Patent ID: 7353656

Claim:
A gas turbine unit comprising: a compressor for compressing a stream of intake air supplied thereto and discharging compressed air; a combustion chamber in which fuel is combusted with the compressed air discharged from said compressor; and a turbine driven by hot combustion air discharged from said combustion chamber; wherein said compressor is working with a pressure ratio larger than 15 bar; wherein at least one liquid droplet injection device is provided on an upstream side of said compressor for injecting liquid into the stream of intake air to increase shaft power generated by the gas turbine unit, said injection device allowing an addition of liquid mass flow in the form of liquid droplets; and wherein responsive to a desired increase of shaft power output the at least one liquid droplet injection device delivers the liquid to reach a discrete rate of mass flow within 60 seconds; and further comprising a fuel control valve that adjusts fuel mass flow in order to maintain firing temperatures of the gas turbine unit, wherein the at least one liquid droplet injection device is operable with an on/off-control signal, and wherein the fuel control valve is controllable as a function of liquid droplet injection using a single feed forward signal synchronized to the on/off-control signal.