ENGINE PROPULSION SYSTEM AND METHODS OF ASSEMBLING THE SAME

• US 20080141653A1
• Filed: 12/13/2006
• Published: 06/19/2008
• Est. Priority Date: 12/13/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Peck, Robert Andrew
• Granted Patent: US 8,205,821 B2
• Time in Patent Office: Days
• US Class Current: 60/224
• CPC Class Codes: B64C 27/18 the means being jet-reaction apparatus
• CPC Class Codes: F02K 3/12 characterised by having more than one gas turbine
• CPC Class Codes: F02K 7/005 the engine comprising a rotor rotating under the actions of jets issuing from this rotor
• CPC Class Codes: F02K 7/08 the jet being continuous

Abstract

A method for exhausting gas from an aircraft engine assembly is provided. The method includes coupling a first exhaust duct in fluid communication only to a first engine. The first exhaust duct includes a primary outlet and a secondary outlet. The method further includes coupling a second exhaust duct in fluid communication only to a second engine. The second exhaust duct includes a primary outlet and a secondary outlet. The method also includes aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet.

Claims

1. A method for exhausting gas from an aircraft engine assembly, said method comprising:

coupling a first exhaust duct in fluid communication only to a first engine, the first exhaust duct comprises a primary outlet and a secondary outlet;

coupling a second exhaust duct in fluid communication only to a second engine, the second exhaust duct comprises a primary outlet and a secondary outlet; and

aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet.

2. A method in accordance with claim 1 further comprising:

coupling the first exhaust duct to a first cruise nozzle; and

coupling the second exhaust duct to a second cruise nozzle.

3. A method in accordance with claim 1 further comprising:

coupling the first exhaust duct to at least one first lift post nozzle; and

coupling the second exhaust duct to at least one second lift post nozzle, wherein a portion of the at least one first lift post nozzle is concentric with a portion of the at least one second lift post nozzle.

4. A method in accordance with claim 1 further comprising coupling at least one directional control to at least one of the first exhaust duct and the second exhaust duct.

5. A method in accordance with claim 1 further comprising:

coupling a first plenum to the first exhaust duct; and

coupling a second plenum to the second exhaust duct, wherein a portion of the first plenum is concentric with a portion of the second plenum.

6. A method in accordance with claim 5 further comprising:

coupling the first plenum to at least one of a first wing outlet and a first rotor outlet; and

coupling the second plenum to at least one of a second wing outlet and a second rotor outlet,

7. A method in accordance with claim 6 further comprising

coupling a variable area tip valve to the first rotor outlet;

and

coupling a variable area tip valve to the second rotor outlet.

8. An engine assembly comprising:

a first engine comprising a first exhaust duct coupled in fluid communication only to said first engine, said first exhaust duct comprises a primary outlet and a secondary outlet; and

a second engine comprising a second exhaust duct coupled in fluid communication only to said second engine, said second exhaust duct comprises a primary outlet and a secondary outlet, a portion of said first engine secondary outlet is aligned substantially concentrically within a portion of said second engine secondary outlet.

9. An engine assembly in accordance with claim 8 wherein said engine assembly further comprises a first plenum coupled to said first exhaust duct and a second plenum coupled to said second exhaust duct, wherein a portion of said first plenum is aligned substantially concentrically within a portion of said second plenum.

10. An engine assembly in accordance with claim 9 wherein said first plenum is coupled to at least one of a first wing outlet and a first rotor outlet, and said second plenum is coupled to at least one of a second wing outlet and a second rotor outlet, said first rotor outlet comprises at least one first variable area tip valve, and wherein said second rotor outlet comprises at least one second variable area tip valve.

11. An engine assembly in accordance with claim 8 wherein said first engine primary outlet is coupled to a first cruise nozzle and said second engine primary outlet is coupled to a second cruise nozzle.

12. An engine assembly in accordance with claim 8 wherein said first exhaust duct is coupled to at least one first lift post nozzle, and said second exhaust duct is coupled to at least one second lift post nozzle, wherein a portion of said at least one first lift post nozzle is aligned substantially concentrically within a portion of said at least one second lift post nozzle.

13. An engine assembly in accordance with claim 8 further comprising at least one directional control coupled to at least one of said first exhaust duct and said second exhaust duct.

14. A propulsion system for an aircraft, said propulsion system comprising:

a first engine comprising a first exhaust duct coupled in flow communication only to said first engine; and

a second engine comprising a second exhaust duct coupled in flow communication only to said second engine, wherein said first exhaust duct comprises a primary exhaust and a secondary exhaust, said second exhaust duct comprises a primary exhaust and a secondary exhaust, and a portion of said first engine secondary exhaust is aligned substantially concentrically within a portion of said second engine secondary exhaust.

15. A propulsion system in accordance with claim 14 wherein said first engine primary exhaust is coupled to a first cruise nozzle and said second engine primary exhaust is coupled to a second cruise nozzle.

16. A propulsion system in accordance with claim 14 wherein said first exhaust duct is coupled to at least one first lift post nozzle, and said second exhaust duct is coupled to at least one second lift post nozzle, wherein said at least one first lift post nozzle is aligned substantially concentrically within said at lest one least one second lift post nozzle.

17. A propulsion system in accordance with claim 14 further comprising at least one directional control coupled to at least one of said first exhaust duct and said second exhaust duct.

18. A propulsion system in accordance with claim 14 wherein said propulsion system further comprises a first plenum coupled to said first exhaust duct and a second plenum coupled to said second exhaust duct, wherein a portion of said first plenum is aligned substantially concentrically within a portion of said second plenum.

19. A propulsion system in accordance with claim 17 wherein said first plenum is coupled to at least one of a first wing outlet and a first rotor outlet, and said second plenum is coupled to at least one of a first wing outlet and a first rotor outlet.

20. A propulsion system in accordance with claim 19 wherein said first rotor outlet comprises at least one first variable area tip valve, and wherein said second rotor outlet comprises at least one second variable area tip valve.