DUAL-WALL IMPINGEMENT, CONVECTION, EFFUSION (DICE) COMBUSTOR TILE

• US 20140250894A1
• Filed: 12/20/2013
• Published: 09/11/2014
• Est. Priority Date: 03/05/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Heffernan, Tab M., Graves, Charles B., Petty, Jack D. Sr., Razdan, Mohan, Bell, Michael S., Smallwood, Michel S.
• Granted Patent: US 10,451,276 B2
• Time in Patent Office: Days
• US Class Current: 60/754
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2230/22 by sintering
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• 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 2900/03043 Convection cooled combustion chamber walls with means for guiding the cooling air flow
• 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 3/007 constructed mainly of ceramic components
• 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 gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor. Cooling is more efficient in part due to the dual wall construction and in part due to reduced parasitic leakage, and the design is less sensitive to attachment features which operate at lower temperatures.

Claims

1. A gas turbine engine having a combustor comprising:

a liner having an inner surface;

a plurality of tile assemblies secured to the inner surface of the liner, each tile assembly having a cooling plenum; and

at least one securing member for securing each tile assembly to the liner.

2. The gas turbine as claimed in claim 1, wherein the cooling plenum feeding the tile assembly includes a first wall and a rail, the rail engages a surface of the liner to form a space for cooling air to flow.

3. The gas turbine as claimed in claim 1, wherein the tile assembly includes a first wall and a second wall that are separated by at least one pedestal member.

4. The gas turbine as claimed in claim 1, wherein the tile assembly includes individual members that are formed of a ceramic composite material.

5. The gas turbine as claimed in claim 1, wherein the tile assembly includes a single member formed of a ceramic composite material.

6. The gas turbine as claimed in claim 1, wherein the tile assembly includes individual members that are formed of a metallic material.

7. The gas turbine as claimed in claim 1, wherein the tile assembly includes a first substantially planar or curved member, a second substantially planar or curved member, a spacer for offsetting said members, and apertures passing through each member for providing a cooling flow path.

8. The gas turbine as claimed in claim 7, wherein the securing member is connected to one of the planar or curved members.

9. The gas turbine as claimed in claim 1, wherein each tile assembly includes a plurality of securing members.

10. The gas turbine as claimed in claim 1, wherein each tile assembly is constructed of one or more ceramic matrix members.

11. The gas turbine as claimed in claim 1, wherein each tile assembly includes a first and second wall, each said wall includes a small dilution port and/or a large dilution port.

12. The gas turbine as claimed in claim 1, wherein the inner case has a tile mounting surface, the tile mounting surface includes cooling ports that permit air flow to the tile assembly.

14. The tile for a gas turbine engine as claimed in claim 12, further comprising a mounting stud that is secured at one end to one of the wall elements, the mounting stud is secured at another end to a wall of a combustor liner.

15. The tile for a gas turbine engine as claimed in claim 12, wherein the first wall element includes a plurality of air channels that are separated by pedestals.

16. The tile for a gas turbine engine as claimed in claim 12, wherein the first wall element includes a rail that extends along an outer perimeter of the wall element.

17. The tile for a gas turbine engine as claimed in claim 12, wherein the second wall element includes cooling holes that extend through the second wall element for delivering air to the first wall element.

18. The tile for a gas turbine engine as claimed in claim 12, further comprising a combustor liner, the first wall element is positioned adjacent to the combustor liner.

20. The combustor for a gas turbine engine as claimed in claim 18, wherein the first layer has an outside surface with cooling holes, and air channels in a section underneath the first surface, the air channels are separated by members that route air underneath the outside surface.

13. A tile for a gas turbine engine combustor comprising:

a first wall element;

a second wall element; and

a cooling plenum disposed between the first and second wall elements.

19. A combustor for a gas turbine engine comprising:

a liner;

a multi-walled tile, the tile having a first layer, a second layer, a stud, a dilution port, an air plenum disposed between the first and second layer; and

a fastening member for securing the tile to the liner.