GAS TURBINE ENGINE COMBUSTOR LINER

• US 20150013340A1
• Filed: 12/27/2013
• Published: 01/15/2015
• Est. Priority Date: 03/15/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Pinnick, Donald E., Froemming, Kenneth W., Varney, Bruce E., Loebig, James C., Taylor, Todd
• Granted Patent: US 9,879,861 B2
• Time in Patent Office: Days
• US Class Current: 60/754
• CPC Class Codes: F23R 2900/00018 Manufacturing combustion chamber liners or subparts
• 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 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 3/10 for primary air F23R3/06, F23R3/045 take precedence
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Claims

1. A gas turbine engine variable porosity combustor liner comprising

a laminated alloy structure having combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side, the combustion chamber facing holes being in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure;

wherein porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

2. The gas turbine engine variable porosity combustor liner of claim 1, wherein the combustion chamber facing holes are arranged in a first array and the cooling plenum facing holes are arranged in a second array that is offset from the first array in the axial and circumferential directions.

3. The gas turbine engine variable porosity combustor liner of claim 1, wherein the different cooling flow amounts in the respective porous zones are based on the combustion chamber facing holes having different diameters in the respective different porous zones.

4. The gas turbine engine variable porosity combustor liner of claim 1, wherein the different cooling flow amounts in the respective porous zones are based on the cooling plenum facing holes having different diameters in the respective different porous zones.

5. The gas turbine engine variable porosity combustor liner of claim 1, wherein the different cooling flow amounts in the respective porous zones are based on the combustion chamber facing holes having different through hole angles in the respective different porous zones.

6. The gas turbine engine variable porosity combustor liner of claim 1, wherein the different cooling flow amounts in the respective porous zones are based on the cooling plenum facing holes having different through hole angles in the respective different porous zones.

7. The gas turbine engine variable porosity combustor liner of claim 1, wherein the combustor liner has an annular shape and the porous zones are arranged in an alternating manner circumferentially about the axis of the annular liner.

8. A gas turbine engine combustor liner comprising

a hot side wall and a cold side wall configured for installation in a gas turbine engine to separate a combustion chamber from a cooling air source, the hot side wall and the cold side wall each comprising metal alloy sheet material;

the hot side wall having a plurality of hot side holes projecting through its thickness for fluid communication with the combustion chamber;

the cold side wall having a plurality of cold side holes projecting through its thickness for fluid communication with the cooling air source and including a plurality of pedestals that connect to the hot side wall such that a plurality of fluid flow passages are defined between the hot side wall and cold side wall and between the pedestals;

the cold side holes being in fluid communication with the hot side holes via the fluid flow passages so as to create a cooling flow path from the cooling air source to the combustion chamber;

first and second arrangements of a plurality of the hot side holes, the cold side holes, and the fluid flow passages defining respective first and second porous regions in the combustor liner having respective first and second porosities, the first porosity being greater than the second porosity.

9. The gas turbine engine combustor liner of claim 8, wherein the first arrangement that defines the first porosity region has hot side holes of a first diameter, and the second arrangement that defines the second porosity region has hot side holes of a second diameter that is different than the first diameter.

10. The gas turbine engine combustor liner of claim 8, wherein the first arrangement that defines the first porosity region has cold side holes of a first diameter, and the second arrangement that defines the second porosity region has cold side holes of a second diameter that is different than the first diameter.

11. The gas turbine engine combustor liner of claim 8, wherein the first arrangement that defines the first porosity region has hot side holes and cold side holes of a first diameter, and the second arrangement that defines the second porosity region has hot side holes and cold side holes of a second diameter that is different than the first diameter.

12. The gas turbine engine combustor liner of claim 8, wherein the hot side holes and the cold side holes are circular.

13. The gas turbine engine combustor liner of claim 8, wherein the hot side holes and the cold side holes are the same size.

14. The gas turbine engine combustor liner of claim 8, wherein the hot side holes and the cold side holes are distributed in an array fashion.

15. The gas turbine engine combustor liner of claim 8, wherein the hot side holes and the cold side holes extend through the respective hot side wall and cold side wall radially in a linear manner.

16. The gas turbine engine combustor liner of claim 8, wherein the hot side holes and the cold side holes extend through the respective hot side wall and cold side wall radially at an angle.

17. The gas turbine engine combustor liner of claim 8, wherein the pedestals are distributed in an array fashion.

18. The gas turbine engine combustor liner of claim 8, wherein the pedestals are distributed in alternating relation with respect to the cold side holes in the axial and circumferential directions.

19. A method of forming a variable porosity laminated alloy combustor liner comprising

providing a hot side metal alloy sheet wall and a cold side metal alloy sheet wall;

laser drilling a configuration of hot side holes and cold side holes into the respective hot side and cold side metal alloy sheet walls;

electrochemically etching a configuration of cooling flow passages into the cold side metal alloy sheet wall so that when the hot side and cold side metal alloy sheet walls are bonded together, the cooling flow passage is disposed between the walls and fluidly connects the cold side holes with one or more of the hot side holes; and

diffusion bonding together the hot side and cold side metal alloy sheet walls to form the laminated alloy combustor liner;

wherein the configurations of the hot side holes, the cold side holes, and the cooling flow passages in the walls together define multiple different porous regions in the laminated alloy combustor liner that provide respective cooling flow amounts through the walls at the respective porous regions.

20. The method of claim 19, wherein the configuration of hot side holes and cold side holes includes different diameter holes in the respective different porous regions.