Method of producing a gas turbine engine component

Patent metadata

Field	Value
Publication number	US-10793943-B2
Application number	US-201815922230-A
Country	US
Kind code	B2
Filing date	Mar 15, 2018
Priority date	Mar 15, 2018
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

A method of producing a gas turbine engine fan blade having a geometric configuration is provided. The method includes: plastically deforming an initial substrate comprised of a first metallic material into a formed substrate; depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blade blank, which depositing includes: additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion; additively depositing second metallic material to at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion; and shaping the blade blank into the geometric configuration.

First claim

What is claimed is:

1. A method of producing a gas turbine engine fan blade having a geometric configuration,
the method comprising:
plastically deforming an initial substrate comprised of a first metallic material into a formed substrate that has a first face surface,
a second face surface,
the first face surface is opposite the second face surface, a first end surface and a second end surface,
the second end surface is opposite the first end surface; and depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a fan blade blank,
the depositing including:
depositing the second metallic material onto at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface,
to form a fan blade root portion;
depositing the second metallic material onto at least one of the first face surface or the second face surface of the formed substrate between the fan blade root portion and the second end surface to form a fan blade airfoil portion; and
shaping the fan blade blank into the geometric configuration of the gas turbine engine fan blade.

2. The method of claim 1 , wherein the first metallic material and the second metallic material each comprise titanium.

3. The method of claim 2 ,
wherein the step of depositing the second metallic material onto the formed substrate to form the fan blade airfoil portion,
includes depositing the second metallic material to define at least one internal cavity.

4. The method of claim 3 , wherein the depositing the second metallic material to define at least one open internal cavity includes defining a plurality of internal cavities and at least one rib separating adjacent internal cavities.

5. The method of claim 4 , wherein the step of depositing the second metallic material to form the fan blade airfoil portion, includes defining a shelf surface extending around a perimeter of the at least one internal cavity.

6. The method of claim 5 , further comprising attaching a cover panel to enclose the at least one open internal cavity.

7. The method of claim 6 , further comprising plastically deforming a substrate to form the cover panel, the cover panel configured to mate with the shelf surface.

8. The method of claim 1 , wherein the additive manufacturing process is a plasma arc, wire feed deposition process.

9. The method of claim 1 , wherein the step of plastically deforming the initial substrate includes hot forming the initial substrate.

10. The method of claim 1 , wherein at least a portion of the first face surface of the formed substrate has a convex configuration, and at least a portion of the second face surface of the formed substrate has a concave configuration.

11. The method of claim 1 , wherein the step of shaping the blade blank into the geometric configuration of the gas turbine engine fan blade includes producing a leading edge, a trailing edge, and a blade tip surface extending between the leading edge and the trailing edge.

12. The method of claim 1 , wherein the step of plastically deforming the initial substrate includes plastically deforming the initial substrate so that at least a portion of the first face surface of the formed substrate has a convex configuration, and at least a portion of the second face surface of the formed substrate has a concave configuration.

13. The method of claim 1 , wherein the initial substrate is a planar body.

14. The method of claim 1 , wherein the step of plastically deforming an initial substrate into a formed substrate includes plastically deforming the initial substrate such that at least a portion of the formed substrate has a twist.

15. A method of producing a gas turbine engine fan blade having a geometric configuration,
the method comprising:
plastically deforming an initial substrate comprised of a first metallic material into a formed substrate that has a first face surface,
a second face surface,
the first face surface is opposite the second face surface, a first end surface and a second end surface,
the second end surface is opposite is opposite the first end surface; and
depositing a second metallic material onto the formed substrate using an additive manufacturing process to produce a blank,
the depositing including:
depositing the second metallic material onto at least one of the first face surface or the second face surface of the formed substrate adjacent the first end surface, to form a root portion;
depositing the second metallic material onto at least one of the first face surface or the second face surface to form an airfoil portion:
depositing the second metallic material onto at least one of the first face surface or the second face surface of the formed substrate between the root portion and the second end surface to form an airfoil portion;
depositing the second metallic material onto the first face surface of the formed substrate between the root portion and the airfoil portion, and
to the second face surface of the formed substrate between the root portion and the airfoil portion to form a platform portion; and
shaping the blade blank into the geometric configuration of the gas turbine engine fan blade.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Malmborg Eric W

Classifications

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2250/291

  hollowed · CPC title

• C23C4/134 Primary

  Plasma spraying · CPC title

• B23K10/027

  Welding for purposes other than joining, e.g. build-up welding · CPC title