Methods and apparatus for exhausting gases from gas turbine engines

• US 6,742,339 B2
• Filed: 09/06/2002
• Issued: 06/01/2004
• Est. Priority Date: 09/06/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Horner, Michael W.
• Primary Examiner(s): Kim, Ted
• Application Number:
  US10/236,600
• Publication Number:
  US 20040045271A1
• Time in Patent Office: 634 Days
• Field of Search: 607/72, 607/96, 607/97, 607/98, 60/395, 181/218, 181/200, 181/204, 181/206, 181/220
• US Class Current: 60/772
• CPC Class Codes: F01D 25/30 Exhaust heads, chambers, or the like
• CPC Class Codes: F01D 25/32 Collecting of condensation water; Drainage ; Removing solid particles
• CPC Class Codes: F02C 7/00 Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants controlling F02C9/00
• CPC Class Codes: F02C 7/04 Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

A method enables a gas turbine engine positioned within a module to be operated. The engine includes an inlet and an exhaust, and the module includes an inlet area, an exhaust area, and an engine area extending therebetween and housing the engine. The exhaust area includes an exhaust duct and an outlet. The engine is operated such that inlet air is routed through the module inlet and into the engine inlet, wherein exhaust gases are discharged through the module exhaust duct and substantially perpendicularly from the gas turbine engine. The exhaust gases are discharged from the module outlet in a direction that is at least ninety degrees offset from exhaust gases flowing within the exhaust duct. Cooling fluid is discharged from the module engine area through a cooling system exhaust, such that the discharged fluid flows through the cooling system exhaust and around the module exhaust area.

Claims

1. A method for operating a gas turbine engine positioned within a module, the engine including an inlet and an exhaust, the module including an inlet area, an exhaust area, and an engine area extending therebetween and housing the engine, the exhaust area including an exhaust duct and an outlet, said method comprising:

operating the engine such that inlet air is routed through the module inlet and into the engine inlet;

discharging exhaust gases from the engine through the module exhaust duct such that the exhaust gases are routed substantially perpendicularly from the gas turbine engine;

discharging exhaust gases from the module outlet such that the exhaust gases are discharged in a direction that is at least ninety degrees offset from exhaust gases flowing within the exhaust duct;

supplying cooling fluid to the module engine area through a cooling system inlet; and

discharging cooling fluid from the module engine area through a cooling system exhaust, such that the discharged cooling fluid flows through the cooling system exhaust and around the module exhaust area disposed within the cooling system exhaust.

2. A method in accordance with claim 1 wherein discharging cooling fluid from the module engine area further comprises discharging cooling fluid from the module engine area to facilitate suppressing an exhaust infrared signature of the gas turbine engine.

3. A method in accordance with claim 2 wherein discharging exhaust gases from the engine through the module exhaust duct further comprises changing a direction of the flow of the exhaust gases by using at least one of a splitter and turning vanes.

4. A method in accordance with claim 2 wherein discharging exhaust gases from the engine through the module exhaust duct further comprises changing a direction of the flow of the exhaust gases without accelerating the exhaust flow.

5. A method in accordance with claim 2 wherein discharging exhaust gases from the engine through the module exhaust duct further comprises discharging exhaust gases from the engine through an insulated exhaust duct to facilitate reducing heat transfer between the exhaust duct and the cooling system exhaust.

6. A gas turbine engine assembly comprising:

a module comprising an inlet area, an engine area, and an exhaust area, said engine area extending between said inlet and exhaust areas to define a cavity, said module exhaust area comprising an exhaust duct and an outlet extending in flow communication from said exhaust duct;

a gas turbine engine within said module cavity, said engine comprising an inlet and an exhaust, said turbine engine exhaust adjacent said module exhaust area, said module exhaust duct for routing exhaust gases discharged from said gas turbine engine exhaust substantially perpendicularly from said gas turbine engine, said exhaust area outlet for routing exhaust gases discharged from said exhaust duct in direction that is at least ninety degrees offset with respect to exhaust gases flowing within said exhaust duct; and

a cooling system comprising an inlet and an exhaust, said inlet for supplying cooling fluid into said module engine area external said gas turbine engine, said cooling system exhaust for discharging cooling fluid from said module engine area, said module exhaust area concentrically disposed within said cooling system exhaust.

7. A gas turbine assembly in accordance with claim 6 wherein said module exhaust area and said cooling system configured to facilitate suppressing an exhaust infrared signature of said gas turbine engine.

8. A gas turbine assembly in accordance with claim 7 wherein said module exhaust duct further comprises a plurality of turning vanes for routing exhaust gases flowing therein towards said module exhaust area outlet.

9. A gas turbine assembly in accordance with claim 7 wherein said module exhaust area outlet further comprises a hood extending across said module exhaust duct, said hood comprising a splitter configured to discharge exhaust gases from said exhaust duct in at least two different directions.

10. A gas turbine assembly in accordance with claim 7 wherein said module exhaust area outlet further comprises a hood extending across said module exhaust duct, said hood comprising a splitter configured to discharge exhaust gases radially outward and circumferentially from said exhaust duct.

11. A gas turbine assembly in accordance with claim 7 wherein said module exhaust area outlet configured to route exhaust gases discharged from said exhaust duct without accelerating the exhaust gases.

12. A gas turbine assembly in accordance with claim 7 wherein said module exhaust duct comprises insulated walls.

13. An exhaust system for a gas turbine engine having an inlet and an exhaust, said exhaust system comprising:

a module comprising an inlet area, an exhaust area, and an engine area extending therebetween, the engine disposed within said module engine area such that the engine exhaust is in flow communication with said module exhaust area, said module exhaust area comprising an exhaust duct and an outlet, said exhaust duct for routing exhaust gases discharged from said engine exhaust substantially perpendicularly from the gas turbine engine, said exhaust area outlet for routing exhaust gases discharged from the exhaust duct in a direction that is at least ninety degrees offset from exhaust gases flowing through said exhaust duct; and

a cooling system comprising an inlet and an exhaust, said inlet coupled to said module engine area for routing cooling fluid into said module engine area, said cooling system exhaust coupled to said module engine area for routing cooling fluid from said module engine area, said module exhaust area concentrically aligned within said cooling system exhaust.

14. An engine exhaust system in accordance with claim 13 wherein said module exhaust area and said cooling system configured to facilitate suppressing an exhaust infrared signature of the gas turbine engine.

15. An engine exhaust system in accordance with claim 13 wherein said module exhaust duct further comprises a plurality of turning vanes for routing exhaust gases flowing therein towards said module exhaust area outlet.

16. An engine exhaust system in accordance with claim 13 wherein at least a portion of said module exhaust duct is insulated to facilitate reducing heat transfer from said exhaust duct to said cooling system exhaust.

17. An engine exhaust system in accordance with claim 13 wherein said module exhaust area outlet comprises a hood extending across said exhaust duct, said hood defining a plurality of passageways for channeling exhaust gases discharged from said exhaust duct radially outwardly from said exhaust duct in at least two different directions.

18. An engine exhaust system in accordance with claim 13 wherein said module exhaust area outlet comprises a hood extending across said exhaust duct, said hood configured to circumferentially discharge exhaust gases from said exhaust duct.

19. An engine exhaust system in accordance with claim 13 wherein said module exhaust area outlet has a substantially rectangular cross-sectional profile.

20. An engine exhaust system in accordance with claim 19 wherein said module exhaust duct has a substantially circular cross-sectional profile.