Combustor liner with improved film cooling

Patent metadata

Field	Value
Publication number	US-9243801-B2
Application number	US-201213490797-A
Country	US
Kind code	B2
Filing date	Jun 7, 2012
Priority date	Jun 7, 2012
Publication date	Jan 26, 2016
Grant date	Jan 26, 2016

Abstract

A heat shield for a combustor liner includes first linear film cooling slots through the heat shield and second linear film cooling slots through the heat shield. The first linear film cooling slots are run in a row and each of the first linear film cooling slots is angled from the row in a first direction. The second linear film cooling slots also run in the row and each of the second linear film cooling slots is angled from the row in a second direction opposite the first direction. The second linear film cooling slots alternate with the first linear film cooling slots in the row. The first and second linear film cooling slots are connected to form a single, multi-cornered film cooling slot.

First claim

The invention claimed is:

1. A heat shield for a combustor liner, the heat shield comprising:
a plurality of first linear film cooling slots through the heat shield, the plurality of first linear film cooling slots running in a row; each of the first linear film cooling slots angled from the row in a first direction; and
a plurality of second linear film cooling slots through the heat shield, the plurality of second linear film cooling slots running in the row; each second linear film cooling slot angled from the row in a second direction opposite the first direction; the second linear film cooling slots alternating with the 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.

2. The heat shield of claim 1 , wherein the plurality of first linear film cooling slots are angled at about 45 degrees in the first direction from the row; and the second linear film cooling slots are angled at about minus 45 degrees in the second direction from the row.

3. The heat shield of claim 1 , further comprising:
a plurality of rows of multi-cornered film cooling slots, the rows running parallel to each other.

4. The heat shield of claim 1 , wherein the heat shield is arcuate in shape defining an axis and a circumferential direction; the row of the multi-cornered film cooling slot runs in the circumferential direction; and the first direction and the second direction are in a first axial direction and second axial direction, respectively.

5. The heat shield of claim 4 , further comprising:
a first row of dilution openings in the heat shield, the first row of dilution openings running in the circumferential direction; and
a second row of dilution openings in the heat shield, 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.

6. The heat shield of claim 5 , wherein the dilution openings are substantially rectangular.

7. A combustor liner for a gas turbine engine, the combustor liner comprising:
a shell including:
a shell cold side; and
a shell hot side; and

a heat shield attached to the shell, the heat shield including:
a shield cold side facing the shell hot side;
a shield hot side facing away from the shell hot side; and
a multi-cornered film cooling slot including:
a plurality of first linear film cooling slots through the heat shield, the plurality of first linear film cooling slots running in a row; each of the first linear film cooling slots angled from the row in a first direction; and
a plurality of second linear film cooling slots through the heat shield, the plurality of second linear film cooling slots running in the row; each second linear film cooling slot angled from the row in a second direction opposite the first direction; the second linear film cooling slots alternating with the first linear film cooling slots in the row; the first and second linear film cooling slots connected to form a single film cooling slot.

8. The combustor liner of claim 7 , wherein the plurality of first linear film cooling slots are angled at about 45 degrees in the first direction from the row; and the second linear film cooling slots are angled at about minus 45 degrees in the second direction from the row.

9. The combustor liner of claim 7 , wherein the heat shield further includes:
a plurality of rows of multi-cornered film cooling slots, the rows running parallel to each other.

10. The combustor liner of claim 7 , wherein the combustor liner is arcuate in shape defining an axis and a circumferential direction, wherein the row of the multi-cornered film cooling slot runs in the circumferential direction; and the first direction and the second direction are in a first axial direction and second axial direction, respectively.

11. The combustor liner of claim 10 , further comprising:
a first row of dilution openings in the heat shield, the first row of dilution openings running in the circumferential direction; and
a second row of dilution openings in the heat shield, 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.

12. The combustor liner of claim 11 , wherein the dilution openings are substantially rectangular.

13. The combustor liner of claim 11 , further comprising:
a row of cooling holes through 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.

14. The combustor liner of claim 13 , further comprising:
a plurality of series of trip strips and a plurality of projecting walls creating a plurality of convergent channels;
the shell further including a plurality of rows of cooling holes; and
the heat shield further including a plurality of rows of multi-cornered film cooling slots, the rows of multi-cornered film cooling slots running parallel to each other; the rows of cooling holes, the convergent channels, and the multi-cornered film cooling slots alternating across the combustor liner.

15. A method of cooling a combustor liner of a gas turbine engine comprises:
providing cooling air to the combustor liner;
flowing the cooling air to an interior of the combustor liner through a row of cooling holes in the combustor liner;
flowing the cooling air from the row of cooling holes to a multi-cornered film cooling slot leading from the interior of the combustor liner to an exterior of the combustor liner;
passing the cooling air through the multi-cornered film cooling slot;
flowing the cooling air out of the multi-cornered film cooling slot;
forming a cooling film on the exterior of 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 openings in the combustor liner to create a second row of dilution jets at the exterior of the combustor liner in a staggered, overlapping relationship with the first row of dilution jets;
producing staggered, overlapping dilution jets at the exterior of the combustor liner; and
creating an even dilution air flow pressure distribution from the staggered, overlapping dilution air jets to promote cooling by eliminating hot spots on a portion of the exterior of the combustor liner.

16. The method of claim 15 , wherein flowing the cooling air from the row of cooling holes to a multi-cornered film cooling slot includes:
increasing the velocity of the cooling air within the combustor liner by flowing it thro

Assignees

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

Inventors

• Cunha Frank J
• Erbas-Sen Nurhak

Classifications

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F23R2900/03043

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

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03045

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

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title