# US 10,502,422 B2 · Cooling a quench aperture body of a combustor wall

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- Number: US 10,502,422 B2
- Document ID: US10502422B2
- Status: Granted
- Kind: B2
- Application number: 15/035,356
- Filed: 2014-12-04
- Published: 2016-10-06
- Granted: 2019-12-10
- Earliest claimed: 2013-12-05
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Frank J. Cunha; Stanislav Kostka, Jr.
- Web page: https://patentgrep.com/patent/US10502422B2

## CPC

- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F02C 7/12: Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P)
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F02C 7/24: Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00)
- F02K 1/822: {Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors}
- F23R 3/04: Air inlet arrangements
- F23R 3/06: Arrangement of apertures along the flame tube
- F05D 2220/30: in turbines
- F05D 2240/35: Combustors or associated equipment
- F05D 2260/201: by impingement of a fluid
- F05D 2260/202: by film cooling
- F05D 2260/231: Preventing heat transfer
- F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies
- 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)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- 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

An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.

## Claims

### Claim 1

An assembly for a turbine engine, the assembly comprising:
a combustor wall including a shell, a heat shield and an annular body engaged with the shell and the heat shield;
the annular body extending vertically through the combustor wall and at least partially defining a quench aperture along a centerline through the combustor wall, and a cooling aperture in fluid communication with the quench aperture;
wherein at least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline;
wherein the annular body includes an inner surface and a shelf surface vertically recessed within the combustor wall relative to an exterior surface of the heat shield, the exterior surface of the heat shield configured to form a portion of a peripheral boundary of a combustion chamber of the turbine engine;
wherein the annular body extends vertically to an exterior surface of the annular body and laterally to the inner surface that at least partially defines the quench aperture;
wherein the inner surface and the shelf surface define a peripheral inner channel in the annular body, the shelf surface facing toward the combustion chamber; and
wherein the exterior surface of the annular body is flush with an exterior surface of the shell, the exterior surface of the shell facing away from the combustion chamber.

### Claim 2 (depends on 1)

The assembly of claim 1, wherein the cooling aperture is one of a plurality of cooling apertures that are defined by and extend through the annular body.

### Claim 3 (depends on 1)

The assembly of claim 1, wherein the cooling aperture extends through the annular body between the exterior surface of the annular body and the inner surface.

### Claim 4 (depends on 3)

The assembly of claim 3, wherein a portion of the cooling aperture at the inner surface extends substantially radially relative to the centerline.

### Claim 5 (depends on 3)

The assembly of claim 3, wherein a portion of the cooling aperture at the inner surface extends substantially tangentially relative to the inner surface.

### Claim 6 (depends on 3)

The assembly of claim 3, wherein a portion of the cooling aperture at the inner surface extends acutely relative to the inner surface.

### Claim 7 (depends on 3)

The assembly of claim 3, wherein the annular body defines the cooling aperture with an inlet portion and an outlet portion; the inlet portion extends vertically from the exterior surface of the annular body; and the outlet portion extends laterally to the inner surface.

### Claim 8 (depends on 7)

The assembly of claim 7, wherein the annular body further defines the cooling aperture with an intermediate portion that extends vertically and laterally between the inlet portion and the outlet portion.

### Claim 9 (depends on 7)

The assembly of claim 7, wherein the annular body includes an annular first segment attached to an annular second segment; the first segment at least partially defines the inlet portion and the exterior surface of the annular body; and the second segment at least partially defines the outlet portion and the inner surface.

### Claim 10 (depends on 3)

The assembly of claim 3, wherein the exterior surface of the annular body is funnel-shaped and defines a portion of the quench aperture.

### Claim 11 (depends on 1)

The assembly of claim 1, wherein the annular body defines a peripheral outer channel in which the shell is seated vertically against the annular body.

### Claim 12 (depends on 1)

The assembly of claim 1, wherein the annular body extends vertically through a cooling cavity defined vertically between the shell and the heat shield; and
the cooling cavity fluidly couples one or more cooling apertures defined in the shell with one or more cooling apertures defined in the heat shield.

### Claim 13 (depends on 1)

The assembly of claim 1, wherein the heat shield includes a plurality of panels that are attached to the shell, and the annular body is connected to one of the panels.

### Claim 14

An assembly for a turbine engine, the assembly comprising:
a combustor wall including a shell, a heat shield and an annular body engaged with the shell and the heat shield;
the annular body extending through the combustor wall and at least partially defining a quench aperture and a cooling aperture, and the annular body including an inner surface that at least partially defines the quench aperture and a shelf surface;
the quench aperture extending along a centerline through the combustor wall from an exterior surface of the annular body to an exterior surface of the heat shield facing a combustion chamber in the turbine engine, the exterior surface of the annular body being flush with an exterior surface of the shell, the exterior surface of the shell facing away from the combustion chamber;
the cooling aperture in fluid communication with the quench aperture, and at least a portion of the cooling aperture extending radially outward from the quench aperture relative to the centerline;
the shelf surface vertically recessed within the combustor wall relative to the exterior surface of the heat shield; and
the inner surface and the shelf surface defining a peripheral inner channel in the annular body, the shelf surface facing toward the combustion chamber.

### Claim 15 (depends on 14)

The assembly of claim 14, wherein the exterior surface of the heat shield is configured to partially form a peripheral boundary of the combustion chamber.