Combustor assembly in a gas turbine engine

• US 8,375,726 B2
• Filed: 04/28/2009
• Issued: 02/19/2013
• Est. Priority Date: 09/24/2008
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Wiebe, David J., Fox, Timothy A.
• Primary Examiner(s): Kim, Ted
• Assistant Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US12/431,302
• Publication Number:
  US 20100071376A1
• Time in Patent Office: 1,393 Days
• Field of Search: 608/00, 607/39, 60752-754, 607/58, 607/60, 607/96, 60/393.7
• US Class Current: 60/800
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence
• CPC Class Codes: F23R 3/34 Feeding into different combustion zones
• CPC Class Codes: F23R 3/346 for staged combustion
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.

Claims

1. A combustor assembly in a gas turbine engine comprising a main casing, the combustor assembly comprising:

a combustor device coupled to the main casing comprising;

a flow sleeve for receiving pressurized air; and

a liner disposed radially inwardly from said flow sleeve having an inlet, an outlet and an inner volume;

a first fuel injection system associated with said flow sleeve for providing fuel which is adapted to be mixed with at least a portion of the pressurized air and ignited in said liner inner volume creating combustion products defining first working gases;

a transition duct downstream of an intermediate duct and having an inlet section and an outlet section that discharges gases to a turbine section; and

the intermediate duct having inlet and outlet portions and disposed between said liner and said transition duct so as to define a path for the first working gases to flow from said liner to said transition duct, wherein said intermediate duct inlet portion is associated with said liner outlet such that substantially unconstrained axial movement occurs between said intermediate duct and said liner and said intermediate duct outlet portion is associated with said transition duct inlet section such that substantially unconstrained axial movement occurs between said intermediate duct and said transition duct, wherein said flow sleeve surrounds said liner and said intermediate duct is integral with said flow sleeve.

2. A combustor assembly as set out in claim 1, further comprising a second fuel injection system comprising at least one fuel injector that injects fuel into said intermediate duct where the fuel injected by said at least one fuel injector mixes with remaining pressurized air and ignites to define further combustion products defining second working gases.

3. A combustor assembly as set out in claim 2, further comprising a first fuel supply structure in fluid communication with a source of fuel for delivering fuel from the source of fuel to said first fuel injection system.

4. A combustor assembly as set out in claim 3, further comprising a second fuel supply structure in fluid communication with the source of fuel for delivering fuel from the source of fuel to said second fuel injection system, said second fuel supply structure comprising at least one fuel supply tube having forward and aft portions.

5. A combustor assembly as set out in claim 4, further comprising a first cover structure located adjacent to an inner surface of said flow sleeve for isolating said forward portion of said at least one fuel supply tube from the pressurized air.

6. A combustor assembly as set out in claim 5, further comprising a second cover structure extending from an outer surface of said flow sleeve for isolating said aft portion of said at least one fuel supply tube from the pressurized air.

7. A combustor assembly as set out in claim 1, wherein a first spring clip structure is provided on one of said liner outlet and said intermediate duct inlet portion such that a friction fit coupling is provided between said liner and said intermediate duct.

8. A combustor assembly as set out in claim 7, wherein a second spring clip structure is provided on one of said intermediate duct outlet portion and said transition duct inlet section such that a friction fit coupling is provided between said intermediate duct and said transition duct.

9. A combustor assembly as set out in claim 1, wherein said flow sleeve comprises a plurality of apertures through which pressurized air passes to enter said flow sleeve.

10. A combustor assembly in a gas turbine engine comprising a main casing, the combustor assembly comprising:

a combustor device coupled to the main casing comprising;

a flow sleeve for receiving pressurized air; and

a liner disposed radially inwardly from said flow sleeve having an inlet, an outlet and an inner volume;

a transition duct downstream of an intermediate duct and having an inlet section and an outlet section that discharges gases to a turbine section;

the intermediate duct having inlet and outlet portions and disposed between said liner and said transition duct, wherein said intermediate duct inlet portion is associated with said liner outlet such that substantially unconstrained axial movement occurs between said intermediate duct and said liner and said intermediate duct outlet portion is associated with said transition duct inlet section such that substantially unconstrained axial movement occurs between said intermediate duct and said transition duct; and

a fuel injection system associated with said intermediate duct to inject fuel into said intermediate duct where the fuel mixes with pressurized air and ignites to define combustion products defining working gases, wherein said flow sleeve surrounds said liner and said intermediate duct is integral with said flow sleeve.

11. A combustor assembly as set out in claim 10, further comprising a fuel supply structure in fluid communication with a source of fuel for delivering fuel from a source of fuel to said fuel injection system, said fuel supply structure comprising at least one fuel supply tube having forward and aft portions.

12. A combustor assembly as set out in claim 11, further comprising a first cover structure located adjacent to an inner surface of said flow sleeve for isolating said forward portion of said at least one fuel supply tube from the pressurized air.

13. A combustor assembly as set out in claim 12, further comprising a second cover structure extending from an outer surface of said flow sleeve for isolating said aft portion of said at least one fuel supply tube from the pressurized air.

14. A combustor assembly as set out in claim 10, wherein a first spring clip structure is provided on one of said liner outlet and said intermediate duct inlet portion such that a friction fit coupling is provided between said liner and said intermediate duct.

15. A combustor assembly as set out in claim 14, wherein a second spring clip structure is provided on one of said intermediate duct outlet portion and said transition duct inlet section such that a friction fit coupling is provided between said intermediate duct and said transition duct.

16. A combustor assembly as set out in claim 10, wherein said fuel injection system comprises an annular manifold and a plurality of injectors extending radially inwardly from said manifold and passing through a corresponding aperture in said intermediate duct.