Low transient thermal stress turbine engine components

• US 7,967,570 B2
• Filed: 07/27/2007
• Issued: 06/28/2011
• Est. Priority Date: 07/27/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Schmidt, Wayde R., Shi, Jun
• Primary Examiner(s): Kershteyn; Igor
• Application Number:
  US11/829,391
• Publication Number:
  US 20090028697A1
• Time in Patent Office: 1,432 Days
• Field of Search: 416/223.R, 416/241.R, 416/223.A, 416/244.A, 298/892, 298/892.7, 415/200
• US Class Current: 416/223.00R
• CPC Class Codes: B33Y 80/00 Products made by additive manufacturing
• 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 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F05D 2230/30 with deposition of material
• CPC Class Codes: F05D 2300/50212 dissimilar
• CPC Class Codes: Y10T 29/4932 Turbomachine making

Abstract

A turbine vane includes a platform; and at least one airfoil mounted to the platform and having a trailing edge and a leading edge, wherein the vane is composed of a functionally graded material having a first material and a second material, wherein the trailing edge includes a greater amount of the first material than the second material, and the leading edge includes a greater amount of the second material than the first material.

Claims

1. A process for manufacturing a turbine engine component comprising fabricating a turbine engine component having an airfoil portion with a leading edge and a trailing edge using a functionally graded composite material having at least two different materials including a first material and a second material, and said fabricating step comprising fabricating said trailing edge to include a greater amount of said first material than said second material and fabricating said leading edge to include a greater amount of said second material than said first material.

2. The process of claim 1, wherein fabricating comprises grading said at least two different materials to form said functionally graded material of said turbine engine component.

3. The process of claim 2, wherein grading comprises at least one of the following types of grading:

linear, non-linear, step functions, quadratic, polynomial, point defects, and combinations thereof.

4. The process of claim 1, wherein fabricating comprises at least one of the following processes:

solid freeform fabricating, selective laser sintering, fused deposition modeling, extrusion freeform fabricating, laser enhanced net shaping, 3-dimensional printing, ink jet printing and combinations thereof.

5. The process of claim 1, wherein said at least two different materials comprises at least two of the following materials:

metal, ceramic, metal alloy, mixed powders, composite particle, multiple metals or ceramics, and combinations thereof.

6. The process of claim 1, wherein said at least two different materials each exhibit different morphologies or different microstructures or both different morphologies and different microstructures.

7. The process of claim 1, wherein said at least two different materials are at least two different powdered materials.

8. The process of claim 1, wherein said turbine engine component comprises a functionally graded composite material structure having a first phase and a second phase.

9. The process of claim 8, further comprising infiltrating at least a portion of said second phase with at least one material.

10. The process of claim 9, wherein said at least one material comprises at least one of the following materials:

metal, metal alloy, ceramic, composite particle, mixed powders and combinations thereof.

11. A process for manufacturing a turbine engine component comprising fabricating a turbine engine component using a functionally graded composite material having at least two different materials, wherein said turbine engine component comprises a functionally graded composite material structure having a first phase and a second phase, infiltrating at least a portion of said second phase with at least one material, and wherein said second phase comprises a residual porosity.

12. A process for manufacturing a turbine engine component, comprises:

fabricating a turbine engine component using a functionally graded composite material having a first phase and a second phase; and

infiltrating at least a portion of said second phase with at least one material, wherein said second phase comprises a residual porosity.

13. The process of claim 12, wherein fabricating comprises at least one of the following processes:

solid freeform fabricating, selective laser sintering, fused deposition modeling, extrusion freeform fabricating, laser enhanced net shaping, 3-dimensional printing, ink jet printing and combinations thereof.

14. The process of claim 13, wherein fabricating further comprises grading at least two different materials to form said functionally graded composite material.

15. The process of claim 14, wherein grading comprises at least one of the following types of grading:

linear, non-linear, step functions, quadratic, polynomial, point defects, and combinations thereof.

16. A turbine vane, comprising:

a platform; and

at least one airfoil mounted to said platform and having a trailing edge and a leading edge,

wherein the vane is composed of a functionally graded material having a first material and a second material,

wherein said trailing edge includes a greater amount of said first material than said second material, and said leading edge includes a greater amount of said second material than said first material.

17. The turbine vane of claim 16, wherein said first material possesses a greater coefficient of thermal expansion and lower heat capacity than a coefficient of thermal expansion and heat capacity of said second material.

18. The turbine vane of claim 16, wherein said second material possesses a greater thermal conductivity value and greater stiffness than a thermal conductivity value and stiffness of said first material.

19. The turbine vane of claim 16, wherein said functionally graded composite material comprises at least two of the following materials:

metal, metal alloy, ceramic, mixed powders, composite particle, multiple metals or ceramics, and combinations thereof.

20. The turbine vane of claim 16, wherein said functionally graded composite material comprises at least two different materials, each of said at least two different materials exhibit different morphologies or different microstructures or both different morphologies and different microstructures.