The design and testing of a cooled high pressure turbine stage to provide advance information for the Ruston Tornado 6MW industrial gas turbine is described. The cooled stage was designed to replace an existing uncooled stage in a current Ruston gas turbine to allow development testing under actual engine conditions. The instrumentation techniques used on the development engine, including infrared pyrometry, are discussed and results of the tests covering nozzle vane and rotor blade cooling under steady state and transient conditions and engine performance are presented and compared with the design predictions.

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