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Method of apparatus for venting rotor parts of an axial flows compressor of a gas turbine power plant having an axial diffuser arranged behind the rotor and stator vanes at the last compressor stage. An annular chamber is formed downstream of the last rotor disk between adjacent rotor and stator par

Method of apparatus for venting rotor parts of an axial flows compressor of a gas turbine power plant having an axial diffuser arranged behind the rotor and stator vanes at the last compressor stage. An annular chamber is formed downstream of the last rotor disk between adjacent rotor and stator parts and compressed air downstream of the diffuser is introduced into the chamber. The air in the chamber is divided into two individual streams, one of which is recycled to the compressor through an annular slot between the rotor and guide vanes at the last compressor stage and the other of which is discharged as a stream of leakage air into the secondary air system of the turbine.

대표청구항 ▼

Apparatus for cooling the rotor of a multi-stage axial compressor of a gas turbine power plant and for maintaining optimum rotor vane clearance in which the compressor has an axial diffusor located downstream of the rotor vanes and stator vanes of the last stage of the compressor, said apparatus com

Apparatus for cooling the rotor of a multi-stage axial compressor of a gas turbine power plant and for maintaining optimum rotor vane clearance in which the compressor has an axial diffusor located downstream of the rotor vanes and stator vanes of the last stage of the compressor, said apparatus comprising: seal means at the last stage of the compressor for sealing a flow channel in the compressor in which compressed air flows but permitting leakage flow of air therethrough, said seal means including a rotating part and a stationary part, the rotor of the compressor including a rotor disk at the last compressor stage and a further rotor disk downstream thereof, said rotor having an axis of rotation, said disks having root portions closest to said axis of rotation, said rotating part of the seal means being secured to the peripheries of said rotor disk at the last compressor stage and said further rotor disk, a combustion chamber into which the compressed air from the compressor is supplied, said combustion chamber including a housing which supports said stationary part of the seal means, means for bleeding off air in the flow channel of the compressor at a location between the stator and rotor vanes at the last compressor stage and supplying the bled air to said seal means, said bled air flowing through said seal means, an annular chamber formed between said further rotor disk and said housing of the combustion chamber for receiving bled air which has flowed through said seal means, said combustion chamber housing having an opening through which compressed air which has passed through the diffusor can enter said annular chamber and be mixed therein with the bled air which has flowed through the seal means, and flow channel means provided in said disk at the last compressor stage and said further disk downstream thereof for flow of the mixture of air in said annular chamber in a direction opposite the direction of flow of the compressed air in said flow channel and radially inwards against said root portions of said disks.