Anti-icing system using radiant infrared energy from turbine exhaust flues

1. A method for assembling a gas turbine engine, said method comprising: providing an air inlet including an air filter assembly to a core engine within the gas turbine engine, wherein the air inlet is oriented to channel air into the core engine; and the air inlet is upstream of the core engine; coupling an exhaust flue including a radiating portion to the core engine, wherein the exhaust flue is oriented to channel exhaust gases from the core engine; and positioning the exhaust flue within the air inlet such that substantially all of the exhaust gases within the air inlet are confined within the radiating portion of the exhaust flue, and the exhaust flue extends at least partially within the air inlet, wherein the radiating portion is oriented to emit infrared radiation towards the air filter assembly and such that the exhaust gases are channeled out of the air inlet via the exhaust flue.

2. A method in accordance with claim 1 , wherein positioning the exhaust flue further comprises extending the exhaust flue between a first side of the air inlet to an opposing second side of the air inlet.

3. A method in accordance with claim 2 , wherein extending the exhaust flue further comprises orienting the exhaust flue to be substantially perpendicular to at least one of the first and second sides.

4. A method in accordance with claim 1 , wherein extending the exhaust flue further comprises orienting the exhaust flue to be substantially parallel to the air filter assembly.

5. A method in accordance with claim 1 , wherein positioning the exhaust flue further comprises positioning the radiating portion upstream from the air filter assembly.

6. A method in accordance with claim 1 , wherein providing an air inlet further comprises providing the air inlet having a first diameter, and wherein coupling an exhaust flue further comprises providing the exhaust flue having a second diameter that is smaller than the first diameter.

7. An exhaust flue for use with a gas turbine engine including a core engine and an air inlet including an air filter assembly, said air inlet located upstream of the core engine, said exhaust flue oriented to channel exhaust gases from the core engine, said exhaust flue comprising a radiating portion within the air inlet such that substantially all of the exhaust gases within the air inlet are confined within said radiating portion of said exhaust flue, said exhaust flue extends at least partially within the air inlet, and wherein said radiating portion is oriented to emit infrared radiation towards the air filter assembly and such that the exhaust gases are channeled out of the air inlet via the exhaust flue.

8. An exhaust flue in accordance with claim 7 , wherein said exhaust flue extends between a first side of the air inlet to an opposing second side of the air inlet.

9. An exhaust flue in accordance with claim 8 , wherein said exhaust flue is oriented to be substantially perpendicular to at least one of the first and second sides.

10. An exhaust flue in accordance with claim 7 , wherein said exhaust flue is oriented to be substantially parallel to the air filter assembly.

11. An exhaust flue in accordance with claim 7 , wherein said radiating portion is positioned upstream from the air filter assembly.

12. An exhaust flue in accordance with claim 7 , wherein said exhaust flue has a diameter that is smaller than a diameter of the air inlet.

13. A turbine engine comprising: a core engine comprising an upstream portion and a downstream portion; an air inlet comprising an air filter assembly, said air inlet coupled to said upstream portion of said core engine to channel ambient air into said core engine; said air inlet located upstream of the core engine; and an exhaust flue comprising a radiating portion positioned within said air inlet such that the exhaust flue extends at least partially within the air inlet, said exhaust flue coupled to said downstream portion of said core engine to channel exhaust gases from said core engine, wherein substantially all of the exhaust gases within the air inlet are confined within said radiating portion of said exhaust flue, said radiating portion oriented to emit infrared radiation towards said air filter assembly, said exhaust flue configured to channel the exhaust gases out of said air inlet.

14. A turbine engine in accordance with claim 13 , wherein said exhaust flue extends between a first side of said air inlet to an opposing second side of said air inlet.

15. A turbine engine in accordance with claim 14 , wherein said exhaust flue is oriented to be substantially perpendicular to at least one of said first and second sides.

16. A turbine engine in accordance with claim 13 , wherein said exhaust flue is oriented to be substantially parallel to said air filter assembly.

17. A turbine engine in accordance with claim 13 , wherein said radiating portion is positioned upstream from said air filter assembly.

18. A turbine engine in accordance with claim 13 , wherein said air inlet has a first diameter and said exhaust flue has a second diameter that is smaller than the first diameter.