Core assemblies and gas turbine engine components formed therefrom

Patent metadata

Field	Value
Publication number	US-10323569-B2
Application number	US-201615283837-A
Country	US
Kind code	B2
Filing date	Oct 3, 2016
Priority date	May 20, 2016
Publication date	Jun 18, 2019
Grant date	Jun 18, 2019

Abstract

Core assemblies and methods for manufacturing components of gas turbine engines include a first core body having a first trunk configured to attach to a first location of a cavity core structure, a first branch extending from the first trunk and configured to form a first portion of a first cooling circuit, the first branch having a first joining surface, and a second core body having a second trunk configured to attach to a second location of a cavity core structure, a first branch of the second core body extending from the second trunk and configured to form a first portion of a second cooling circuit in the component. The first branches of the core bodies joined to form a junction. The junction defines a merger of the first cooling circuit and the second cooling circuit proximate to an exit of the first and second cooling circuits.

First claim

What is claimed is:

1. A core assembly for manufacturing a component of a gas turbine engine, the core assembly comprising:
a first core body having a first trunk configured to attach to a first location of a cavity core structure, a first branch of the first core body extending from the first trunk and configured to form a first portion of a first cooling circuit in the component, the first branch having a first joining surface; and
a second core body having a second trunk configured to attach to a second location of a cavity core structure, a first branch of the second core body extending from the second trunk and configured to form a first portion of a second cooling circuit in the component, the first branch of the second core body having a second joining surface joined to the first joining surface to form a junction,
wherein the junction defines a merger of the first cooling circuit and the second cooling circuit proximate to an exit of the first and second cooling circuits from the component,
wherein the first location is on a first internal cavity core structure and the second location is on second internal cavity core structure that is different from the first internal cavity core structure.

2. The core assembly of claim 1 , wherein the first core body includes a second branch extending from the first trunk to define a second exit of the first cooling circuit.

3. The core assembly of claim 2 , wherein the second exit is formed in one of a pressure side surface or a suction side surface of the component.

4. The core assembly of claim 2 , wherein the second core body includes a second branch extending from the second trunk to define a second exit of the second cooling circuit.

5. The core assembly of claim 4 , wherein the second exit of the first cooling circuit and the second exit of the second cooling circuit are on opposite side surfaces of the component.

6. The core assembly of claim 1 , wherein at least one of the first core body and the second core body is a refractory metal core.

7. The core assembly of claim 1 , wherein the first core body and the second core body are attached at the junction by at least one of welding, gluing, forging, pressing, laser operations, or mechanical attachment.

8. The core assembly of claim 1 , wherein at least one of the first core body and the second core body includes a plurality of openings configured to form a plurality of air disturbance features in the component.

9. The core assembly of claim 1 , wherein the first location and the second location are different from each other.

10. A component for a gas turbine engine comprising:
a cavity formed inside the component and defining a cooling flow path within the component;
a first cooling circuit fluidly connecting the cavity to an exterior of the component, wherein the first cooling circuit comprises a first portion and a second portion wherein the first portion of the cooling circuit and the second portion of the cooling circuit are configured to define a first exit and a second exit at two different locations on the exterior of the component, and wherein the first portion and the second portion extend from a trunk portion of the first cooling circuit; and
a second cooling circuit formed within the component and merging with the first cooling circuit proximate the first exit of the first cooling circuit,
wherein the second cooling circuit is fluidly connected to a second cavity different from the cavity the first cooling circuit is fluidly connected to.

11. The component of claim 10 , wherein at least one of the trunk portion, the first portion of the cooling circuit, or the second portion of the cooling circuit includes a plurality of air disturbance features in the cooling circuit.

12. The component of claim 10 , wherein the first exit is on an end of the component and the second exit of the first cooling circuit is on a pressure side surface or suction side surface of the component.

13. The component of claim 10 , wherein the second cooling circuit has a second exit separate from the location of the merging with the first cooling circuit.

14. A method of forming a core for a component of a gas turbine engine, the method comprising:
forming a core assembly having a first core body with a trunk that attaches to a cavity core structure, a first branch extending from the trunk and configured to form a first portion of a first cooling circuit in the component, and a second branch extending from the trunk and configured to form a second portion of the first cooling circuit in the component, the first branch of the first core body having a first joining surface;
attaching a second core body to the first core body at the first joining surface to form a junction, the second core body configured to define a second cooling circuit within the component; and
attaching the first core body to a cavity core structure,
wherein the junction of the first core body and the second core body define a merging of the first and second cooling circuits proximate an end of the component; and
attaching the second core body to a different cavity core structure than the cavity core structure the first core body is attached to.

15. The method of claim 14 , further comprising forming a component having an interior cavity based on the cavity core structure and cooling circuits defined by the first and second core bodies.

Assignees

• United Technologies Corp

Inventors

• King Christopher

Classifications

• F05B2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F05D2260/202

  by film cooling · CPC title

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B22C9/103 Primary

  Multipart cores · CPC title

• F05D2230/20

  essentially without removing material · CPC title