Turbine engine combustor wall with non-uniform distribution of effusion apertures

Patent metadata

Field	Value
Publication number	US-9052111-B2
Application number	US-201213531132-A
Country	US
Kind code	B2
Filing date	Jun 22, 2012
Priority date	Jun 22, 2012
Publication date	Jun 9, 2015
Grant date	Jun 9, 2015

Abstract

A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench apertures fluidly coupled with the shell quench apertures, first effusion apertures fluidly coupled with the first impingement apertures, and second effusion apertures fluidly coupled with the second impingement apertures. The shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield. A density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region.

First claim

What is claimed is:

1. A combustor wall for a turbine engine with an axial centerline, comprising:
a combustor support shell including a plurality of shell quench apertures, a plurality of first impingement apertures, and a plurality of second impingement apertures; and
a combustor heat shield including a plurality of shield quench apertures fluidly coupled with the shell quench apertures, a plurality of first effusion apertures fluidly coupled with the first impingement apertures, and a plurality of second effusion apertures fluidly coupled with the second impingement apertures;
wherein the shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield;
wherein a density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region;
wherein at least one of the first axial region or the second axial region includes a plurality of circumferential first sub-regions and a plurality of circumferential second sub-regions;
wherein a density of the effusion apertures in each first sub-region is greater than a density of the effusion apertures in each second sub-region; and
wherein the density of the effusion apertures in the respective axial region is equal to an average or mean of the densities of the effusion apertures in the first sub-regions and the densities of the effusion apertures in the second sub-regions.

2. The combustor wall of claim 1 , wherein the combustor wall is included in an axial flow combustor that further includes a second combustor wall and an annular combustor bulkhead extending radially between an upstream end of the combustor wall and an upstream end of the second combustor wall.

3. The combustor wall of claim 2 , wherein the combustor wall is disposed radially within the second combustor wall.

4. The combustor wall of claim 2 , wherein the second combustor wall is disposed radially within the combustor wall.

5. The combustor wall of claim 2 , wherein the support shell further includes a plurality of third impingement apertures;
the heat shield further includes a plurality of third effusion apertures fluidly coupled with the third impingement apertures;
the third effusion apertures are configured in a third axial region of the heat shield located axially between the first axial region and an upstream end of the heat shield; and
a density of the third effusion apertures in the third axial region is less than the density of the first effusion apertures in the first axial region.

6. The combustor wall of claim 2 , wherein the support shell further includes a plurality of third impingement apertures;
the heat shield further includes a plurality of third effusion apertures fluidly coupled with the third impingement apertures;
axes of more than seventy five percent of the third effusion apertures extend circumferentially through the heat shield and are substantially perpendicular to the axial centerline; and
the third effusion apertures are configured in a third axial region of the heat shield located axially between the first axial region and anthe upstream end of the heat shield.

7. The combustor wall of claim 1 , wherein each of the first sub-regions is configured for circumferential alignment with a respective fuel injector assembly of the combustor.

8. The combustor wall of claim 1 , wherein the heat shield is disposed radially within the support shell.

9. The combustor wall of claim 1 , wherein the heat shield includes at least one of a plurality of circumferential heat shield panels and a plurality of axial heat shield panels.

10. The combustor wall of claim 1 , wherein a plurality of the impingement apertures and a plurality of the effusion apertures have substantially equal diameters.

11. The combustor wall of claim 1 , wherein diameters of a plurality of the effusion apertures are greater than diameters of a plurality of the impingement apertures.

12. The combustor wall of claim 1 , wherein
axes of a plurality of the effusion apertures are offset from a combustion chamber surface of the heat shield by between about fifteen and about thirty degrees; and
axes of a plurality of the impingement apertures are substantially perpendicular to an impingement cavity surface of the support shell.

13. The combustor wall of claim 1 , wherein an impingement cavity extends radially between the support shell and the heat shield, and fluidly couples at least some of the impingement apertures with at least some of the effusion apertures;
the support shell has an annular cross-sectional geometry and extends axially between an upstream end of the support shell and a downstream end of the support shell; and
the heat shield has an annular cross-sectional geometry and extends axially between an upstream end of the heat shield and the downstream end of the heat shield.

14. The combustor wall of claim 1 , wherein a plurality of the first effusion apertures located adjacent to a first of the panel quench apertures have axes that are substantially tangent to a downstream side of the first panel quench aperture.

Assignees

• Erbas-Sen Nurhak
• Hoke James B
• Cheung Albert K
• Sonntag Robert M
• Snyder Timothy S
• United Technologies Corp

Inventors

• Erbas-Sen Nurhak
• Hoke James B
• Cheung Albert K
• Sonntag Robert M
• Snyder Timothy S

Classifications

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F05B2260/202

  by film cooling · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title