Abradable coating system

• US 8,821,116 B2
• Filed: 10/29/2010
• Issued: 09/02/2014
• Est. Priority Date: 10/30/2009
• Status: Active Grant

• Current Assignee: Ansaldo Energia Switzerland AG (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Grasso, Piero-Daniele, Ferber, Joergen, Stankowski, Alexander, Duval, Sophie, Olliges, Sven
• Primary Examiner(s): MCDOWELL, LIAM J
• Application Number:
  US12/915,978
• Publication Number:
  US 20110103940A1
• Time in Patent Office: 1,404 Days
• Field of Search: 415/173.4, 415/174.4, 416/229.R, 416/241.A, 416/241.B, 416/241.R, 427/140, 427/142, 427/202, 427/205, 427/244, 427/243, 427/372.2, 427/385.5, 427/388.1, 427/397.7
• US Class Current: 415/173.4
• CPC Class Codes: F01D 11/122 with erodable or abradable material blades having cutting or grinding tips F01D5/20
• CPC Class Codes: F01D 11/125 with a reinforcing structure
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment
• CPC Class Codes: F05D 2300/21 Oxide ceramics
• CPC Class Codes: F05D 2300/6012 Woven fabrics
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/612 Foam
• CPC Class Codes: F05D 2300/615 Filler
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An abradable coating system (2-8) for a turbine or a compressor is proposed has at least one layer of woven or non-woven tissue (15) or foam made of: ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. A free-standing preformed element (18) has at least one layer of such a woven or non-woven tissue or foam is filled with fillers and/or binder. A method prepares such a system. Finally, a method for the repair of an abradable coating portion of a turbine or the compressor component (9) includes in a first optional step that the damaged portion is at least partly removed and/or cleaned and/or surface treated, and in a second step at least one free-standing preformed abradable coating element (18) or a complete abradable coating system is attached to the component (9), preferably by using a matrix, wherein for example only a center part (2) or a fraction of a center part (2) is replaced.

Claims

1. An abradable coating system for clearance reduction in a turbine or a compressor, the turbine or compressor defining an axis of rotation and having blading and a component on which said system can be applied, the system comprising:

at least one block, wherein the block comprises;

a woven or non-woven tissue or foam made of a material selected from the group consisting of ceramic, glass, glass-ceramic, ceramic-metal composite, and combinations thereof, and

filler particles, filler fibers, an inorganic polymer binder, or combinations thereof, at least partially filling the tissue or foam;

a center part, wherein at least the center part of the system has an abradability which is graded along a radial direction with respect to the axis of rotation, such that the surface region of a side facing the blading is more abradable than an opposite side facing the component, wherein the center part is stripe-like and circumferentially oriented, wherein the center part is highly abradable such that it can be abraded by the blading;

a pair of stripe-like, circumferentially oriented side parts immediately axially adjacent to the center part, wherein the side parts are less abradable than the center part; and

wherein an abradable differentiation between the center part and the side parts is achieved by using a different impregnation matrix material for the center part and the side parts.

2. The abradable coating system according to claim 1, wherein the center part comprises layers of different abradability or a single layer with a graded abradability within said single layer.

3. The abradable coating system according to claim 2, wherein:

the center part comprises a plurality of layers each having the same tissue but having different impregnation in each layer, or

the center layer includes a single layer with a graded impregnation.

4. The abradable coating system according to claim 3, wherein the impregnation differs by type of filler particles, density of filler particles, type of filler fibers, density of filler fibers, type of binder material, density of binder material, or combinations thereof.

5. The abradable coating system according to claim 1, wherein the filler particles or filler fibers are formed from a material selected from the group consisting of ceramic, glass, glass-ceramic, ceramic-metal composite, and combinations thereof.

6. The abradable coating system according to claim 1, wherein the inorganic binder is selected from the group consisting of alkali silicate, alumino silicate, and aluminum phosphate.

7. The abradable coating system according to claim 1, wherein the at least one block has a height along the radial direction with respect to the axis of rotation in the range of 0.2-4 mm.

8. The abradable coating system according to claim 1, wherein an outer surface of the center part comprises surface texturing.

9. The abradable coating system according to claim 1, further comprising:

cooling elements including channels, grooves, or both, in the at least one block.

10. The abradable coating system according to claim 1, wherein the at least one block comprises a monoblock or an assembly of several blocks.

11. The abradable coating system according to claim 1, wherein fibers of the woven or non-woven tissue are aligned along a rotation direction.

12. The abradable coating system according to claim 1, further comprising:

said turbine or compressor component;

wherein the at least one block is on said component attached with a matrix.

13. The abradable coating system according to claim 12, wherein the matrix comprises filler particles, filler fibers embedded in inorganic polymer, or combinations thereof.

14. A method for the repair of an abradable coating portion of a turbine or a compressor component, the method comprising:

attaching at least complete abradable coating system according to claim 1 to the component.

15. The method according to claim 14, further comprising before said attaching:

inspecting the coating; and

at least partially removing, cleaning, surface treating, or combinations thereof, a damaged portion of the component.

16. The method according to claim 14, wherein attaching comprises attaching with a matrix.

17. The method according to claim 14, wherein attaching comprises attaching on at least a fraction of a center part of a damaged portion of the component.

18. The method according to claim 14, further comprising:

inspecting the repaired coating.

19. The abradable coating system according to claim 1, wherein the side parts are erosion resistant.

20. A method for the preparation of an abradable coating system on a turbine or compressor component, the turbine or compressor defining an axis of rotation and having blading and a component on which said system can be applied, and wherein the abradable coating system includes a center part having an abradability which is graded along a radial direction with respect to the axis of rotation, such that the surface region of a side facing the blading is more abradable than an opposite side facing the component, wherein the center part is stripe-like and circumferentially oriented, and a pair of stripe-like, circumferentially oriented side parts immediately axially adjacent to the center part, the method comprising:

(A1) first attaching a woven or non-woven tissue or foam made of a material selected from the group consisting of ceramic, glass, glass-ceramic, ceramic-metal composite, and combinations thereof, to the component or to a previous tissue or foam with a matrix, and

(A2) second impregnating the woven or non-woven tissue or foam with filler particles or fibers formed of a material selected from the group consisting of oxide precursor, oxide, and combinations thereof, with a binder of organic or inorganic polymer, or with both;

or

(B1) first impregnating a woven or non-woven tissue or foam made of a material selected from the group consisting of ceramic, glass, glass-ceramic, ceramic-metal composite, and combinations thereof, with filler particles or fibers selected from the group consisting of oxide precursor, oxide, and combinations thereof, with a binder selected formed from organic or inorganic polymer, or with both, and optionally pre-sintering, to form a matrix impregnated tissue, and

(B2) second attaching the matrix impregnated tissue to the component or the previous tissue or foam with a matrix,

(C) third heat treating the abradable coating system after (A2) or (B2), and

(D) producing an abradable differentiation between the center part and the side parts either before or after heat treating the abradable coating system, wherein the center part is highly abradable such that it can be abraded by the blading, and the side parts are less abradable than the center part; and

achieving the abradable differentiation between the center part and the side parts by using a different impregnation matrix material for the center part and the side parts.

21. The method according to claim 20, wherein, in (A1) and (B2), the matrix comprises:

filler particles, filler fibers, or both, formed from oxide precursor, oxide, and combinations thereof;

or

a binder formed from organic or inorganic polymer;

or both.

22. The method according to claim 20, further comprising:

repeating steps (A1) and (A2) as often as required before performing step (C).

23. The method according to claim 20, further comprising:

repeating steps (B1) and (B2) as often as required before performing step (C).

24. The method according to claim 20, wherein (A2) or (B1) comprises differentially impregnating or differentially selecting a matrix material to form grading of abradability along the radial direction of the abradable coating system.

25. The method according to claim 20, further comprising:

repeating (A1) plus (A2), or (B1) plus (B2), and (C), to form a multitude of abradable coating elements.

26. The method according to claim 20, further comprising:

forming a preform before (A1) or between (B1) and (B2).

27. The method according to claim 26, wherein the component is a new component or a component requiring repair.

28. The method according to claim 20, wherein the side parts are erosion resistant.