FUEL COMPRESSOR SYSTEM FOR GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To provide a fuel compressor system for a gas turbine not becoming large-sized nor jetting fuel gas into the atmosphere. SOLUTION: A check valve 15 is interposed at an intermediate part of a fuel intake passage 12 of a fuel compressor system 10 for a gas turbine, and the fuel intake passage 12 and the intake side low pressure part of a fuel compressor 11 are composed of pressure tight piping and a pressure tight member capable of withstanding pressure rise in the case of the emergency stop of the fuel compressor system 10 for the gas turbine. The system 10 can therefore withstand the pressure sufficiently without providing a safety valve at the fuel intake passage 12 or the intake side low pressure part to jet fuel gas outside, and there is no need to newly add a storage tank to the intake side so as to provide the system not becoming large-sized nor jetting fuel gas into the atmosphere.