Patent ID: 6907738

Claim:
A pilot air system for a combustor of a gas turbine, the system comprising: a pilot air compressor having inlet connectable to in to a main passageway, wherein said main passageway receives compressed air from a compressor for the gas turbine; a pilot air platform positioned adjacent to the combustor of the gas turbine, wherein said pilot air compressor is positioned on said platform; an inline throttling valve coupled to the first main passageway; a by-pass passageway for the pilot air, proximate to the platform, and arranged in parallel to the main passageway and the pilot air compressor, wherein said by-pass passageway receives pilot air from the main passageway downstream of the pilot air compressor and passes a portion of the compressed pilot air to the main passageway upstream of the pilot air compressor; a by-pass throttling valve inline with said by-pass passageway to meter pilot air flowing through said by-pass passageway, and said main passageway having an outlet connectable to said combustor.