초록 ▼

A method for assembling a gas turbine engine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, and coupling a low-pressure compressor between the core gas turbine engine and a motor such that the low-pressure compres

A method for assembling a gas turbine engine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, and coupling a low-pressure compressor between the core gas turbine engine and a motor such that the low-pressure compressor is driven only by the motor.

대표청구항 ▼

1. 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 elec

1. 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. 2. A method in accordance with claim 1, wherein coupling the intercooler between the low-pressure compressor and the core gas turbine engine facilitates reducing a volume of air between the low-pressure compressor and the high-pressure compressor. 3. A method in accordance with claim 2 further comprising coupling a booster duct between the low-pressure compressor and the intercooler such that the booster duct is substantially concentrically aligned with a centerline axis of the core gas turbine engine. 4. A method in accordance with claim 3 further comprising coupling the variable bypass valve in flow communication with the booster duct and upstream of the intercooler to facilitate controlling a quantity of air flowing from the low-pressure compressor to the high-pressure compressor by matching an output airflow from the low-pressure compressor to an input airflow requirement of the high-pressure compressor. 5. A method in accordance with claim 3 further comprising coupling a high-pressure compressor inlet duct between the intercooler and the high-pressure compressor such that the inlet duct is substantially concentrically aligned with a centerline axis of the core gas turbine engine. 6. A method in accordance with claim 1 further comprising coupling a variable frequency drive system to the motor to facilitate varying a rotational speed of the motor. 7. A method in accordance with claim 1 further comprising coupling a variable frequency drive system to the motor to facilitate varying a rotational speed of the low-pressure compressor. 8. A method in accordance with claim 1 further comprising: coupling a variable frequency drive system to the motor to facilitate varying a rotational speed of the low-pressure compressor; andtransmitting power from the generator to the variable frequency drive system to facilitate driving the motor. 9. A gas turbine engine assembly comprising: a first skid comprising a core gas turbine engine comprising a high-pressure compressor, a combustor, and a high-pressure turbine and a turbine generator coupled to said core gas turbine engine, said turbine generator including a power turbine rotatably coupled to an electrical generator such that the power turbine drives the electrical generator; anda second skid comprising a variable frequency motor, a low-pressure compressor, and a variable bypass valve, wherein said electrical generator is coupled to said variable frequency motor such that said variable frequency motor is driven by said electrical generator, said low-pressure compressor coupled between said core gas turbine engine and said motor such that said low-pressure compressor is driven only by said motor to facilitate supplying compressed air to said high-pressure compressor, wherein said variable bypass valve is coupled between said low-pressure compressor and said core gas turbine engine to facilitate controlling a quantity of air by discharging airflow to the atmosphere during predetermined operational conditions, wherein each of the first and second skids is configured to be shipped. 10. A gas turbine engine assembly in accordance with claim 9 further comprising an intercooler coupled between said low-pressure compressor and said core gas turbine engine, said intercooler substantially concentrically aligned with a centerline axis of said core gas turbine engine. 11. A gas turbine engine assembly in accordance with claim 10 further comprising a booster duct coupled between said low-pressure compressor and said intercooler such that said booster duct is substantially concentrically aligned with a centerline axis of said core gas turbine engine. 12. A gas turbine engine assembly in accordance with claim 11, wherein said variable bypass valve is coupled in flow communication with said booster duct and upstream of said intercooler, said variable bypass valve configured to control a quantity of air flowing from the low-pressure compressor to the high-pressure compressor by matching an output airflow from the low pressure compressor to an input airflow requirement of the high-pressure compressor. 13. A gas turbine engine assembly in accordance with claim 11 further comprising a high-pressure compressor inlet duct coupled between said intercooler and said high-pressure compressor such that said inlet duct is substantially concentrically aligned with a centerline axis of said core gas turbine engine. 14. A gas turbine engine assembly in accordance with claim 9 further comprising a variable frequency drive system coupled to said motor, said drive system configured to vary a rotational speed of said motor. 15. A gas turbine engine assembly in accordance with claim 9 further comprising a variable frequency drive system coupled to said motor, said drive system configured to vary a rotational speed of said low-pressure compressor. 16. A gas turbine engine assembly in accordance with claim 9 further comprising: a variable frequency drive system coupled to said motor to facilitate varying a rotational speed of said low-pressure compressor, said generator configured to transmit power to said variable frequency drive system to facilitate driving said motor.