GAS TURBINE ENGINE COMBUSTOR LINER PANEL

• US 20160116166A1
• Filed: 04/14/2014
• Published: 04/28/2016
• Est. Priority Date: 06/14/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: DRAKE, Christopher, KOSTKA, Stanislav Jr., CUNHA, Frank J.
• Granted Patent: US 10,352,566 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 2900/03045 Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.

Claims

1. A liner panel for a combustor of a gas turbine engine comprising:

a multiple of heat transfer augmentors, at least one of said multiple of heat transfer augmentors includes a hemi-spherical protuberance.

2. The liner panel as recited in claim 1, wherein said liner panel includes an entrance to at least one passage within a valley formed by a subset of said multiple of heat transfer augmentors.

3. The liner panel as recited in claim 2, wherein said at least one passage is an effusion flow passage.

4. The liner panel as recited in claim 3, wherein said entrance is within a hemi-spherical depression.

5. The liner panel as recited in claim 4, wherein said entrance is centered within said hemi-spherical depression.

6. The liner panel as recited in claim 5, wherein said at least one passage defines an angle through the liner panel.

7. A liner panel for a combustor of a gas turbine engine comprising:

a multiple of heat transfer augmentors, a subset of said multiple of heat transfer augmentors defines a valley with a hemi-spherical depression.

8. The liner panel as recited in claim 7, wherein at least one of said multiple of heat transfer augmentors includes a hemi-spherical protuberance.

9. The liner panel as recited in claim 7, wherein an entrance to an effusion flow passage is located within said hemi-spherical depression.

10. The liner panel as recited in claim 9, wherein said effusion flow passage defines an angle through the liner panel.

11. A combustor of a gas turbine engine comprising:

a shell with a multiple of impingement flow passages; and

a liner panel mounted to said shell, said liner panel includes a multiple of heat transfer augmentors which extend from a cold side thereof toward said shell, at least one of said multiple of heat transfer augmentors includes a hemi-spherical protuberance, a subset of said multiple of heat transfer augmentors defines a valley with a hemi-spherical depression.

12. The combustor as recited in claim 11, further comprising a plurality of studs which extend from a cold side of said liner panel.

13. The combustor as recited in claim 11, wherein at least one of said multiple of impingement flow passages is directed toward said hemi-spherical protuberance.

14. The combustor as recited in claim 11, wherein said effusion flow passage defines an angle through the liner panel.

15. The combustor as recited in claim 11, wherein an entrance to an effusion flow passage is located adjacent to said hemi-spherical depression.

16. The combustor as recited in claim 11, wherein an entrance to an effusion flow passage is located within said hemi-spherical depression.

17. The combustor as recited in claim 11, wherein an entrance to an effusion flow passage is centered within said hemi-spherical depression.