Dilution holes with ridge feature for gas turbine engines

Patent metadata

Field	Value
Publication number	US-11137140-B2
Application number	US-201715725019-A
Country	US
Kind code	B2
Filing date	Oct 4, 2017
Priority date	Oct 4, 2017
Publication date	Oct 5, 2021
Grant date	Oct 5, 2021

Abstract

A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow.

First claim

What is claimed is:

1. A grommet having at least one of an annular geometry or an elliptical geometry defining a dilution hole, comprising:
a ridge formed about an inner diameter of the grommet,
wherein the ridge projects radially inward of an inner diameter wall of the grommet and defines a step,
wherein the step is defined by a step geometry and a ridge face geometry, wherein the ridge face geometry comprises at least one of a sharp geometry, a radial geometry, or a multi-radial geometry,
wherein the ridge comprises a passage,
wherein the step comprises a trench feature extending circumferentially about the dilution hole and axially into the ridge parallel to an axis of the dilution hole, and
wherein an outlet of the passage opens through a base of the trench feature.

2. The grommet of claim 1 , wherein the passage comprises an outlet and the ridge comprises a first fillet about the inner diameter of the grommet at an intersection between the step and the inner diameter wall.

3. The grommet of claim 2 , wherein the outlet opens through one of the step or the first fillet.

4. The grommet of claim 3 , wherein the outlet is configured to direct a cooling flow circumferentially along the first fillet and fill a volume of space, defined by a radially inward projection of the ridge and below a plane defined by a hot side of the grommet, with the cooling flow.

5. The grommet of claim 3 , wherein the outlet is configured to direct a cooling flow radially inward of the first fillet and the ridge toward the dilution hole.

6. The grommet of claim 2 , wherein the grommet further comprises a bell-mouth comprising a second fillet, wherein an inlet of the passage opens through one of the bell-mouth or the second fillet.

7. The grommet of claim 1 , wherein the passage circumferentially spirals through a solid portion of the ridge.

8. A combustor liner comprising:
an array of cooling holes defined by the combustor liner; and
a grommet having at least one of an annular geometry or an elliptical geometry and formed integrally with the combustor liner and defining a dilution hole, wherein the grommet comprises:
a ridge formed about an inner diameter of the grommet,
wherein the ridge projects radially inward of an inner diameter wall of the grommet and defines a step,
wherein the step is defined by a step geometry and a ridge face geometry, wherein the ridge face geometry comprises at least one of a sharp geometry, a radial geometry, or a multi-radial geometry,
wherein the ridge comprises a passage,
wherein the step comprises a trench feature extending circumferentially about the dilution hole and axially into the ridge parallel to an axis of the dilution hole, and
wherein an outlet of the passage opens through a base of the trench feature.

9. The combustor liner of claim 8 , wherein the passage comprises an outlet and the ridge comprises a first fillet about the inner diameter of the grommet at an intersection between the step and the inner diameter wall.

10. The combustor liner of claim 9 , wherein the outlet is configured to direct a cooling flow circumferentially along the first fillet and fill a volume of space, defined by a radially inward projection of the ridge and below a plane defined by a hot side of the grommet, with the cooling flow.

11. A gas turbine engine comprising:
a compressor section configured to compress a gas;
a combustor section aft of the compressor section and configured to combust the gas, wherein the combustor section comprises a combustor liner having a grommet formed integrally with the combustor liner, having at least one of an annular geometry or an elliptical geometry and defining a dilution hole, wherein the grommet comprises:
a ridge formed about an inner diameter of the grommet,
wherein the ridge projects radially inward of an inner diameter wall of the grommet and defines a step,
wherein the step is defined by a step geometry and a ridge face geometry, wherein the ridge face geometry comprises at least one of a sharp geometry, a radial geometry, or a multi-radial geometry,
wherein the ridge comprises a passage,
wherein the step comprises a trench feature extending circumferentially about the dilution hole and axially into the ridge parallel to an axis of the dilution hole, and
wherein an outlet of the passage opens through a base of the trench feature; and the gas turbine engine further comprises:
a turbine section aft of the combustor section and configured to extract energy from the gas.

12. The gas turbine engine of claim 11 , wherein the passage comprises an outlet and the ridge comprises a first fillet about the inner diameter of the grommet at an intersection between the step and the inner diameter wall.

13. The gas turbine engine of claim 12 , wherein the outlet is configured to direct a cooling flow circumferentially along the first fillet and fill a volume of space, defined by a radially inward projection of the ridge and below a plane defined by a hot side of the grommet, with the cooling flow.

14. The gas turbine engine of claim 11 , wherein the grommet further comprises a bell-mouth comprising a second fillet, wherein an inlet of the passage opens through one of the bell-mouth or the second fillet.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Mongillo Jr Dominic
• Whitfield Christopher
• Phropheter-Hinckley Tracy

Classifications

• F23R3/02

  characterised by the air-flow or gas-flow configuration (reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58) · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title