# US 10,370,980 B2 · Lost core structural frame

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- Number: US 10,370,980 B2
- Document ID: US10370980B2
- Status: Granted
- Kind: B2
- Application number: 15/039,918
- Filed: 2014-11-20
- Published: 2017-01-26
- Granted: 2019-08-06
- Earliest claimed: 2013-12-23
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Steven Taffet; Brandon S. Donnell; Daniel C. Nadeau; Russell Deibel; San Quach
- Web page: https://patentgrep.com/patent/US10370980B2

## CPC

- F01D 5/187: {Convection cooling}
- B22C 7/02: Lost patterns
- B22C 9/04: Use of lost patterns
- B22C 9/10: Cores; Manufacture or installation of cores {(breaker cores B22C9/084)}
- B22C 9/24: for hollow articles
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 25/12: Cooling
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2230/21: by casting
- F05D 2230/211: by precision casting, e.g. microfusing or investment casting
- F05D 2240/121: related to the leading edge of a stator vane
- F05D 2240/122: related to the trailing edge of a stator vane
- F05D 2240/303: related to the leading edge of a rotor blade
- F05D 2240/304: related to the trailing edge of a rotor blade
- F05D 2260/202: by film cooling
- 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)
- B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B)
- 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 lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

## Claims

### Claim 1

A lost core mold component comprising:
a first leg and a second leg, with a plurality of crossover members connecting said first and second legs, with said plurality of crossover members including outermost crossover members spaced from each other and adjacent ends of each of said first and second legs, second crossover members spaced closer to each other than are said outermost crossover members, and central crossover members extending between said first and second leg and between said second crossover members; and
said outermost crossover members extending for a first cross-sectional area, said second crossover members extending for a second cross-sectional area and said central crossover members extending for a third cross-sectional area, with said first cross-sectional area being greater than said second cross-sectional area and said second cross-sectional area being greater than said third cross-sectional area.

### Claim 2 (depends on 1)

The lost core mold component as set forth in claim 1, wherein a ratio of said first cross-sectional area to said second cross-sectional area to said third cross-sectional area is 3:2:1.

### Claim 3 (depends on 2)

The lost core mold component as set forth in claim 2, wherein said lost core member is further provided with pins to form film cooling holes.

### Claim 4 (depends on 3)

The lost core mold component as set forth in claim 3, wherein said lost core member is utilized to form two cooling channels adjacent at least one of a leading and trailing edge in an airfoil which is to be molded around said lost core member.

### Claim 5 (depends on 4)

The lost core mold component as set forth in claim 4, wherein said lost core member is utilized to form two cooling channels adjacent the leading edge.

### Claim 6 (depends on 1)

The lost core mold component as set forth in claim 1, wherein there are intermediate hollows between said outermost crossover members and said second crossover members, and between said second members and said central crossover members, and between individual ones of said central crossover members.

### Claim 7 (depends on 6)

The lost core mold component as set forth in claim 6, wherein said hollows extend for a cross-sectional area that is less than said first and said second cross-sectional area.

### Claim 8 (depends on 1)

The lost core mold component as set forth in claim 1, wherein said lost core member is further provided with pins to form film cooling holes.

### Claim 9 (depends on 1)

The lost core mold component as set forth in claim 1, wherein said lost core member is utilized to form two cooling channels adjacent at least one of a leading and trailing edge in an airfoil which is to be molded around said lost core member.