Abstract: An accumulation of heat which takes place in gas turbines during deceleration of turbine components, such as during shut-down, may be dissipated by flowing a supply of cooling air through the turbine stages. The cooling air is selectively supplied after the supply of combustion air and fuel has been discontinued. The cooling air is preferably flowed through the combustion chambers prior to entry into the turbine stages so that the cooling air is initially pre-heated. Additional air may preferably be supplied to the final ring of blades of each stage or of the final stage of a multi-staged turbine.

Abstract: A gas turbine is disclosed having at least one turbine stage with hot gas flowing axially through the one stage. At least one balance piston is provided on the shaft to equalize an axial thrust and is located adjacent to at least a first pressurized fluid chamber. The first pressurized fluid chamber is adjacent to a hot gas intake of the turbine stage and is separated from at least a second pressurized fluid chamber by a first transfer gasket co-acting with the balance piston. Pressurized fluid within the first fluid chamber has a pressure greater than the pressure of the hot gas in the vicinity of a hot gas intake. A cooling system is connected to the second fluid chamber for supplying a cooling fluid. A slot of the first transfer gasket is selected so that a pressure difference between the first and second fluid chambers at least partially brings the axial thrust into equalization through the balance piston.