DUAL WALL STRUCTURE FOR USE IN A COMBUSTOR OF A GAS TURBINE ENGINE

• US 20100095680A1
• Filed: 10/22/2008
• Published: 04/22/2010
• Est. Priority Date: 10/22/2008
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Rudrapatna, Nagaraja S., Kettinger, Jon
• Application Number:
  US12/256,246
• Publication Number:
  US 20100095680A1
• Time in Patent Office: Days
• US Class Current: 60/754
• CPC Class Codes: F23R 2900/00017 Assembling combustion chamber liners or subparts
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A dual wall structure for a combustor of a gas turbine engine including an inner liner and an outer liner coupled to a combustor dome and defining a combustion chamber there between. Each of the inner liner and the outer liner include an outer wall and an inner wall. Each of the outer walls includes a plurality of impingement holes formed therein for allowing a coolant to flow therethrough. Each of the inner walls is coupled to the outer wall and a combustor dome and includes a plurality of heat shield panels. Each of the plurality of heat shield panels extends a longitudinal length of the combustor chamber and includes a plurality of side rails, an aft rail and a forward flange that when coupled to the outer wall defines a single cavity there between. A plurality of cavities being formed by the plurality of heat shield panels.

Claims

1. A dual wall structure for a combustor of a gas turbine engine comprising:

a combustor dome;

an outer liner coupled to said combustor dome; and

an inner liner coupled to said combustor dome and spaced a distance from said outer liner, wherein each of said outer liner and said inner liner comprise;

an outer wall including a plurality of impingement holes formed therein for allowing a coolant to flow therethrough; and

an inner wall coupled to said outer wall and the combustor dome, said inner wall comprising a plurality of heat shield panels, each having a hot side and a cold side, said cold side having a plurality of side rails, an aft rail and a forward angled flange that when coupled to the outer wall define a cavity there between, a plurality of cavities formed by the plurality of heat shield panels;

wherein each of said plurality of heat shield panels extends a longitudinal length of said combustor;

wherein each of said plurality of heat shield panels includes a plurality of effusion holes for allowing said coolant to flow from said cold side to said hot side and form a cooling film on a surface of said hot side.

2. A dual wall structure for a combustor as claimed in claim 1, further including a plurality of integral threaded studs including a platform formed adjacent the surface of the cold side of each of the plurality of heat shield panels and configured to provide mechanical support, the plurality of integral threaded studs extending substantially perpendicular from a surface of the cold side of each of the plurality of heat shield panels.

3. A dual wall structure for a combustor as claimed in claim 2, wherein the platform is a substantially star-shaped platform.

4. A dual wall structure for a combustor as claimed in claim 2, wherein each of the plurality of integral threaded studs extends through an opening formed in the outer wall, thereby providing a means for coupling of each of the plurality of heat shield panels to the outer wall.

5. A dual wall structure for a combustor as claimed in claim 1, wherein the aft rail includes a plurality of controlled openings formed therein, the plurality of controlled openings providing fluidic communication between each of the plurality of cavities and the surface of the hot side of each of the heat shield panels.

6. A dual wall structure for a combustor as claimed in claim 1, wherein said forward angled flange of each of said plurality of heat shield panels is sandwiched between the combustor dome and the outer wall, thereby providing at least a portion of a seal for the cavity defined between each of the plurality of heat shield panels and the outer wall.

7. A dual wall structure for a combustor as claimed in claim 1, further including a plurality of vertically aligned dilution holes formed in said outer wall and each of said plurality of heat shield panels.

8. A dual wall structure for a combustor as claimed in claim 7, wherein each of said plurality of vertically aligned dilution holes includes one of a brazed insert, a tack welded insert or a press-fit insert.

9. A dual wall structure for a combustor of a gas turbine engine comprising:

a combustor dome;

an outer liner coupled to said combustor dome; and

an inner liner coupled to said combustor dome and spaced a distance from said outer liner, wherein each of said outer liner and said inner liner comprise;

an outer wall including a plurality of impingement holes formed therein for allowing a coolant to flow therethrough; and

an inner wall coupled to said outer wall and the combustor dome, said inner wall comprising a plurality of heat shield panels, each having a hot side and a cold side,

each of the plurality of heat shield panels further comprises a plurality of side rails and an aft rail extending substantially perpendicular from a surface of the cold side and a forward angled flange, the plurality of side rails, the aft rail and the forward angled flange defining a cavity between the inner wall and the outer wall when coupled together, a plurality of cavities formed by the plurality of heat shield panels;

each of said plurality of heat shield panels further comprising a plurality of integral threaded studs extending substantially perpendicular from the surface of the cold side and through a plurality of holes defined in the outer wall, the plurality of integral threaded studs providing a means for coupling each of the plurality of heat shield panels to the outer wall;

wherein each of said plurality of heat shield panels extends a longitudinal length of said combustor; and

wherein each of said plurality of heat shield panels includes a plurality of effusion holes for allowing said coolant to flow from said cold side to said hot side and form a cooling film on a surface of said hot side.

10. A dual wall structure for a combustor as claimed in claim 9, wherein each of the plurality of integral threaded studs includes a platform adjacent the surface of the cold side of each of the plurality of heat shield panels and configured to provide mechanical support.

11. A dual wall structure for a combustor as claimed in claim 10, wherein platform is a star-shaped platform.

12. A dual wall structure for a combustor as claimed in claim 9, wherein the aft rail includes a plurality of controlled openings formed therein, the plurality of controlled openings providing fluidic communication between each of the plurality of cavities and the surface of the hot side of each of the plurality of heat shield panels.

13. A dual wall structure for a combustor as claimed in claim 9, wherein said forward flange of each of said plurality of heat shield panels is sandwiched between the combustor dome and the outer wall, thereby providing at least a portion of a seal for the cavity defined between each of the plurality of heat shield panels and the outer wall.

14. A dual wall structure for a combustor as claimed in claim 9, further including a plurality of vertically aligned dilution holes formed in said outer wall and each of said plurality of heat shield panels.

15. A dual wall structure for a combustor as claimed in claim 14, wherein each of said plurality of vertically aligned dilution holes includes one of a brazed insert, a tack welded insert or a press-fit insert.

16. A combustor for a gas turbine engine comprising:

a combustor dome;

an outer liner and an inner liner coupled to the combustor dome, wherein said inner liner and said outer liner define a combustion chamber there between;

an outer wall comprising a portion of each of said outer liner and said inner liner;

a plurality of heat shield panels comprising a portion of each said outer liner and said inner liner, each of the plurality of heat shield panels extending substantially a longitudinal length of said combustion chamber;

each of said plurality of heat shield panels having a hot side and a cold side, said cold side having a plurality of side rails, an aft rail and a forward angled flange that when coupled to the outer wall of each of the outer liner and the inner liner define a cavity between each of the plurality of heat shield panels and the outer wall, a plurality of cavities formed by the plurality of heat shield panels;

wherein each of said plurality of heat shield panels includes a plurality of effusion holes for allowing a coolant to flow from said cold side to said hot side and form a cooling film on a surface of said hot side.

17. A combustor for a gas turbine engine as claimed in claim 16, further including a plurality of integral threaded studs extending substantially perpendicular from the surface of the cold side of each of the plurality of heat shield panels.

18. A combustor for a gas turbine engine as claimed in claim 17, wherein each of the plurality of integral threaded studs extends through an opening formed in the outer wall of each of the inner liner and the outer liner, thereby providing coupling of each of the plurality of heat shield panels to the outer wall.

19. A combustor for a gas turbine engine as claimed in claim 16, wherein the aft rail includes a plurality of controlled openings formed therein, the plurality of controlled openings providing fluidic communication between each of the plurality of cavities and the surface of the hot side of each of the plurality of heat shield panels.

20. A combustor for a gas turbine engine as claimed in claim 16, wherein said forward angled flange of each of said plurality of heat shield panels is sandwiched between the combustor dome and the outer wall, thereby providing at least a portion of a seal for the cavity defined between each of the plurality of heat shield panels and the outer wall.