# US 10,502,065 B2 · Gas turbine engine component with rib support

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- Number: US 10,502,065 B2
- Document ID: US10502065B2
- Status: Granted
- Kind: B2
- Application number: 14/896,730
- Filed: 2014-06-06
- Published: 2016-05-12
- Granted: 2019-12-10
- Earliest claimed: 2013-06-17
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: San Quach; Tracy A. Propheter-Hinckley; Matthew A. Devore
- Web page: https://patentgrep.com/patent/US10502065B2

## CPC

- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- B22C 9/103: {Multipart cores}
- F01D 5/187: {Convection cooling}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- 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 29/324: {Blades}
- F05D 2220/32: in gas turbines
- F05D 2230/211: by precision casting, e.g. microfusing or investment casting
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2240/125: related to the tip of a stator vane
- F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D 2240/307: related to the tip of a rotor blade
- F05D 2240/35: Combustors or associated equipment
- F05D 2260/202: by film cooling
- 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)
- B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B)
- 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

## Abstract

A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending from a base to a tip. A plenum is defined inside the airfoil. A first cooling cavity merges into the plenum and a second cooling cavity merges into the plenum. A rib extends from at least one of the first sidewall and the second sidewall at least partially into the plenum to separate the first cooling cavity from the second cooling cavity.

## Claims

### Claim 1

A component, comprising:
an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending radially from a base to a tip;
a plenum defined inside said airfoil, and said plenum is positioned in said tip;
a first cooling cavity merging into said plenum;
a second cooling cavity merging into said plenum; and
a rib that extends from said first sidewall at least partially into said plenum to separate said first cooling cavity from said second cooling cavity, wherein said rib extends radially between opposing sides of said plenum such that said first cooling cavity and said second cooling cavity extend along said first sidewall on opposed sides of said rib, said rib extends transversely between said opposing sides, one of said opposite sides defining a floor and another one of said opposing sides bounded by a wall of said tip, a portion of said rib extends from said first sidewall and terminates prior to said second sidewall, and said first and second cooling cavities have respective first and second outlets into said plenum, said first and second outlets both defined along said floor such that said first and second outlets are spaced apart by said rib.

### Claim 2 (depends on 1)

The component as recited in claim 1, wherein said component is a blade.

### Claim 3 (depends on 1)

The component as recited in claim 1, wherein said component is a vane.

### Claim 4 (depends on 1)

The component as recited in claim 1, wherein said rib extends across said plenum.

### Claim 5 (depends on 1)

The component as recited in claim 1, wherein said rib defines a surface that constricts a flow of cooling fluid that exits at least one of said first cooling cavity and said second cooling cavity into said plenum.

### Claim 6 (depends on 5)

The component as recited in claim 5, wherein said first and second cooling cavities extend radially inward from said rib towards said base.

### Claim 7 (depends on 1)

The component as recited in claim 1, comprising a third cooling cavity that merges into said plenum.

### Claim 8 (depends on 7)

The component as recited in claim 7, wherein said third cooling cavity exits adjacent to another rib.

### Claim 9 (depends on 1)

The component as recited in claim 1, wherein said rib includes a radially extending face that is offset from at least one of said first and second outlets.

### Claim 10 (depends on 1)

The component as recited in claim 1, wherein said rib includes a radially extending face that is offset from said first outlet and said second outlet, and said radially extending face opposes one of said first and second sidewalls.

### Claim 11 (depends on 10)

The component as recited in claim 10, wherein said radially extending face slopes away from said floor.

### Claim 12

A gas turbine engine, comprising:
a component disposed in at least one of a compressor section and a turbine section, wherein said component includes a body that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending radially from a base to a tip, said component having an internal cooling scheme comprising:
a cooling cavity that merges into a plenum;
a rib that extends from said first sidewall into said plenum to control expansion of a cooling fluid from said cooling cavity into said plenum, wherein said rib extends radially between opposing sides of said plenum such that said cooling cavity extends along said first sidewall, one of said opposing sides defining a floor and another one of said opposing sides bounded by a wall of said tip, said rib extends transversely between said opposing sides, a portion of said rib extends from said first sidewall and terminates prior to said second sidewall, and said cooling cavity has an outlet into said plenum, said outlet defined along said floor.

### Claim 13 (depends on 12)

The gas turbine engine as recited in claim 12, wherein said cooling cavity includes a first cooling cavity and a second cooling cavity each merging into said plenum, said first and second cooling cavities separated by said rib, and wherein said outlet includes and outlet of said first cooling cavity and an outlet of said second cooling cavity.

### Claim 14 (depends on 13)

The gas turbine engine as recited in claim 13, wherein said outlet of said first cooling cavity and said outlet of said second cooling cavity are spaced apart from said rib.

### Claim 15

A core assembly for fabricating a component, comprising:
a first core that defines a first cooling cavity of a component;
a second core that defines a second cooling cavity of said component;
a partial rib that extends from said first core and said second core and defines a plenum of said component; and
at least one cut-out in said partial rib that defines a rib in said component, wherein said partial rib extends radially between opposing sides of said plenum such that said first cooling cavity and said second cooling cavity extend along a first sidewall of said component on opposed sides of said partial rib, said partial rib extends transversely between said opposing sides, a portion of said partial rib extends from said first sidewall of said component and terminates prior to a second sidewall of said component, said first core and said second core arranged such that said first and second cooling cavities have respective first and second outlets into said plenum, and said first and second outlets both defined along a common one of said opposing sides such that said first and second outlets are spaced apart by said partial rib.

### Claim 16 (depends on 15)

The core assembly as recited in claim 15, wherein said component is a completed component.

### Claim 17 (depends on 15)

The core assembly as recited in claim 15, comprising a third core that defines a third cooling cavity of said component.

### Claim 18 (depends on 17)

The core assembly as recited in claim 17, wherein said partial rib extends from said third core.

### Claim 19 (depends on 15)

The core assembly as recited in claim 15, wherein said at least one cut-out includes a plurality of cut-outs disposed on opposing faces of said partial rib.