In-situ formed thermal barrier coating for a ceramic component

• US 7,402,347 B2
• Filed: 01/07/2005
• Issued: 07/22/2008
• Est. Priority Date: 12/02/2004
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Power Generation, Inc.
• Inventors: Morrison, Jay A., Merrill, Gary B., Thompson, Daniel G., Lane, Jay Edgar
• Primary Examiner(s): Speer; Timothy M.
• Assistant Examiner(s): Baldwin; Gordon R
• Application Number:
  US11/031,796
• Publication Number:
  US 20060121296A1
• Time in Patent Office: 1,292 Days
• Field of Search: None
• US Class Current: 428/701
• CPC Class Codes: B05D 3/02 by baking B05D3/04 takes precedence
• 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: F04D 29/388 characterised by construction
• CPC Class Codes: F05D 2230/23 by permanently joining parts together
• CPC Class Codes: F05D 2300/601 Fabrics
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/614 Fibres or filaments

Abstract

A thermal barrier layer (20) is formed by exposing an oxide ceramic material to a thermal regiment to create a surface heat affected zone effective to protect an underlying structural layer (18) of the material. The heat affected surface layer exhibits a lower strength and higher thermal conductivity than the underlying load-carrying material; however, it retains a sufficiently low thermal conductivity to function as an effective thermal barrier coating. Importantly, because the degraded material retains the same composition and thermal expansion characteristics as the underlying material, the thermal barrier layer remains integrally connected in graded fashion with the underlying material without an interface boundary there between. This invention is particularly advantageous when embodied in an apparatus formed of an oxide-oxide ceramic matrix composite (CMC) material wherein reinforcing fibers (24) are anchored in the underlying load-carrying portion and extend into the non-structural thermal barrier portion to provide support and to function as surface crack arrestors. In one embodiment an airfoil (10) is formed of a stacked plurality of CMC plates having such a heat-affected thermal barrier layer formed thereon.

Claims

1. An apparatus comprising a heat-affected thermal barrier portion of a ceramic oxide material integral with an underlying cooled structural portion of the ceramic oxide material, the heat-affected thermal barrier portion effective to thermally protect the underlying structural portion from a high temperature operating environment.

2. The apparatus of claim 1, further comprising the heat-affected portion having an effective k/t of less than 5,000 W/m².

3. The apparatus of claim 1, further comprising the heat-affected portion having an effective k/t of less than 2,500 W/m².

4. The apparatus of claim 1, further comprising the heat-affected portion having an effective k/t of less than 1,000 W/m².

5. The apparatus of claim 1, further comprising the heat-affected portion having a thickness of at least 0.25 mm.

6. The apparatus of claim 1, further comprising the heat-affected portion having a thickness of at least 0.5 mm.

7. The apparatus of claim 1, further comprising the heat-affected portion having a thickness of at least 3 mm.

8. The apparatus of claim 1, wherein the ceramicoxide material comprises an oxide-oxide ceramic matrix composite material, and wherein reinforcing fibers of the ceramic matrix composite material interconnect the heat-affected portion and the structural layer.

9. An apparatus comprising:

an inner load-bearing portion of a ceramic oxide material exhibiting a first thermal conductivity and a first strength;

a cooling passage effective to cool the inner load-bearing portion;

an outer heat-affected thermal barrier portion of the ceramic oxide material integrally connected in graded fashion with the inner load-bearing portion;

the outer portion exhibiting a graded thermal conductivity range higher than the first thermal conductivity and a graded strength range lower than the first strength resulting from exposure of a surface of the ceramic oxide material to a high temperature while the inner load-bearing portion of the ceramic oxide material is cooled by coolant passing through the cooling passage; and

a thickness of the outer portion effective to provide a desired degree of thermal protection to the cooled inner load-bearing portion during use of the apparatus in a high temperature environment such that a strength of the inner load-bearing portion remains greater than a level of stress applied to the inner load-bearing portion.

10. The apparatus of claim 9, further comprising the outer heat-affected thermal barrier portion having an effective k/t of less than 5,000 W/m².

11. The apparatus of claim 9, further comprising the outer heat-affected thermal barrier portion having an effective k/t of less than 1,000 W/m².

12. The apparatus of claim 9, further comprising the outer heat-affected thermal barrier portion having a thickness of at least 0.25 mm.

13. The apparatus of claim 9, further comprising the outer heat-affected thermal barrier portion having a thickness of at least 0.5 mm.

14. The apparatus of claim 9, wherein the ceramic oxide material comprises an oxide-oxide ceramic matrix composite material comprising reinforcing fibers extending between the inner load-bearing portion and the outer heat-affected thermal barrier portion.

15. An apparatus comprising:

a structural member comprising an oxide-oxide ceramic matrix composite material;

an outer heat-affected layer having a thickness of at least 0.25 mm formed in the oxide-oxide ceramic matrix composite material and effective to thermally insulate an underiying structural layer of the oxide-oxide ceramic matrix composite material from an exterior environment; and

reinforcing fibers of the oxide-oxide ceramic matrix composite material extending to interconnect the outer heat-affected layer with the underlying structural layer.

16. The apparatus of claim 15, wherein the heat-affected layer has a thickness of at least 0.5 mm.

17. The apparatus of claim 15, wherein the heat-affected layer exhibits an effective k/t of less than 5,000 W/m².

18. The apparatus of claim 15, wherein the heat-affected layer exhibits an effective k/t of less than 1,000 W/m².

19. An airfoil comprising:

a stacked plurality of plates, each plate comprising an oxide-oxide ceramic matrix composite material comprising an outer surface defining an airfoil shape;

an outer heat-affected portion of each plate collectively defining a thermal barrier layer for the airfoil effective to thermally protect an underlying structural portion of each plate from an exterior environment; and

reinforcing fibers of the oxide-oxide ceramic matrix composite material extending to interconnect the outer heat-affected portion with the underlying structural portion.

20. The airfoil of claim 19, further comprising the thermal barrier layer comprising an effective k/t of less than 5,000 W/m².

21. The airfoil of claim 19, further comprising the thermal barrier layer comprising an effective k/t of less than 1,000 W/m².

22. The airfoil of claim 19, further comprising the thermal barrier layer comprising a thickness of at least 0.25 mm.

23. The airfoil of claim 19, further comprising the thermal barrier layer comprising a thickness of at least 0.5 mm.

24. An apparatus comprising:

an inner load-bearing portion of a ceramic oxide material;

a coolant applied to the inner load-bearing portion;

an outer heat-affected thermal barrier portion of the ceramic oxide material integrally connected in graded fashion with the inner load-bearing portion, the outer heat-affected thermal barrier portion formed by exposure of a surface of the ceramic oxide material to a high temperature while the inner load-bearing portion of the ceramic oxide material is cooled by the coolant; and

a plurality of cracks extending from the surface into the outer portion and formed as a result of residual stresses generated in the outer portion by the exposure of the surface to the high temperature and subsequent cool down, the plurality of cracks effective to provide stress relief in the outer portion.

25. The apparatus of claim 24, further comprising:

reinfoming fibers disposed within the ceramic oxide material and extending proximate the surface;

wherein respective depths of the cracks are arrested by the reinforcing fibers.

26. The apparatus of claim 25, further comprising theouter heat-affected thermal barrier portion of the ceramic oxide material comprising an effective k/t of less than 2,500 W/m².

27. The apparatus of claim 26, wherein the apparatus comprises a plate comprising an outer surface defining an airfoil shape.