The logical progression for the gas turbine engine in aircraft and other related industries is to extend its usefulness by providing longer service life. Careful attention during the design and development phase is necessary to obtain this goal in actual production engines. A full knowledge of the operational environment to which the engine will be subjected is of primary importance in defining design and test requirements. This paper presents some of the design considerations and tests conducted in development of a high temperature long life turbine. The specific program involves the application of air cooling in the initial stage of blades and vanes to reduce metal temperatures.