Methods and apparatus for supplying air to gas turbine engines

• US 6,412,284 B1
• Filed: 03/07/2001
• Issued: 07/02/2002
• Est. Priority Date: 03/07/2001
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Horner, Michael William
• Primary Examiner(s): Gartenberg, Ehud
• Application Number:
  US09/801,120
• Time in Patent Office: 482 Days
• Field of Search: 607/72, 60/395.11, 60/395.2, 607/97
• US Class Current: 60/772
• CPC Class Codes: F01D 25/30 Exhaust heads, chambers, or the like
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep

Abstract

A gas turbine engine assembly including a gas turbine engine mounted within a module and including an inlet in flow communication with a module inlet area and a module exhaust area is described. The turbine engine also includes an exhaust, and is mounted within an engine area between the module inlet and exhaust areas. More specifically, the gas turbine engine is mounted such that the engine exhaust is in flow communication with the module exhaust area. Because the module also includes a secondary supply duct, the gas turbine engine is in flow communication with the module inlet and exhaust areas.

Claims

1. A method for supplying air to a gas turbine engine positioned within a housing including an air inlet module, ail exhaust gas module, and a duct, the inlet module connecting an inlet of the gas turbine engine to the atmosphere, the exhaust gas module including a first conduit and a second conduit, the first conduit within the second conduit and connecting an exhaust of the gas turbine engine to the atmosphere, the second conduit open only to the atmosphere, the duct connected to the exhaust gas module second conduit anti in flow communication with the gas turbine engine inlet, said method comprising:

operating the gas turbine engine within the module such that exhaust airflow exits the engine through the exhaust module first conduit; and

supplying air to the gas turbine engine inlet from the exhaust module second conduit through the duct.

2. A method in accordance with claim 1 wherein said supplying air to the gas turbine engine inlet further comprises supplying air to the housing inlet module through the duct.

3. A method in accordance with claim 1 wherein the housing further includes an inlet barrier wall extending around the gas turbine engine inlet, said supplying air to the gas turbine engine inlet further comprises supplying air to the gas turbine inlet upstream from the inlet barrier wall.

4. A method in accordance with claim 1 wherein the housing further includes an inlet barrier wall extending around the gas turbine engine inlet, said supplying air to the gas turbine engine inlet further comprises supplying air to the gas turbine inlet through a plurality of vents within the inlet barrier wall.

5. A method in accordance with claim 1 wherein said operating the gas turbine engine within the module further comprises discharging exhaust airflow through an exhaust module first conduit that is coaxially aligned with respect to the exhaust module second conduit.

6. A gas turbine engine housing for a gas turbine engine including an inlet and an exhaust, said housing comprising:

an air inlet module connecting the gas turbine engine inlet to the atmosphere;

an exhaust gas module comprising a first conduit and a second conduit, said first conduit within said second conduit and connecting the gas turbine engine exhaust to the atmosphere, said second conduit open only to the atmosphere; and

a duct connecting the turbine inlet in flow communication with said exhaust gas module second conduit.

7. A gas turbine engine housing in accordance with claim 6 wherein said duct comprises a shutoff damper configured to control flow therethrough.

8. A gas turbine engine housing in accordance with claim 6 wherein said exhaust gas module second conduit in selective flow communication with tie gas turbine engine inlet.

9. A gas turbine engine housing in accordance with claim 6 further comprising an inlet barrier wall extending around the gas turbine engine inlet between said air inlet module and said exhaust gas module.

10. A gas turbine engine housing in accordance with claim 9 wherein said duct connected to said air inlet module upstream from said inlet barrier wall.

11. A gas turbine engine housing in accordance with claim 9 wherein said inlet barrier wall further comprises a plurality of vents in flow communication with said duct and the gas turbine engine inlet.

12. A gas turbine engine housing in accordance with claim 6 wherein said duct connected to said air inlet module upstream from the gas turbine engine inlet.

13. A gas turbine engine assembly comprising:

a gas turbine engine comprising an inlet and an exhaust; and

a housing comprising an air inlet module, an exhaust module, and a duct coupled to said exhaust module, said gas turbine engine within said housing, said air inlet module connecting said gas turbine engine inlet to the atmosphere, said exhaust gas module comprising a first conduit and a second conduit, said first conduit within said second conduit and connecting said gas turbine engine exhaust to the atmosphere, said second conduit open only to the atmosphere, said duct connecting said gas turbine inlet in flow communication with said exhaust gas module second conduit.

14. A gas turbine engine assembly in accordance with claim 13 wherein said housing second conduit substantially coaxial with said housing first conduit.

15. A gas turbine engine assembly in accordance with claim 13 wherein said housing duct comprises a shutoff damper configured to control flow therethrough.

16. A gas turbine engine assembly in accordance with claim 13 wherein said housing exhaust gas module in selective flow communication with said gas turbine engine inlet.

17. A gas turbine engine assembly in accordance with claim 13 wherein said housing further comprises an inlet barrier wall extending around said gas turbine engine inlet between said housing air inlet module and said housing exhaust gas module.

18. A gas turbine engine assembly in accordance with claim 17 wherein said housing duct connected to said housing air inlet module upstream from said housing inlet barrier wall.

19. A gas turbine engine assembly in accordance with claim 17 wherein said housing inlet barrier wall comprises a plurality of vents in flow communication with said housing duct and said gas turbine engine inlet.