# US 11,306,919 B2 · Combustor panel cooling hole arrangement

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- Number: US 11,306,919 B2
- Document ID: US11306919B2
- Status: Granted
- Kind: B2
- Application number: 16/224,012
- Filed: 2018-12-18
- Published: 2020-04-23
- Granted: 2022-04-19
- Earliest claimed: 2018-10-19
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Scott D. Lewis
- Web page: https://patentgrep.com/patent/US11306919B2

## CPC

- F23R 3/06: Arrangement of apertures along the flame tube
- F23R 3/50: Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52)
- F05D 2240/35: Combustors or associated equipment
- F05D 2260/202: by film cooling
- F23R 2900/03041: Effusion cooled combustion chamber walls or domes
- F23R 2900/03042: Film cooled combustion chamber walls or domes
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A cooling hole arrangement for a combustor panel including a first group of cooling holes, each of the first cooling holes extending from a first inlet to a first outlet. Also included is a second group of cooling holes, each of the second cooling holes extending from a second inlet to a second outlet, each of the first cooling holes and the second cooling holes spaced from an edge of the combustor panel in an axial direction to be arranged substantially parallel to the edge of the combustor panel. At least a portion of the first inlet of each first cooling holes is axially overlapped with a portion of the second inlet of the second cooling holes. The first outlet of each of the first cooling holes is closer to the edge of the combustor panel than the second outlet of the second cooling holes is to the edge.

## Claims

### Claim 1

A cooling hole arrangement for a combustor panel comprising:
a plurality of cooling holes that are located closest to an edge of the combustor panel, relative to every other cooling holes of the combustor panel, the plurality of cooling holes comprising:
a first group of cooling holes located in a first row, each of the first group of cooling holes extending from a first inlet to a first outlet; and
a second group of cooling holes located in a second row adjacent to the first row, each of the second group of cooling holes extending from a second inlet to a second outlet, each of the first group of cooling holes and the second group of cooling holes spaced from the edge of the combustor panel in an axial direction to be arranged parallel to the edge of the combustor panel, wherein the first row is located closer to the edge of the combustor panel than the second row,
wherein at least a portion of the first inlet of each first group of cooling holes axially overlapped with a portion of the second inlet of the second group of cooling holes,
the first outlet of each of the first group of cooling holes being closer to the edge of the combustor panel than the second outlet of the second group of cooling holes is to the edge.

### Claim 2 (depends on 1)

The cooling hole arrangement of claim 1, wherein each of the first group of cooling holes extend from the first inlet to the first outlet at a first angular orientation, each of the second group of cooling holes extending from the second inlet to the second outlet at a second angular orientation, the first angular orientation ranging from about 10 degrees to about 50 degrees relative to a circumferential direction.

### Claim 3 (depends on 1)

The cooling hole arrangement of claim 1, wherein each of the first group of cooling holes extend from the first inlet to the first outlet at a first angular orientation, each of the second group of cooling holes extending from the second inlet to the second outlet at a second angular orientation, the second angular orientation ranging from about −15 degrees to about 15 degrees relative to a circumferential direction.

### Claim 4 (depends on 1)

The cooling hole arrangement of claim 1, wherein a distance between the second outlet and the edge is about 3 times to about 4 times greater than the distance between the first outlet and the edge.

### Claim 5 (depends on 1)

The cooling hole arrangement of claim 1, wherein a distance between the second outlet and the edge is about 3.4 times greater than the distance between the first outlet and the edge.

### Claim 6 (depends on 1)

The cooling hole arrangement of claim 1, wherein each of the first group of cooling holes extend from the first inlet to the first outlet at a first angular orientation, the first angular orientation not parallel to an oncoming gas flow path direction.

### Claim 7

A cooling hole arrangement for a combustor panel comprising: a plurality of cooling holes that are located closest to a leading edge of the combustor panel, relative to every other cooling holes of the combustor panel, the plurality of cooling holes comprising: a first group of cooling holes located in a first row, the first group of cooling holes having a first angular orientation; and a second group of cooling holes located in a second row adjacent to the first row, the second group of cooling holes having a second angular orientation, wherein the first angular orientation different than the second angular orientation, each of the first group of cooling holes and the second group of cooling holes spaced from the leading edge of the combustor panel in an axial direction to be arranged parallel to the leading edge of the combustor panel, wherein the first row is located closer to the edge of the combustor panel than the second row, wherein each of the first group of cooling holes extends from a first inlet to a first outlet, each of the second group of cooling holes extending from a second inlet to a second outlet, at least a portion of the first inlet of each first group of cooling holes axially overlapped with a portion of the second inlet of the second group of cooling holes.

### Claim 8 (depends on 7)

The cooling hole arrangement of claim 7, wherein the first outlet of each of the first group of cooling holes is closer to a leading edge of the combustor panel than the second outlet of the second group of cooling holes is to the leading edge.

### Claim 9 (depends on 7)

The cooling hole arrangement of claim 7, wherein the first angular orientation ranges from about 10 degrees to about 50 degrees relative to a circumferential direction.

### Claim 10 (depends on 7)

The cooling hole arrangement of claim 7, wherein the second angular orientation ranging from about −15 degrees to about 15 degrees relative to a circumferential direction.

### Claim 11 (depends on 8)

The cooling hole arrangement of claim 8, wherein a distance between the second outlet and the leading edge is about 3 times to about 4 times greater than the distance between the first outlet and the leading edge.

### Claim 12 (depends on 7)

The cooling hole arrangement of claim 7, wherein the first angular orientation is not parallel to an oncoming gas flow path direction.

### Claim 13

A gas turbine engine comprising:
a compressor section;
a combustor section;
a turbine section; and
a cooling hole arrangement for a combustor panel of the combustor section, the combustor panel extending axially from a leading edge to a trailing edge, the cooling hole arrangement comprising:
a plurality of cooling holes that are located closest to the leading edge of the combustor panel, relative to every other cooling holes of the combustor panel, the plurality of cooling holes comprising:
a first group of cooling holes located in a first row, the first group of cooling holes having a first angular orientation; and
a second group of cooling holes located in a second row adjacent to the first row, the second group of cooling holes having a second angular orientation, the first angular orientation different than the second angular orientation, each of the first group of cooling holes and the second group of cooling holes spaced from the leading edge of the combustor panel in an axial direction to be arranged parallel to the leading edge of the combustor panel,
wherein the first row is located closer to the edge of the combustor panel than the second row.

### Claim 14 (depends on 13)

The gas turbine engine of claim 13, wherein each of the first group of cooling holes extends from a first inlet to a first outlet, each of the second group of cooling holes extending from a second inlet to a second outlet, at least a portion of the first inlet of each first group of cooling holes axially overlapped with a portion of the second inlet of the second group of cooling holes, the first outlet of each of the first group of cooling holes being closer to a leading edge of the combustor panel than the second outlet of the second group of cooling holes is to the leading edge.

### Claim 15 (depends on 13)

The gas turbine engine of claim 13, wherein the first angular orientation ranges from about 10 degrees to about 50 degrees relative to the circumferential direction.