The Taurus gas turbine was first introduced in 1989 with ratings of 6200 HP for single shaft and 6500 HP for twin shaft configurations. A new design of the single shaft third stage turbine rotor and exhaust diffuser brought its power to 6500 HP in 1991. A program was initiated early in 1992 to identify opportunities to further optimize performance of the Taurus. Thorough investigation of performance sensitivity to thermodynamic cycle parameters has resulted in significant improvement over the original design with no change in firing temperature. Aerodynamic and mechanical design changes were implemented in 1993 which raised Taurus performance to 7000 HP and 32% thermal efficiency. Selection of the final design configuration was the outcome of performance maximization versus cost increase, durability risk and loss of commonality with previous engines. This paper details these changes and the design selection process.

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