Patent ID: 7036318

Claim:
A gas turbine electric powerplant, comprising: an aeroderivative split-shaft gas turbine engine; an engine mounting system for affixing said gas turbine engine to a mounting surface, said engine mounting system comprising: a mounting frame substantially encircling a portion of said gas turbine engine; a plurality of mounting shafts affixed to and spaced about the circumference of said gas turbine engine; and a plurality of linear bearings affixed to said mounting frame, each linear bearing provided to receive a corresponding one of said mounting shafts; a speed reducer coupled to an output shaft of said gas turbine engine, said speed reducer having an output shaft that rotates at a slower speed than said output shaft of said gas turbine engine; an electric generator coupled to said output shaft of said speed reducer, said electric generator selected to provide a predetermined electric power output when driven by said gas turbine engine; a fuel valve for metering a supply of fuel to said gas turbine engine; a cooling system for providing cooling fluid to said speed reducer and said gas turbine engine, said cooling system having at least one cooling pump and at least one cooling fluid reservoir; a turbine engine overspeed control system, said system adapted to slow or shut down said turbine engine if an overspeed condition thereof is detected; sensors placed at various locations on said gas turbine electric powerplant, said sensors for monitoring and reporting on a plurality of conditions selected from the group consisting of turbine speed, turbine engine exhaust gas temperature, turbine engine inlet temperature, turbine engine oil temperature and pressure, gearbox oil temperature and pressure, gearbox output shaft speed, generator output voltage, fuel flow rate, and inlet guide vane position; and a microprocessor-based control system for receiving signals from said sensors and controlling said gas turbine electric powerplant, said microprocessor-based control system further adapted to detect an overspeed condition of said gas turbine engine and to activate said turbine engine overspeed control system in response thereto.