Gas turbine engine variable porosity combustor liner

Patent metadata

Field	Value
Publication number	US-9719684-B2
Application number	US-201314136705-A
Country	US
Kind code	B2
Filing date	Dec 20, 2013
Priority date	Mar 15, 2013
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

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 alloy 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.

First claim

The invention claimed is:

1. 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; and
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;
wherein at least one of 1) the plurality of hot side holes or 2) the plurality of cold side holes include holes of a first diameter and of a second diameter that is different from the first diameter; and
wherein the first arrangement that defines the first porous region has the hot side holes of the first diameter, and the second arrangement that defines the second porous region has the hot side holes of the second diameter that is different than the first diameter.

2. The gas turbine engine combustor liner of claim 1 in which the hot side holes and the cold side holes are circular.

3. The gas turbine engine combustor liner of claim 1 in which the hot side holes and the cold side holes are distributed in an array fashion.

4. The gas turbine engine combustor liner of claim 1 in which 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.

5. The gas turbine engine combustor liner of claim 1 in which the pedestals are distributed in an array fashion.

6. The gas turbine engine combustor liner of claim 1 in which the pedestals are distributed in alternating relation with respect to the cold side holes in the axial and circumferential directions.

7. 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;
wherein first and second arrangements of a plurality of the hot side holes, the cold side holes, and the fluid flow passages define respective first and second porous regions in the combustor liner having respective first and second porosities;
wherein at least one of 1) the hot side holes or 2) the cold side holes include holes of a first diameter and of a second diameter that is different from the first diameter; and
wherein the first arrangement that defines the first porous region has the hot side holes of the first diameter, and the second arrangement that defines the second porous region has the hot side holes of the second diameter that is different than the first diameter.

8. The method of claim 7 in which the electrochemically etching comprises electrochemically etching pedestals into the cold side metal alloy sheet wall that provide boundaries to the cooling flow passages, the pedestals being axially offset relative to the hot side holes.

9. 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;

wherein at least one of 1) the plurality of hot side holes or 2) the plurality of cold side holes include holes of a first diameter and of a second diameter that is different from the first diameter; and
the first arrangement that defines the first porous region has the cold side holes of the first diameter, and the second arrangement that defines the second porous region has the cold side holes of the second diameter that is different than the first diameter.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp
• Rolls-Royce North America Tech Inc

Inventors

• Pinnick Donald E
• Froemming Kenneth W
• Varney Bruce E

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title