초록 ▼

An apparatus for cooling an axial-flow gas turbine of the type comprising a multi-stage turbine (1) which drives a compressor (10) arranged on a common shaft (13), involves means for removing leakage air from the space surrounding the portion of the shaft between the turbine and the compressor. In s

An apparatus for cooling an axial-flow gas turbine of the type comprising a multi-stage turbine (1) which drives a compressor (10) arranged on a common shaft (13), involves means for removing leakage air from the space surrounding the portion of the shaft between the turbine and the compressor. In such an installation, the portion of the shaft between the turbine (1) and the compressor (10) is shaped as a drum (14) and is surrounded by a drum cover (15), which forms an annular duct (20). A labyrinth seal (21) sealing against the drum cover (15) is disposed in the annular duct (20), and the drum cover (15) together with the end face (18) of the turbine rotor (3) defines a radially directed wheel side space (19). Separate lines (22) for carrying the turbine-rotor cooling air from the compressor (10) to the end face (18) of the turbine rotor (3) are provided, and the connection between these lines (22) and the wheel side space (19) is made via at least one swirl nozzle (23). Cooling devices (24) are provided for introducing cooling air to the turbine rotor (3) and its moving-blade rings, and all the cooling air for the rotor side for the turbine (1) is extracted from the compressor (10) in the area of the compressor discharge. At least one suction device (25) for removing the leakage air and a portion of the cooling air from the annular duct is connected to the annular duct in the area of the drum labyrinth (21). The suction device (25) is connected to deliver the removed leakage air to cooling devices for the rear turbine stages.

대표청구항 ▼

An apparatus for cooling an axial-flow gas turbine, comprising: a multi-stage turbine and a compressor connected on a common shaft, the turbine having a rotor, wherein a portion of the shaft between the turbine and the compressor is formed as a drum, a drum cover surrounding the drum shaped portion

An apparatus for cooling an axial-flow gas turbine, comprising: a multi-stage turbine and a compressor connected on a common shaft, the turbine having a rotor, wherein a portion of the shaft between the turbine and the compressor is formed as a drum, a drum cover surrounding the drum shaped portion of the shaft and spaced therefrom to define an annular duct connected to the compressor to carry leakage air from the compressor, a labyrinth seal mounted on the drum cover and disposed in the annular duct for sealing the drum shaped portion of the shaft against the drum cover, wherein an end face of the drum cover and an adjacent end face of the turbine rotor define therebetween a radially directed wheel side space connected to the annular duct, at least one separate line for carrying cooling air from the compressor to the end face of the turbine rotor, at least two swirl nozzles disposed in the at least one separate line to introduce air from the line into the wheel side space, cooling devices for introducing cooling air from the wheel side space to the turbine rotor and moving-blade rings on the rotor, and at least one suction device connected to the annular duct in an area of the labyrinth seal for removing the leakage air from the annular duct.