# US 10,767,492 B2 · Turbine engine airfoil

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- Number: US 10,767,492 B2
- Document ID: US10767492B2
- Status: Granted
- Kind: B2
- Application number: 16/223,808
- Filed: 2018-12-18
- Published: 2020-06-18
- Granted: 2020-09-08
- Earliest claimed: 2018-12-18
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Zachary Daniel Webster; Steven Robert Brassfield; Gregory Terrence Garay; Tingfan Pang; Daniel Endecott Osgood
- Web page: https://patentgrep.com/patent/US10767492B2

## CPC

- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F05D 2240/301: Cross-sectional characteristics
- F05D 2240/304: related to the trailing edge of a rotor blade
- F05D 2240/81: Cooled platforms
- F05D 2250/20: Three-dimensional
- F05D 2260/202: by film cooling
- F05D 2260/204: by the use of microcircuits
- F05D 2260/2212: by creating turbulence
- 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)
- 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 component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.

## Claims

### Claim 1

An airfoil for a turbine engine, comprising:
an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction;
a first passage extending along one of the leading edge, the trailing edge, or the tip;
a second passage extending along another of the leading edge, the trailing edge, or the tip;
a first cooling air supply conduit comprising a first three-dimensional plexus of fluidly interconnected cooling passages fluidly coupled to one of the first passage or the second passage; and
a second cooling air supply conduit comprising a non-furcated passage fluidly coupled to the other of the first passage or the second passage.

### Claim 2 (depends on 1)

The airfoil of claim 1 further comprising at least one of: leading edge outlets located in the exterior surface along the leading edge and fluidly coupled to the first passage defining a leading edge passage, trailing edge outlets located in the exterior surface along the trailing edge and fluidly coupled to the second passage defining a trailing edge passage, or tip outlets located in the exterior surface along the tip and fluidly coupled to a third passage defining a tip passage.

### Claim 3 (depends on 2)

The airfoil of claim 2 further comprising a third cooling air supply conduit comprising a second three-dimensional plexus of fluidly interconnected cooling passages.

### Claim 4 (depends on 3)

The airfoil of claim 3 wherein the first cooling air supply conduit with first three-dimensional plexus is fluidly coupled to the trailing edge passage.

### Claim 5 (depends on 4)

The airfoil of claim 4 wherein the second cooling air supply conduit with non-furcated passage is fluidly coupled to the leading edge passage.

### Claim 6 (depends on 5)

The airfoil of claim 5 wherein the third cooling air supply conduit with second three-dimensional plexus is fluidly coupled to the tip passage.

### Claim 7 (depends on 4)

The airfoil of claim 4 wherein the first cooling air supply conduit further comprises a non-furcated passage fluidly coupled to the first three-dimensional plexus.

### Claim 8 (depends on 7)

The airfoil of claim 7 wherein the non-furcated passage is upstream of the first three-dimensional plexus.

### Claim 9 (depends on 8)

The airfoil of claim 8 wherein the first three-dimensional plexus is fluidly coupled to the trailing edge outlets.

### Claim 10 (depends on 3)

The airfoil of claim 3 wherein the third cooling air supply conduit further comprises a third three-dimensional plexus of fluidly interconnected cooling passages.

### Claim 11 (depends on 2)

The airfoil of claim 2 further comprising a third cooling air supply conduit fluidly coupled to at least one of the leading edge passage, tip passage, or trailing edge passage.

### Claim 12 (depends on 1)

The airfoil of claim 1 further comprising a second three-dimensional plexus and a third three-dimensional plexus located adjacent one another in a cross-wise direction defined between the pressure side and the suction side.

### Claim 13 (depends on 1)

The airfoil of claim 1 further comprising a surface channel in the exterior surface of the outer wall and fluidly coupled to tip outlets located along the tip of the airfoil.

### Claim 14

An airfoil for a turbine engine, comprising:
an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction;
outlets on the exterior surface; and
a first cooling air supply conduit having a first supply passage and a first three-dimensional plexus of fluidly interconnected cooling passages which are fluidly connected to the outlets, wherein the first supply passage is at least partially radially aligned with the first three-dimensional plexus.

### Claim 15 (depends on 14)

The airfoil of claim 14 wherein the outlets are adjacent one of the leading edge, trailing edge, or tip.

### Claim 16 (depends on 14)

The airfoil of claim 14 wherein the outlets are on at least one of the pressure side or suction side.

### Claim 17 (depends on 14)

The airfoil of claim 14 further comprising a channel in the exterior surface and at least some of the outlets are located in the channel.

### Claim 18 (depends on 17)

The airfoil of claim 17 wherein the channel is located adjacent the tip.

### Claim 19 (depends on 14)

The airfoil of claim 14 further comprising a second plexus of fluidly interconnected cooling passage fluidly coupled to the first plexus.

### Claim 20 (depends on 19)

The airfoil of claim 19 wherein the second plexus is upstream of the first plexus.

### Claim 21 (depends on 14)

The airfoil of claim 14 further comprising an in-wall cooling passage extending through the interior of the outer wall and fluidly coupled to the first plexus.

### Claim 22 (depends on 21)

The airfoil of claim 21 wherein the in-wall cooling passage fluidly couples the first plexus to the outlets.

### Claim 23 (depends on 22)

The airfoil of claim 22 wherein the in-wall cooling passage comprises a non-furcated passage.

### Claim 24

A cooled component, comprising:
an outer wall defining an exterior surface bounding an interior;
outlets on the exterior surface; and
a three-dimensional plexus of fluidly interconnected cooling passages located within the interior and fluidly coupled to the outlets, the three-dimensional plexus having at least one planar set of cooling passages.

### Claim 25 (depends on 24)

The cooled component of claim 24 further comprising an airfoil assembly in a turbine engine, wherein the outer wall further comprises an airfoil outer wall.

### Claim 26 (depends on 25)

The cooled component of claim 25 wherein the airfoil assembly further comprises a platform coupled to the airfoil outer wall, and wherein the outlets are located on the platform.