Multi-material turbine components

Patent metadata

Field	Value
Publication number	US-9266170-B2
Application number	US-201213360126-A
Country	US
Kind code	B2
Filing date	Jan 27, 2012
Priority date	Jan 27, 2012
Publication date	Feb 23, 2016
Grant date	Feb 23, 2016

Abstract

A turbine component for a turbine of an engine is provided. The turbine component includes a blade portion of a first material; and an attachment portion coupled to the blade portion, the attachment portion being a second material.

First claim

What is claimed is:

1. A method for manufacturing an engine component, comprising the steps of:
providing a blade portion of an intermediate component article, the blade portion comprising a first material;
subjecting the blade portion of the intermediate component article to a heat treatment unsuitable for the second material
forming, after the subjecting step, an attachment portion of the intermediate component article on the blade portion of the intermediate component article with an additive manufacturing technique, the attachment portion comprising a second material; and
finishing the intermediate component article to form the engine component.

2. The method of claim 1 , wherein the forming step includes direct metal laser fusing sequential layers of build material into the attachment portion.

3. The method of claim 1 , wherein forming step includes forming the attachment portion with direct metal laser fusion.

4. The method of claim 1 , wherein providing step includes providing the blade portion such that the first material is a single crystal material.

5. The method of claim 1 , wherein the forming step includes forming the attachment portion such that the second material is a powder metal nickel base superalloy.

6. The method of claim 1 , wherein the providing step includes direct metal laser fusing sequential layers of build material into the blade portion, and wherein the subjecting step includes subjecting the blade portion to a hot isostatic pressing (HIP) process prior to the forming of the attachment portion.

7. A method for manufacturing an engine component, comprising the steps of:
providing a blade portion of an intermediate component article, the blade portion comprising a first material;
forming an attachment portion of the intermediate component article on the blade portion of the intermediate component article with an additive manufacturing technique, the attachment portion comprising a second material;
forming a tip portion of the intermediate component article on the blade portion of the intermediate component article, the tip portion comprising a third material; and
finishing the intermediate component article to form the engine component.

8. The method of claim 7 , wherein the step of forming the tip portion includes forming the tip portion such that the third material is at least one of HON4A or a high temperature nickel base superalloy that is predominately gamma prime hardened.

9. The method of claim 7 , wherein the first, second, and third materials are different materials.

10. A method for manufacturing an engine component, comprising the steps of:
providing a first portion of an intermediate component article, the first portion comprising a first material;
forming a second portion of the intermediate component article on the first portion of the intermediate component article with an additive manufacturing technique, the second portion comprising a second material; and
forming a third portion of the intermediate component article on the first portion of the intermediate component article, the third portion comprising a third material,
wherein the engine component is a turbine component, and wherein the providing step includes providing a blade portion as the first portion, the forming the second portion includes providing a tip portion as the second portion, and the forming the third portion includes providing an attachment portion as the third portion;
subjecting first and second portions of the intermediate component article to a heat treatment prior to the step of forming the third portion of the intermediate component article; and
finishing the intermediate component article to form the engine component.

Assignees

• Godfrey Donald G
• Morris Mark C
• Menon Mamballykalathil
• Honeywell Int Inc

Inventors

• Godfrey Donald G
• Morris Mark C
• Menon Mamballykalathil

Classifications

• C30B29/52

  Alloys · CPC title

• B22F5/04

  of turbine blades · CPC title

• Y10T29/49336

  Blade making · CPC title

• C30B11/00

  Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method (C30B13/00, C30B15/00, C30B17/00, C30B19/00 take precedence; under a protective fluid C30B27/00) · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title