Method of Forming a Turbine Engine Component Having a Vapor Resistant Layer

• US 20100021643A1
• Filed: 07/22/2008
• Published: 01/28/2010
• Est. Priority Date: 07/22/2008
• Status: Abandoned Application

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Power Generation, Inc.
• Inventors: Lane, Jay E., Merrill, Gary B.
• Application Number:
  US12/177,567
• Publication Number:
  US 20100021643A1
• Time in Patent Office: Days
• US Class Current: 427/376.200
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/614 Fibres or filaments

Abstract

A method of forming a turbine component that includes a ceramic matrix composite-ceramic insulation composite with a vapor resistant layer is disclosed. The method includes providing an inner tool and an outer tool, wherein the inner and outer tools define a mold for forming a turbine component. A vapor resistant layer can be applied to the inner tool, and a ceramic insulation layer can be applied over the vapor resistant layer in the mold. The vapor resistant layer and the ceramic insulation layer can be partially fired to form a bisque turbine component, and the outer tool can be removed. The inner tool can include a transitory material. A layer of ceramic matrix composite material can be applied to the outside of the bisque turbine component to form a component, and the component can be fired to form a turbine component.

Claims

1. A method of forming a turbine component having a vapor resistant layer, comprising:

providing an inner tool and an outer tool, wherein the inner and outer tools define a mold for forming a turbine component;

applying a vapor resistant layer to the inner tool;

applying a ceramic insulation layer over the vapor resistant layer in the mold;

partially firing the vapor resistant layer and the ceramic insulation layer to form a bisque turbine component; and

removing the outer tool.

2. The method of claim 1, wherein providing the inner tool comprises providing the inner tool comprising a transitory material.

3. The method of claim 2, further comprising removing the transitory material and the inner tool.

4. The method of claim 2, further comprising removing the transitory material and the inner tool after forming the bisque turbine component.

5. The method of claim 1, wherein applying the vapor resistant layer comprises applying the vapor resistant layer comprising a composition selected from the group consisting of HfSiO₄;

ZrSiO₄;

Y₂Si₂O₇;

Y₂O₃;

ZrO₂;

HfO₂;

ZrO₂ stabilized by yttria, HfO₂ stabilized by yttria, ZrO₂/HfO₂ stabilized by yttria, yttrium aluminum garnet;

Rare Earth (RE) silicates of the form RE₂Si₂O₇;

RE oxides of the form RE₂O₃;

RE zirconates or hafnates of the form RE₄Zr₃O₁₂ or RE₄Hf₃O₁₂; and

combinations thereof, wherein RE is one or more of Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu.

6. The method of claim 1, further comprising,

applying a layer of ceramic matrix composite material to the outside of the bisque turbine component to form a component;

and

firing the component.

7. The method of claim 6, further comprising machining the ceramic insulation layer of the bisque turbine component before applying the ceramic matrix composite layer.

8. The method of claim 6, wherein providing an inner tool comprises providing the inner tool comprising a transitory material, and the method further comprises removing the transitory material and the inner tool.

9. The method of claim 8, further comprising installing a inner machining tool in the bisque turbine component after the inner tool is removed, wherein the inner machining tool comprises a second transitory material.

10. The method of claim 9, further comprising machining the ceramic insulation layer of the bisque turbine component after installing the inner machining tool and before applying the ceramic matrix composite layer.

11. The method of claim 10, wherein the transitory material and the second transitory material are different.

12. The method of claim 10, further comprising removing the second transitory material and the inner machining tool after machining the ceramic insulation layer of the bisque turbine component.

13. The method of claim 6, further comprising compacting the ceramic matrix composite material using a CMC compaction tool.

14. The method of claim 6, wherein the component is a turbine component selected from the group consisting of transitions, combustor liners, combustor ring segments, vane shrouds and blade platform covers.

15. The method of claim 1, wherein applying the vapor resistant layer comprises applying the vapor resistant layer in the form of a viscous paste, a paint, a tape, a spray, or a combination thereof.

16. The method of claim 1, wherein applying the vapor resistant layer comprises applying the vapor resistant layer to the inner tool using an intermediate outer tool, wherein the inner tool and the intermediate outer tool form a mold for casting the vapor resistant layer.

17. The method of claim 16, further comprising,

stabilizing the vapor resistant layer;

and

removing the intermediate outer tool before applying the ceramic insulation layer.

18. The method of claim 1, further comprising stabilizing the vapor resistant layer, wherein the vapor resistant layer is stabilized by a process comprising heating, drying, curing, and combinations thereof.

19. The method of claim 18, wherein the vapor resistant layer is partially stabilized and diffusion between the vapor resistant layer and the ceramic insulation layer occurs before or during the partial firing step.

20. The method of claim 1, wherein applying the ceramic insulation layer comprises applying a friable graded insulation.