# US 10,309,255 B2 · Blade outer air seal cooling passage

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- Number: US 10,309,255 B2
- Document ID: US10309255B2
- Status: Granted
- Kind: B2
- Application number: 15/104,092
- Filed: 2014-12-10
- Published: 2016-11-03
- Granted: 2019-06-04
- Earliest claimed: 2013-12-19
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Dmitriy A. Romanov
- Web page: https://patentgrep.com/patent/US10309255B2

## CPC

- F01D 25/12: Cooling
- F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20)
- F01D 11/24: by selectively cooling-heating stator or rotor components
- F05D 2220/32: in gas turbines
- F05D 2240/11: Shroud seal segments
- F05D 2240/127: Vortex generators, turbulators, or the like, for mixing
- F05D 2260/201: by impingement of a fluid
- F05D 2260/2212: by creating turbulence
- F05D 2260/22141: using fins or ribs
- 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

## Abstract

A gas turbine engine component includes a structure including a first wall and a second wall that provide a cooling passage. The cooling passage extends a length from a first end to a second end. A cluster of impingement inlet holes is provided in the second wall at the first end. An outlet is provided at the second end.

## Claims

### Claim 1

A gas turbine engine component comprising:
a structure including a first wall and a second wall that provide a cooling passage, the cooling passage extends a length from a first end to a second end, a cluster of impingement inlet holes is provided in the second wall at the first end, and an outlet is provided at the second end wherein a first region is provided within the cooling passage beneath the cluster of impingement inlet holes, and a second region includes turbulators, the first region extends in the range of 25-65% of the length and has lower fluid friction than the second region, and the first region is without the turbulators, wherein the structure includes multiple parallel discrete cooling passages each having the outlet and the cluster of impingement inlet holes arranged on opposite sides of the structure.

### Claim 2 (depends on 1)

The gas turbine engine component according to claim 1, wherein the structure is a blade outer air seal.

### Claim 3 (depends on 2)

The gas turbine engine component according to claim 2, wherein the cooling passage extends in a circumferential direction and is provided between lateral walls, the outlet provided in one of the lateral walls.

### Claim 4 (depends on 3)

The gas turbine engine component according to claim 3, wherein the structure includes multiple parallel cooling passages.

### Claim 5 (depends on 2)

The gas turbine engine component according to claim 2, wherein the first wall includes a sealing surface, and the second wall provides an outer wall configured to be in fluid communication with a cooling source.

### Claim 6 (depends on 1)

The gas turbine engine component according to claim 1, wherein at least one of the first and second walls includes turbulators arranged downstream from the cluster of impingement inlet holes.

### Claim 7 (depends on 6)

The gas turbine engine component according to claim 6, wherein the turbulators are chevrons.

### Claim 8 (depends on 1)

The gas turbine engine component according to claim 1, wherein the second region has a Darcy friction factor that is higher than a Darcy friction factor of the first region.

### Claim 9 (depends on 8)

The gas turbine engine component according to claim 8, wherein the first region has a Darcy friction factor of around 1.0, and the second region has a Darcy friction factor of around 8.4.