Metal-ceramic turbine shroud and method of making the same

• US 4,289,447 A
• Filed: 10/12/1979
• Issued: 09/15/1981
• Est. Priority Date: 10/12/1979
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Hemsworth, Martin C., Lenahan, Dean T., Sterman, Albert P., Gay, Charles H. Jr., Tegarden, Frederick W.
• Primary Examiner(s): Smith, Leonard E.
• Application Number:
  US06/084,244
• Time in Patent Office: 704 Days
• Field of Search: 415/200, 415/174, 428/593, 428/598, 264/60, 264/62, 264/81, 29/156.4 WL
• US Class Current: 415/200
• CPC Class Codes: F01D 11/125 with a reinforcing structure
• CPC Class Codes: Y10T 29/49316 Impeller making
• CPC Class Codes: Y10T 428/1234 Honeycomb, or with grain orientation or elongated elements in defined angular relationship in respective components [e.g., parallel, inter- secting, etc.]
• CPC Class Codes: Y10T 428/12375 having member which crosses the plane of another member [e.g., T or X cross section, etc.]
• CPC Class Codes: Y10T 428/24149 Honeycomb-like

Abstract

A turbine shroud includes a ceramic sealing layer secured to a metal substrate. In one form, the metal substrate includes a plurality of pegs extending therefrom. Intermediate bonding layers are disposed on the peg-metal substrate structure. A ceramic sealing layer of zirconium oxide with about 20 weight percentage magnesium oxide is disposed, e.g., plasma sprayed, on the intermediate bonding layers. The ceramic sealing layer includes an ordered pattern of very fine cracks therein which reduce the thermal stress in the ceramic sealing layer. A method of constructing a turbine shroud structure is also disclosed.

Claims

1. A turbine shroud structure of the type having a metal substrate and a ceramic sealing layer secured thereto, wherein the improvement comprises:

mechanical matrix bonding means disposed between said metal substrate and said ceramic sealing layer and bonding said ceramic sealing layer to said metal substrate with said ceramic sealing layer including an ordered pattern of very fine cracks which reduce the thermal stress in said ceramic sealing layer.

2. A turbine shroud structure in accordance with claim 1 in which said ceramic sealing layer comprises a ceramic selected from the group consisting of zirconium oxide and zirconium phosphate.

3. A turbine shroud structure in accordance with claim 2 including at least one intermediate layer disposed between said metal substrate and said ceramic sealing layer.

4. A turbine shroud structure in accordance with claim 3 in which said mechanical matrix bonding means comprises a plurality of pegs extending from said metal substrate.

5. A turbine shroud structure in accordance with claim 4 in which said pegs extend at least partially through said ceramic sealing layer.

6. A turbine shroud structure in accordance with claim 3 in which said mechanical matrix bonding means comprises wire mesh.

7. A turbine shroud structure in accordance with claim 6 in which said mechanical matrix bonding means comprises a plurality of pegs cooperating with said wire mesh.

8. A turbine shroud structure in accordance with claim 3 in which said ceramic sealing layer has a thickness of between about 0.035 to 0.040 inches.

9. A turbine shroud structure in accordance with claim 8 in which said ceramic sealing layer comprises zirconium oxide with about 6 to 25 weight percentage magnesium oxide.

10. A turbine shroud structure in accordance with claim 8 in which said ceramic sealing layer comprises zirconium oxide with about 6 to 25 weight percentage yttrium oxide.

11. A turbine shroud structure in accordance with claim 8 in which said ceramic sealing layer comprises zirconium phosphate.

12. A method of constructing a turbine shroud structure, comprising the steps of:

(a) providing a metal substrate;

(b) providing said metal substrate with mechanical matrix bonding means having a predetermined spatial configuration, and then

(c) applying a ceramic sealing layer to said mechanical matrix bonding means and causing said ceramic sealing layer to develop an ordered pattern of very fine cracks therein which reduce the thermal stress in said ceramic sealing layer.

13. A method in accordance with claim 12 in which said ceramic sealing layer comprises a ceramic selected from the group consisting of zirconium oxide and zirconium phosphate.

14. A method in accordance with claim 13 in which said ceramic sealing layer comprises zirconium oxide modified with about 6 to 25 weight percentage magnesium oxide.