Plated polymer fan

Patent metadata

Field	Value
Publication number	US-11268526-B2
Application number	US-201414903996-A
Country	US
Kind code	B2
Filing date	Jul 9, 2014
Priority date	Jul 9, 2013
Publication date	Mar 8, 2022
Grant date	Mar 8, 2022

Abstract

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

First claim

What is claimed is:

1. A fan blade for a gas turbine engine, the blade comprising:
at least one polymeric substrate forming a fan blade airfoil and having at least one exposed surface; and
at least one metallic plating layer deposited on the at least one exposed surface of the at least one polymeric substrate, wherein the at least one metallic plating layer has at least one area strengthened by bonding the at least one area to another metal-plated or metallic component using transient liquid phase bonding and the fan blade is located in a fan section of the gas turbine engine.

2. The blade of claim 1 , wherein the at least one polymeric substrate is formed into at least one of a root and a platform.

3. The blade of claim 1 , wherein the at least one metallic plating layer is selectively deposited on the at least one exposed surface providing vibration control.

4. The blade of claim 1 , wherein the at least one metallic plating layer is selectively deposited on the at least one exposed surface providing an electrical grounding path.

5. The blade of claim 1 , wherein the at least one metallic plating layer has an average thickness of 0.254 to 1.91 millimeters.

6. The blade of claim 1 , wherein the at least one polymeric substrate has local thicknesses between 1.27 and 50.8 millimeters.

7. A gas turbine engine, the engine comprising:
a plurality of fan blades comprising airfoils, each airfoil of the plurality of fan blades including a first at least one polymeric substrate having a first at least one exposed surface; and
a first at least one metallic plating layer deposited on the first at least one exposed surface, wherein the first at least one metallic plating layer has at least one area strengthened by bonding the at least one area to another metal-plated or metallic component using transient liquid phase bonding and the plurality of fan blades are located in a fan section of the gas turbine engine.

8. The engine of claim 7 , further comprising a fan case surrounding the plurality of fan blades, the fan case comprises a second at least one polymeric substrate having a second at least one exposed surface and a second at least one metallic plating layer deposited on the second at least one exposed surface.

9. The engine of claim 8 , further comprising at least one ice impact panel disposed on the fan case, the at least one ice impact panel comprises a third at least one polymeric substrate having a third at least one exposed surface and a third at least one metallic plating layer deposited on the third at least one exposed surface.

10. The engine of claim 7 , further comprising a plurality of discrete fan platforms, a single discrete fan platform of the plurality of discrete fan platforms is disposed between adjacent airfoils, each discrete fan platform comprises a second at least one polymeric substrate having a second at least one exposed surface and a second at least one metallic plating layer deposited on the second at least one exposed surface.

11. The engine of claim 10 , wherein the each discrete fan platform of the plurality of discrete fan platforms comprises at least one endwall, the at least one endwall comprises a third at least one polymeric substrate having a third at least one exposed surface and a third at least one metallic plating layer deposited on the third at least one exposed surface, wherein the third at least one metallic plating layer is polished.

12. The engine of claim 7 , wherein the first at least one metallic plating layer has an average thickness of 0.254 to 1.91 millimeters.

13. The engine of claim 7 , wherein the at least one polymeric substrate has local thicknesses between 1.27 and 50.8 millimeters.

14. A method of fabricating a fan blade for a gas turbine engine, the method comprising:
forming at least one polymeric substrate in a desired shape of the fan blade for a fan section of the gas turbine engine;
depositing at least one metallic plating layer on at least one exposed surface of the at least one polymeric substrate, wherein the at least one metallic plating layer has at least one weak area; and
using transient liquid phase bonding to bond the at least one weak area to another metal-plated or metallic component and strengthen the at least one weak area.

15. The method of claim 14 , wherein the desired shape is at least one of a root, a platform, and an airfoil of a fan blade.

16. The method of claim 14 , wherein the at least one metallic plating layer is selectively deposited on the at least one exposed surface.

17. The method of claim 14 , wherein the at least one metallic plating layer is polished.

18. The method of claim 14 , wherein the at least one polymeric substrate has local thicknesses between 1.27 and 50.8 millimeters.

19. The method of claim 14 , wherein the at least one metallic plating layer has an average thickness of 0.254 to 1.91 millimeters.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Roach James T
• Barnett Barry
• Cook Iii Grant O
• Watson Charles R
• Bugaj Shari L
• Levasseur Glenn
• Twelves Jr Wendell V
• Hertel Christopher J
• Kling Colin J
• Turner Matthew A
• Xu Jinquan
• Clarkson Steven
• Caulfield Michael

Classifications

• F01D5/147 Primary

  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

• F05D2230/90

  Coating; Surface treatment · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F04D19/002 Primary

  Axial flow fans · CPC title

• F01D5/26

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title