Gas turbine

摘要

In order to suppress the Mach number in the final stage moving blade of a gas turbine operating at a pressure ratio of 20 or more, a duct wall (16) in a portion of a specified distance (L) from an end opposing said gas turbine, of a duct (14) forming a diffuser passage (15) communicating with a final exit side of the gas turbine is drawn parallel to or inside of a shaft (O-O) of the gas turbine. Thereby, a decline of turbine efficiency due to shock wave loss can be prevented.