Systems and methods for bypassing an inlet air treatment filter

1. A method of assembling an inlet air filter assembly for use with a turbine engine system, said method comprising:

coupling an inlet hood having a base member that defines an inlet and an upper hood member that extends from the base member, to an air filter enclosure, such that an airflow path is defined between the inlet hood and the air filter enclosure;

coupling a pre-filter to the base member, such that the pre-filter is positioned within the airflow path; and

coupling a filter bypass assembly to the pre-filter for selectively moving the pre-filter between an operating position wherein an airflow passes through the at least a portion of the pre-filter, and a bypass position wherein the airflow enters the inlet hood without flowing through at least a portion of the pre-filter, during operation of the turbine engine system.

2. A method in accordance with claim 1 further comprising coupling an actuator to the pre-filter to selectively move the pre-filter between the operating and bypass positions.

3. A method in accordance with claim 1 further comprising coupling a pressure sensor to the pre-filter for sensing a pressure drop across the pre-filter.

4. A method in accordance with claim 1 further comprising coupling a temperature sensor to the pre-filter for sensing a temperature of ambient air entering the inlet air filter assembly.

5. An inlet air filter assembly for use in a gas turbine engine system, said inlet air filter assembly comprising:

an inlet hood coupled in flow communication with an air filter enclosure, said inlet hood comprising a base member that defines an inlet and an upper hood member that extends from the base member and a pre-filter coupled to the base member; and

a filter bypass assembly coupled to said pre-filter for selectively moving said pre-filter between an operating position wherein an airflow passes through at least a portion of the pre-filter and a bypass position wherein the airflow enters the inlet hood without flowing through at least a portion of the pre-filter, during operation of the gas turbine engine.

6. An inlet air filter assembly in accordance with claim 5 , wherein said filter bypass assembly further comprises a hydraulic actuator coupled to said pre-filter for selectively moving said pre-filter between the operating and bypass positions.

7. An inlet air filter assembly in accordance with claim 5 , wherein said filter bypass assembly comprises a pressure sensor coupled to said pre-filter for measuring a pressure drop across said pre-filter.

8. An inlet air filter assembly in accordance with claim 5 , wherein said filter bypass assembly comprises a temperature sensor coupled to said pre-filter for measuring a temperature of ambient air entering said inlet air filter assembly.

9. An inlet air filter assembly in accordance with claim 5 , wherein said pre-filter comprises at least one of a coalescing pad and a moisture separator.

10. An inlet air filter assembly in accordance with claim 5 , wherein said filter bypass assembly further comprises a biasing mechanism extending between an inlet hood upper member and said pre-filter for biasing said pre-filter to the bypass position.

11. An inlet air filter assembly in accordance with claim 10 , wherein said filter bypass assembly further comprises a fastener assembly coupled to said pre-filter for securing said pre-filter in the operating position.

12. An inlet air filter assembly in accordance with claim 11 , wherein said filter bypass assembly further comprises a valve coupled to said fastener assembly for selectively moving said fastener assembly, said pre-filter selectively moves in response to movement of said fastener assembly.

13. An inlet air filter assembly in accordance with claim 5 , wherein said filter bypass assembly further comprises a pulley assembly coupled to said pre-filter for selectively moving said pre-filter between the operating and bypass positions.

14. A gas turbine engine system comprising:

a compressor;

a combustor in flow communication with said compressor to receive at least some of the air discharged by said compressor; and

an inlet air filter assembly coupled in flow communication with said compressor; said inlet air filter assembly comprising a filter bypass assembly coupled to a pre-filter positioned within an inlet hood having a base member that defines an inlet and an upper hood member that extends from the base member, said filter bypass assembly configured to selectively move said pre-filter between an operating position, wherein an airflow passes through at least a portion of the pre-filter and a bypass position, wherein the airflow enters the inlet hood without flowing through at least a portion of the pre-filter, during operation of said gas turbine engine system.

15. A gas turbine engine system in accordance with claim 14 , wherein said filter bypass assembly further comprises an actuator coupled to said pre-filter for selectively moving said pre-filter between the operating and bypass positions.

16. A gas turbine engine system in accordance with claim 14 , wherein said filter bypass assembly comprises a pressure sensor coupled to said pre-filter for measuring a pressure drop across said pre-filter.

17. A gas turbine engine system in accordance with claim 14 , wherein said filter bypass assembly comprises a temperature sensor coupled to said pre-filter for measuring a temperature of ambient air entering said inlet air filter assembly.

18. A gas turbine engine system in accordance with claim 14 , wherein said pre-filter comprises at least one of a coalescing pad and a moisture separator.

19. A gas turbine engine system in accordance with claim 14 , wherein said filter bypass assembly further comprises:

a biasing mechanism extending between an inlet hood upper member and said pre-filter for biasing said pre-filter to the bypass position;

a fastener assembly coupled to said pre-filter for securing said pre-filter in the operating position; and

a valve coupled to said fastener assembly for selectively moving said fastener assembly, said pre-filter selectively moves in response to movement of said fastener assembly.

20. A gas turbine engine system in accordance with claim 14 , wherein said filter bypass assembly further comprises a pulley assembly coupled to said pre-filter for selectively moving said pre-filter between the operating and bypass positions.