Patent ID: 8584464

Claim:
A method for assembling a gas turbine engine assembly, said method comprising: providing a first skid including: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; and a turbine generator including a power turbine rotatably coupled to an electrical generator such that the power turbine drives the electrical generator; providing a second skid including a low pressure compressor, a variable bypass valve, and a variable frequency motor, wherein each of the first and second skids is configured to be shipped; coupling the variable bypass valve between the low-pressure compressor and the core gas turbine engine to facilitate controlling a quantity of air by discharging airflow from the low-pressure compressor to the atmosphere during predetermined operational conditions; coupling an intercooler between the low-pressure compressor and the core gas turbine engine to facilitate channeling air along a path that is aligned substantially along a centerline axis of the core gas turbine engine; coupling the electrical generator to the variable frequency motor such that the variable frequency motor is driven by the electrical generator; and coupling the low-pressure compressor between the core gas turbine engine and the variable frequency motor such that the low-pressure compressor is driven only by the motor to facilitate supplying compressed air to the high-pressure compressor.