# US 9,518,738 B2 · Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 9,518,738 B2
- Document ID: US9518738B2
- Status: Granted
- Kind: B2
- Application number: 14/180,028
- Filed: 2014-02-13
- Published: 2014-08-28
- Granted: 2016-12-13
- Earliest claimed: 2013-02-26
- Assignees: Rolls-Royce Deutschland Ltd & Co KG
- Applicants: Rolls-Royce Deutschland Ltd & Co KG
- Inventors: Miklos Gerendas
- Web page: https://patentgrep.com/patent/US9518738B2

## CPC

- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F23R 3/06: Arrangement of apertures along the flame tube
- F23R 2900/03041: Effusion cooled combustion chamber walls or domes
- F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies
- F23R 2900/03045: Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
- 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)

## Abstract

The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier.

## Claims

### Claim 1

A gas turbine combustion chamber, comprising:
a combustion chamber wall including a tile carrier,
a plurality of wall tiles mounted on the tile carrier spaced apart from the tile carrier to form an impingement cooling gap between the tile carrier and the plurality of wall tiles,
wherein the tile carrier includes a plurality of impingement cooling holes and each wall tile includes a plurality of effusion holes with inlet openings,
wherein each wall tile includes, on a side facing the tile carrier, a surface structure which includes raised portions rising from a surface of the wall tile and extending in a direction toward the tile carrier;
wherein the inlet openings of the effusion holes are located on the raised portions of the surface structure;
wherein the centric axes of the inlet openings are arranged substantially perpendicular to a surface of the tile carrier;
wherein the centric axes of the inlet openings are arranged substantially parallel to centric axes of the impingement cooling holes;
wherein the raised portions are formed as ribs;
wherein the impingement cooling holes are arranged to direct impingement air jets into a space between the ribs and spaced apart from the inlet openings.

### Claim 2 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the inlet openings of the effusion holes are spaced a distance from the surface of the tile carrier which is 0.5 to 1.5 times a diameter of the inlet openings.

### Claim 3 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, and further comprising a spacer arranged around at least one of the inlet openings that at least partially encloses the at least one of the inlet openings.

### Claim 4 (depends on 3)

The gas turbine combustion chamber in accordance with claim 3, wherein the spacer is shaped to impart a swirl to air flowing into the at least one of the inlet openings.

### Claim 5 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, and further comprising a spacer arranged adjacent to at least one of the inlet openings.

### Claim 6 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the effusion holes are straight.

### Claim 7 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the effusion holes have a constant.

### Claim 8 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the raised portions include polygonal cells, with a prism positioned in each of the polygonal cells.

### Claim 9 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the effusion holes have a widening diameter.

### Claim 10 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the effusion holes are curved.

### Claim 11 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the effusion holes are partially straight.

### Claim 12 (depends on 1)

The gas turbine combustion chamber in accordance with claim 1, wherein the effusion holes are partially curved.