turbine, firing at 2600°F (1427°C) on low-Btu gas, are being performed by General Electric. A composite construction first stage nozzle was chosen so that low surface temperature [1000°F (538°C)], necessary to control corrosion and high heat flux induced strain, would result. This paper discusses the prototype testing of a three throat segment of this design. The segment consists of two test vanes and a pressure and suction side slave. Hot gas conditions exceeded the design point conditions of 2600°F (1427°C) firing temperature, 166 psia (1.14 MPa) and 6.37 lbm/s (2.89 kg/s) per throat. Nozzle temperatures are presented as a function of firing temperature. Discussion of boiling phenomena which occurred during coolant flow reduction is included. Results are discussed as they relate to verification of the design method and to establishing the “technology readiness” of this design.

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