초록 ▼

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

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.

대표청구항 ▼

An apparatus for dissipating heat in a gas turbine engine resulting from a deceleration of turbine components, comprising: a gas turbine engine having at least one turbine stage and having combustor means for supplying hot propellant gas to said turbine stage during operation of the gas turbine engi

An apparatus for dissipating heat in a gas turbine engine resulting from a deceleration of turbine components, comprising: a gas turbine engine having at least one turbine stage and having combustor means for supplying hot propellant gas to said turbine stage during operation of the gas turbine engine; a source of coolant gas under pressure; and means for selectively supplying said coolant gas to said turbine stage at a temperature below a temperature of the hot propellant gas when the flow of said hot propellant gas is discontinued, said means for selectively supplying said coolant gas including; an annular duct surrounding a final blade ring of the at least one turbine stage, the annular duct having a plurality of apertures providing communication between the duct and the final blade ring, and valve means for selectively supplying the coolant gas to the annular duct after the flow of hot propellant gas is discontinued.