Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud

• US 20090053045A1
• Filed: 08/22/2007
• Published: 02/26/2009
• Est. Priority Date: 08/22/2007
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Trangsrud, Christopher Hans, Myers, Melbourne James, Nowak, Daniel, Krishnakumar, Poornathresan, Zhao, Richard L.
• Application Number:
  US11/843,346
• Publication Number:
  US 20090053045A1
• Time in Patent Office: Days
• US Class Current: 415/173.100
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2230/232 by welding
• CPC Class Codes: F05D 2230/236 Diffusion bonding
• CPC Class Codes: F05D 2300/171 Steel alloys
• CPC Class Codes: Y10T 29/49297 Seal or packing making

Abstract

A gas turbine assembly includes a shroud that includes a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material. The arcuate base is made up of an annular member having an axial component and a pair of upstanding ribs having flanges, wherein the arcuate base further comprises a high temperature capable material layer disposed on a surface of the arcuate base so as to define an inner diameter of the shroud segment (i.e., the hot gas path side or environmental side).

Claims

1. A gas turbine comprising:

a shroud comprising a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material and made up of an annular member having an axial component and a pair of upstanding ribs and having flanges, wherein the arcuate base further comprises a second metal material bonded to the first metal material of the arcuate base so as to define an inner diameter of the shroud segment.

2. The gas turbine of claim 1, wherein the second metal material is selected to be stable at temperatures greater than 600°

C. and the first metal material is stable at temperatures less than 800°

C.

3. The gas turbine of claim 1, wherein the second metal material is a superalloy.

4. The gas turbine of claim 1, wherein the first metal material is formed of a stainless steel.

5. The gas turbine of claim 1, wherein the second metal material has a higher melting point than the first metal material.

6. The gas turbine of claim 1, wherein the second metal material is at a thickness of less than about 2 inches and the first metal material is at a thickness from about 1 inch to about 12 inches.

7. The gas turbine of claim 1, wherein the second metal material is at a thickness less than about 1 inch and the first metal material is at a thickness of about 1 inch to about 12 inches.

8. The gas turbine of claim 1, wherein the second metal material has a thickness less than about 0.75 inches and the first metal material is at a thickness of about 1 inch to about 12 inches.

9. A process for manufacturing a shroud for a turbine engine, comprising:

forming a ring having a pair of upstanding ribs and having flanges, wherein the ring is formed of a first metal material; and

bonding a second metal material to a surface of the ring defining an inner diameter.

10. The process of claim 9, wherein the second metal material is selected to be stable at temperatures greater than 600°

C. and the first metal material is stable at temperatures less than 800°

C.

11. The process of claim 9, further comprising segmenting the ring into segments.

12. The process of claim 9, wherein bonding the second metal material to the first metal material comprises a weld build-up process, a strip cladding process, a brazing process or a solid state bonding process.

13. The process of claim 9, wherein forming the ring comprises a forging process, sand casting, investment casting, centrifugal casting, and a fabrication process.

14. The process of claim 9, wherein the second metal material is selected to have a higher melting point than the first metal material.

15. A gas turbine comprising:

a shroud comprising a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material stable at a temperature less than 800°

C. and made up of an annular member having an axial component and a pair of upstanding ribs and having flanges; and

a second metal material bonded to the first metal material so as to define an inner diameter of the shroud segment, wherein the second metal material is stable at temperatures greater than 600°

C.

16. The gas turbine of claim 15, wherein the second metal material is a superalloy.

17. The gas turbine of claim 15, wherein the first metal is formed of a stainless steel.

18. The gas turbine of claim 15, wherein the layer of the second metal material is at a thickness less than about 2 inches and the first metal material is at a thickness from about 1 inch to about 12 inches.

19. The gas turbine of claim 15, wherein the second material is selected to have a higher melting point than the first metal material.

20. The gas turbine of claim 15, wherein the second metal material has a thickness less than about 0.75 inches and the first metal material is at a thickness of about 1 inch to about 12 inches.