# US 2014/0190654 A1 · Cast features for a turbine engine airfoil

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- Number: US 2014/0190654 A1
- Document ID: US20140190654A1
- Status: Published application
- Kind: A1
- Application number: 14/155,545
- Filed: 2014-01-15
- Published: 2014-07-10
- Earliest claimed: 2007-03-14
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Jason Edward Albert; Atul Kohli; Eric L. Couch
- Web page: https://patentgrep.com/patent/US20140190654A1

## CPC

- B22C 9/24: for hollow articles
- B22C 9/04: Use of lost patterns
- B22C 9/108: {Installation of cores}
- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F01D 25/12: Cooling
- F05D 2230/21: by casting
- F05D 2260/202: by film cooling
- Y10T 29/49341: with cooling passage
- Y10T 29/49826: Assembling or joining
- B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B)
- 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
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A core assembly for a turbine engine blade includes a generally radially extending trunk interconnected to multiple generally axially extending tabs. The tabs are interconnected by a generally radially extending ligament. Multiple generally axially extending protrusions are interconnected to the ligament opposite the trunk. A mold is configured to define an exterior surface of an airfoil. The core is arranged within the mold and is configured such that the tabs and the ligament break through at the exterior surface.

## Claims

### Claim 1

A core assembly for a turbine engine blade comprising:
a generally radially extending trunk interconnected to multiple generally axially extending tabs, the tabs interconnected by a generally radially extending ligament, and multiple generally axially extending protrusions interconnected to the ligament opposite the trunk; and
a mold configured to define an exterior surface of an airfoil, the core arranged within the mold and configured such that the tabs and the ligament break through at the exterior surface.

### Claim 2 (depends on 1)

The core assembly according to claim 1, wherein the tabs extend in an axial direction, and the trunk extends in a radial direction, the axial direction is at a non-perpendicular angle relative to the radial direction.

### Claim 3 (depends on 2)

The core assembly according to claim 2, wherein the angle is approximately between 10-45 degrees.

### Claim 4 (depends on 1)

The core assembly according to claim 1, comprising a refractory metal material providing the trunk, tabs and ligament.