COMPOSITE AIRFOIL

• US 20090081032A1
• Filed: 09/20/2007
• Published: 03/26/2009
• Est. Priority Date: 09/20/2007
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Tipton, Thomas R., Moroso, Joseph L.
• Application Number:
  US11/858,326
• Publication Number:
  US 20090081032A1
• Time in Patent Office: Days
• US Class Current: 415/200
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F05D 2300/43 Synthetic polymers, e.g. plastics; Rubber
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine component includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material. A plastic airfoil portion envelopes at least a portion of the core.

Claims

1. A turbine component comprising:

mounting structure for attaching the turbine component;

a core attached to the mounting structure, the core made from a structural material; and

a plastic airfoil portion enveloping at least a portion of the core.

2. The turbine component of claim 1 wherein the core has a leading edge and the airfoil portion envelopes at least the leading edge portion of the core.

3. The turbine component of claim 1 wherein the airfoil portion envelopes the entire core.

4. The turbine component of claim 1 wherein the core has at least one void therein.

5. The turbine component of claim 4 wherein the airfoil portion is made from an injection molded plastic material that extends at least partially into the void in the core.

6. The turbine component of claim 4 wherein the core has a plurality of voids extending through the core.

7. The turbine component of claim 6 wherein the airfoil portion is made from an injection molded plastic material that extends at least partially into the voids in the core.

8. The turbine component of claim 1 wherein the core is made from a material selected from the group of metal and ceramic.

9. The turbine component of claim 1 wherein the core and mounting structure are integrally formed as one piece.

10. The turbine component of claim 1 wherein the core is made from a forged, die cast or investment cast metal material formed into a desired shape.

11. A turbine component comprising:

mounting structure for attaching the turbine component;

a core attached to the mounting structure, the core made from a structural material and having at least one void formed in the core; and

an airfoil portion enveloping at least a portion of the core, the airfoil portion made from a plastic material that extends at least partially into the void in the core.

12. The turbine component of claim 11 wherein the core has a leading edge and the airfoil portion envelopes at least the leading edge portion of the core.

13. The turbine component of claim 11 wherein the airfoil portion envelopes the entire core.

14. The turbine component of claim 11 wherein the void extends through the core.

15. The turbine component of claim 11 wherein the core is made from a material selected from the group of metal and ceramic.

16. The turbine component of claim 11 wherein the core and mounting structure are integrally formed as one piece.

17. The turbine component of claim 11 wherein the airfoil portion is injection molded onto the core.

18. A component for a gas turbine having a plurality of compressor and turbine stages, the component comprising:

mounting structure for attaching the component to gas turbine structure;

a core integrally formed as one piece with the mounting structure, the core made from a material selected from the group of metal and ceramic and having a plurality of voids extending through the core; and

an airfoil enveloping the entire core, the airfoil made from an injection molded plastic material that extends at least partially into the voids in the core.

19. The component of claim 18 wherein the airfoil extends into and completely fills the voids in entire core.

20. The component of claim 18 wherein the component is used in one of the first gas turbine compressor stages.