# US 10,480,331 B2 · Airfoil having panel with geometrically segmented coating

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- Number: US 10,480,331 B2
- Document ID: US10480331B2
- Status: Granted
- Kind: B2
- Application number: 15/354,260
- Filed: 2016-11-17
- Published: 2018-05-17
- Granted: 2019-11-19
- Earliest claimed: 2016-11-17
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Eric A. Hudson; Raymond Surace
- Web page: https://patentgrep.com/patent/US10480331B2

## CPC

- F01D 5/284: {Selection of ceramic materials}
- F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)}
- F01D 5/187: {Convection cooling}
- F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall}
- F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/288: {Protective coatings for blades}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 25/005: {Selecting particular materials}
- F01D 25/12: Cooling
- F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16)
- F04D 29/023: {especially adapted for elastic fluid pumps}
- F04D 29/388: {characterised by construction}
- F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)}
- F05D 2220/32: in gas turbines
- F05D 2230/90: Coating; Surface treatment
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2240/35: Combustors or associated equipment
- F05D 2250/283: honeycomb
- F05D 2260/202: by film cooling
- F05D 2300/6033: Ceramic matrix composites [CMC]
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- 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)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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 airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a distinct panel that forms a portion of the airfoil profile. The panel has a geometrically segmented coating section. The geometrically segmented coating section includes a wall that has an outer side. The outer side includes an array of cells, and there is a coating disposed in the array of cells.

## Claims

### Claim 1

An airfoil comprising:
an airfoil section defining an airfoil profile, the airfoil section including a core skeleton, a distinct panel attached with the core skeleton and forming a portion of the airfoil profile, the distinct panel having a geometrically segmented coating section, the geometrically segmented coating section including
a wall having an outer side, the outer side including an array of cells, and
a coating disposed in the array of cells.

### Claim 2 (depends on 1)

The airfoil as cited in claim 1, wherein the panel is integral with the core skeleton.

### Claim 3 (depends on 1)

The airfoil as recited in claim 1, wherein the core skeleton is metal.

### Claim 4 (depends on 1)

The airfoil as recited in claim 1, further comprising compliment panel attached with the core skeleton and defining a different portion of the airfoil profile.

### Claim 5 (depends on 4)

The airfoil as recited in claim 4, wherein the compliment panel includes a non-segmented coating section.

### Claim 6 (depends on 4)

The airfoil as recited in claim 4, wherein the distinct panel and the compliment panel define a cooling hole there between.

### Claim 7 (depends on 4)

The airfoil as recited in claim 4, wherein the compliment panel is ceramic.

### Claim 8 (depends on 7)

The airfoil as recited in claim 7, wherein the ceramic is selected from the group consisting of a monolithic ceramic and a ceramic matrix composite.

### Claim 9 (depends on 1)

The airfoil as recited in claim 1, further comprising spacers that offset the panel from the core skeleton such that there is a passage between the panel and the core skeleton.

### Claim 10 (depends on 9)

The airfoil as recited in claim 9, wherein the spacers are projections on the core skeleton.

### Claim 11 (depends on 1)

The airfoil as recited in claim 1, wherein the core skeleton includes an internal passage and a plurality of cooling holes with inlets that open to the internal passage and outlets adjacent the distinct panel.

### Claim 12 (depends on 11)

The airfoil as recited in claim 11, wherein the core skeleton includes a baffle in the internal passage.

### Claim 13 (depends on 1)

The airfoil as recited in claim 1, wherein the core skeleton includes an exterior wall portion that forms a portion of the airfoil profile.

### Claim 14 (depends on 13)

The airfoil as recited in claim 13, wherein the core skeleton includes a recess in which the distinct panel is disposed such that the distinct panel is flush with the exterior wall portion.

### Claim 15

A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
at least one of the turbine section or the compressor section including an airfoil having an airfoil section defining an airfoil profile, the airfoil section including a core skeleton, a distinct panel attached with the core skeleton and forming a portion of the airfoil profile, the distinct panel having a geometrically segmented coating section, the geometrically segmented coating section including
a wall having an outer side, the outer side including an array of cells, and
a coating disposed in the array of cells.

### Claim 16 (depends on 15)

The gas turbine engine as recited in claim 15, further comprising a compliment panel attached with the core skeleton and defining a different portion of the airfoil profile, wherein the compliment panel includes a non-segmented coating section.

### Claim 17

An article comprising:
a distinct panel having a geometrically segmented coating section, the geometrically segmented coating section including
a wall having an array of cells, wherein the array of cells are geometric cells that are closed-sided, and
a coating disposed in the array of cells.

### Claim 18 (depends on 17)

The article as recited in claim 17, wherein the distinct panel defines a portion of an airfoil profile, the wall is metal, and the coating is ceramic.

### Claim 19 (depends on 1)

The airfoil as recited in claim 1, wherein the cells are geometric cells.

### Claim 20 (depends on 19)

The airfoil as recited in claim 19, wherein the geometric cells are closed-sided cells.

### Claim 21 (depends on 20)

The airfoil as recited in claim 20, wherein the closed-sided cells are polygonal cells.