Combustor liner with reduced cooling dilution openings

Patent metadata

Field	Value
Publication number	US-9335049-B2
Application number	US-201213490809-A
Country	US
Kind code	B2
Filing date	Jun 7, 2012
Priority date	Jun 7, 2012
Publication date	May 10, 2016
Grant date	May 10, 2016

Abstract

A combustor liner is arcuate in shape and defines an axis and a circumferential direction. The combustor liner includes a first row of dilution openings and a second row of dilution openings. The first row runs in the circumferential direction. The second row runs parallel to the first row and is axially spaced from the first row. Each dilution opening of the second row overlaps in an axial direction a portion of each of two adjacent dilution openings of the first row.

First claim

The invention claimed is:

1. A combustor liner for a gas turbine engine, the combustor liner being arcuate in shape and defining an axis and a circumferential direction, the combustor liner comprising:
a first row of dilution openings in the liner, the first row of dilution openings running in the circumferential direction; and
a second row of dilution openings in the liner, the second row of dilution openings running parallel to the first row of dilution openings and axially spaced from the first row of dilution openings; each dilution opening of the second row of dilution openings at least partially overlapping in an axial direction a portion of each of two adjacent dilution openings of the first row of dilution openings; and
wherein the dilution openings are substantially rectangular.

2. The combustor liner of claim 1 further comprising:
a heat shield including:
a shield hot side; and
a shield cold side;

a shell attached to the heat shield, the shell including:
a shell hot side facing the shield cold side;
a shell cold side facing away from the shield cold side; and
a row of cooling holes in the shell;

a series of trip strips projecting from the shield cold side, the trip strips running parallel to each other and all projecting from the shield cold side the same distance; and
a series of projecting walls, each projecting wall running parallel to, and opposite of, a corresponding trip strip and projecting from the shell hot side such that a distance to which each projecting wall projects from the shell hot side is greater for projecting walls farther from the row of cooling holes to create successive gaps between projecting walls and corresponding trip strips that decrease from the row of cooling holes to create a convergent channel.

3. The combustor liner of claim 2 , further comprising:
a jet wall projecting from the shell hot side, the jet wall running parallel to the projecting walls; the jet wall downstream from the convergent channel; the jet wall for creating a wall shear jet of increased velocity cooling flow in a tangential direction along the shield cold side.

4. The combustor liner of claim 3 , further comprising:
a plurality of jet walls projecting from the shell hot side;
a plurality of series of trip strips and a plurality of series of projecting walls creating a plurality of convergent channels; and
the shell further includes a plurality of rows of cooling holes;
the rows of cooling holes, the convergent channels, and the jet walls alternating across the liner.

5. The combustor liner of claim 3 , wherein the heat shield further includes:
a plurality of first linear film cooling slots through the heat shield, the first linear film cooling slots angled in a first axial direction and disposed in a row running in the circumferential direction; and
a plurality of second linear film cooling slots through the heat shield, the second linear film cooling slots angled in a second axial direction opposite to the first axial direction and alternating with first linear film cooling slots in the row; the first and second linear film cooling slots connected to form a single, multi-cornered film cooling slot downstream from the jet wall.

6. The combustor liner of claim 5 , wherein the plurality of first linear film cooling slots are angled at about 45 degrees in the second linear film cooling slots are angled at about minus 45 degrees in the axial direction from the axial direction from the circumferential direction; and the circumferential direction.

7. A gas turbine engine comprising:
a compressor; and
a combustor receiving a flow of cooling air from the compressor, the combustor including:
a combustor liner defining at least a portion of a combustion chamber, the combustor liner being arcuate in shape and defining an axis and a circumferential direction, the combustor liner including:
a first row of dilution openings in the liner, the first row of dilution openings running in the circumferential direction; and
a second row of dilution openings in the liner, the second row of dilution openings running parallel to the first row of dilution openings and axially spaced from the first row of dilution openings; each dilution opening of the second row of dilution openings at least partially overlapping in an axial direction a portion of each of two adjacent dilution openings of the first row of dilution openings; and
wherein the combustor liner dilution openings are substantially rectangular.

8. The engine of claim 7 , wherein the combustor liner further includes:
a heat shield including:
a shield hot side facing the combustion chamber; and
a shield cold side facing away from the combustion chamber;

a shell attached to the heat shield, the shell including:
a shell hot side facing the shield cold side;
a shell cold side facing away from the shield cold side;
a row of cooling holes in the shell;

a series of trip strips projecting from the shield cold side, the trip strips running parallel to each other and all projecting from the shield cold side the same distance; and
a series of projecting walls, each projecting wall running parallel to, and opposite of, a corresponding trip strip and projecting from the shell hot side such that a distance to which each projecting wall projects from the shell hot side is greater for projecting walls farther from the row of cooling holes to create successive gaps between projecting walls and corresponding trip strips that decrease from the row of cooling holes to create a convergent channel.

9. The engine of claim 8 , wherein the combustor liner further comprises:
a jet wall projecting from the shell hot side, the jet wall running parallel to the plurality of projecting walls; the jet wall downstream from the projecting walls; the jet wall for creating a wall shear jet of increased velocity cooling flow in a tangential direction along the shield cold side.

10. The engine of claim 9 , wherein the combustor liner further comprises:
a plurality of jet walls projecting from the shell hot side;
a plurality of series of trip strips and a plurality of series of projecting walls creating a plurality of convergent channels; and
the shell further includes a plurality of rows of cooling holes;
the rows of cooling holes, the convergent channels, and the jet walls alternating across the liner.

11. The engine of claim 9 , wherein the heat shield further comprises:
a plurality of first linear film cooling slots through the heat shield, the first linear film cooling slots angled in a first axial direction and disposed in a row running in the circumferential direction; and
a plurality of second linear film cooling slots through the heat shield, the second linear film cooling slots angled in a second axial direction opposite to the first axial direction and alternating with first linear film cooling slots in the row;
the first and second linear film cooling slots connected to form a single, multi-cornered film cooling slot downstream from the jet wall.

12. The engine of claim 11 , wherein the plurality of first linear film cooling slots are angled at about 45 degrees in the axial direction from the circumferential direction; and the second linear film cooling slots are angled at about minus 45 degrees in the axial direction from the circumferential direction.

13. A method of cooling a combustor liner of a gas turbine engine comprises:
providing cooling air to the combustor liner;
flowing the cooling air through dilution openings in the combustor liner to create a first row of dilution jets at an exterior of the combustor liner;
flowing the cooling air through dilution open

Assignees

• Cunha Frank J
• Erbas-Sen Nurhak
• United Technologies Corp

Inventors

• Cunha Frank J
• Erbas-Sen Nurhak

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R2900/03043

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

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title