# US 2014/0193246 A1 · Cooling hole with crenellation features

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- Number: US 2014/0193246 A1
- Document ID: US20140193246A1
- Status: Published application
- Kind: A1
- Application number: 14/204,465
- Filed: 2014-03-11
- Published: 2014-07-10
- Earliest claimed: 2012-02-15
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Glenn Levasseur; Edward F. Pietraszkiewicz
- Web page: https://patentgrep.com/patent/US20140193246A1

## CPC

- F01D 25/14: Casings modified therefor (double casings F01D25/26)
- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F05D 2240/81: Cooled platforms
- F05D 2250/182: crenellated, notched
- F05D 2250/183: zigzag
- F05D 2250/324: divergent
- F05D 2260/202: by film cooling
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F23R 2900/03042: Film cooled combustion chamber walls or domes
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- Y10T 29/49229: Prime mover or fluid pump making
- Y10T 29/49323: Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- 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)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.

## Claims

### Claim 1

A wall of a component of a gas turbine engine, the wall comprising:
first and second wall surfaces;
an inlet located at the first wall surface;
an outlet located at the second surface;
a metering section commencing at the inlet and extending downstream from the inlet;
a diffusing section extending from the metering section and terminating at the outlet, wherein the diffusing section comprises:
a leading edge formed at an upstream end of the outlet;
a trailing edge formed at a downstream end of the outlet;
a body region upstream of the trailing edge; and
a plurality of crenellation features located on the body region.

### Claim 2 (depends on 1)

The wall of claim 1, wherein each crenellation feature includes a crenellation body that projects generally towards the leading edge.

### Claim 3 (depends on 1)

The wall of claim 1, wherein the trailing edge has a profile that is generally straight.

### Claim 4 (depends on 1)

The wall of claim 1, wherein the trailing edge has a profile that is generally curved.

### Claim 5 (depends on 1)

The wall of claim 1, wherein the crenellation features comprise V-shaped projections.

### Claim 6 (depends on 1)

The wall of claim 1, wherein the crenellation features comprise rounded projections.

### Claim 7 (depends on 1)

The wall of claim 1, wherein the crenellation features comprise grooves.

### Claim 8 (depends on 1)

The wall of claim 1, wherein the diffusing section further comprises:
a first lobe diverging longitudinally and laterally from the metering section; and
a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.

### Claim 9

A method for producing a cooling hole having a plurality of crenellation features in a wall having first and second surfaces, the method comprising:
forming an inlet at the first surface, wherein the inlet meters a flow of fluid through the cooling hole;
forming a diffusing section between the inlet and an outlet at the second surface, wherein the diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end the outlet generally opposite the upstream end, and a body region located upstream of the trailing edge; and
forming a plurality of crenellation features on the body region of the diffusing section.

### Claim 10 (depends on 9)

The method of claim 9, wherein each crenellation feature includes a crenellation body that projects generally towards the leading edge.

### Claim 11 (depends on 9)

The method of claim 9, wherein the crenellation features are formed by removing material from the diffusing section.