Patent ID: 6609360
Filing Date: 2003-08-26
Classification: F01K,F02C,F04D,F05D,Y02E,Y02T

Abstract:
A gas turbine, comprising:a compressor for compressing air supplied thereto and discharging the compressed air; a filter or a louver disposed on an upstream side of said compressor; a combustor in which fuel is combusted with the compressed air discharged from said compressor; a turbine driven by the combusted gas of said combustor; and a liquid droplet injection device for forming and injecting liquid droplets having droplet diameters principally from 1 &mgr;m to 50 &mgr;m into a space between said compressor and said filter or said louver, the liquid droplets being evaporated in the air so that the temperature of the air is lower than that of ambient air before entering said compressor with the air being compressed by said compressor and evaporated as the air flows through said compressor; said liquid droplet injection device including pressurized gas supply means for supplying pressurized gas to atomize the liquid droplets; and a control device for controlling an amount of liquid droplets to be injected into said space so that the injected liquid droplets can cool the air in said space by partial evaporation of the liquid droplets before entering said compressor and cool compressed air by evaporation of the remaining liquid droplets contained in the inlet air at the inside of said compressor.