Multiple piece engine component

Patent metadata

Field	Value
Publication number	US-10329918-B2
Application number	US-201415030243-A
Country	US
Kind code	B2
Filing date	Oct 17, 2014
Priority date	Oct 18, 2013
Publication date	Jun 25, 2019
Grant date	Jun 25, 2019

Abstract

One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

First claim

What is claimed is:

1. A method of forming a component of a gas turbine engine, comprising:
forming a first portion of the component using one of a casting and a forging process, the first portion including a root, platform, and at least one radial support projecting from the platform;
additively manufacturing a second portion of the component, the second portion providing a side wall of the component; and
joining the second portion to the first portion;
wherein the step of additively manufacturing the second portion includes directly additively building the second portion onto the first portion, wherein the at least one radial support of the first portion is used as a base for the additive build occurring during the step of additively manufacturing the second portion such that the step of joining the second portion to the first portion occurs concurrent with the step of additively manufacturing the second portion.

2. The method as recited in claim 1 , including:
additively manufacturing a third portion of the component; and
joining the third portion to the first portion.

3. The method as recited in claim 1 , wherein the additive manufacturing step includes one of a direct metal laser sintering (DMLS) process, an electron beam melting (EBM) process, electron beam wire deposition (EBWD) process, a laser powder deposition (LPD) process, and a laser powder plasma spray (LPPS) process.

4. The method as recited in claim 1 , wherein the additive manufacturing step includes selectively melting a powdered metal, the powdered metal being one of (1) a titanium alloy, (2) tungsten alloy, (3) nickel alloy, (4) cobalt alloy, (5) steel alloy, and (6) a molybdenum alloy.

5. The method as recited in claim 2 , wherein the second and third portions each include channels therein, the channels formed during the steps of additively manufacturing the second and third portions, respectively, and configured to direct a cooling flow of fluid from a core passageway of the component toward an exterior of the component.

6. The method as recited in claim 5 , wherein the second portion is additively manufactured such that it includes a different quantity of channels than the third portion.

7. The method as recited in claim 5 , wherein the second portion is additively manufactured such that it includes at least one different type of channel than the third portion.

8. The method as recited in claim 2 , wherein the second portion and the third portion provide pressure and suction side walls of the component.

9. The method as recited in claim 8 , wherein the at least one radial support includes at least one rib projecting into a corresponding slot formed in one of the second portion and the third portion.

10. The method as recited in claim 1 , wherein the component is one of a rotor blade and a stator vane.

11. The method as recited in claim 1 , wherein the root, platform, and at least one radial support are integrally formed of one of a single crystal, directionally solidified, and an equiax alloy.

12. A method of forming a component of a gas turbine engine, comprising
forming a first portion of the component using one of a casting and a forging process, the first portion including a root, platform, and at least one radial support projecting from the platform;
additively manufacturing a second portion of the component, the second portion providing a side wall of the component;
joining the second portion to the first portion;
additively manufacturing a third portion of the component; and
joining the third portion to the first portion;
wherein the second portion and the third portion provide pressure and suction side walls of the component,
wherein the at least one radial support includes at least one rib projecting into a corresponding slot formed in one of the second portion and the third portion, and
wherein the at least one radial support includes a plurality of radial supports, each of the radial supports including a first rib and a second rib projecting into slots formed in the second portion and the third portion.

13. The method as recited in claim 12 , wherein the at least one radial support provides a mate face corresponding to a mate face of one of the second portion and the third portion.

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Zelesky Mark F

Classifications

• B22F10/40

  Structures for supporting workpieces or articles during manufacture and removed afterwards · CPC title

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B23K2103/04

  Steel {or steel} alloys · CPC title

• B23K26/0006

  taking account of the properties of the material involved (B23K26/32, B23K26/40 take precedence) · CPC title