Sealing arrangement for turbine engine having ceramic components

1. A seal arrangement for reducing seal gaps within a turbine engine including a circumferentially extending structure having an axially extending surface forming a gas flow path extending parallel to an axis of said turbine engine, said seal arrangement comprising:

a plurality of circumferentially disposed segments defining said circumferentially extending structure, each said segment including:

an axially forward circumferential edge, an axially aft circumferential edge, and a pair of circumferentially spaced axial edges extending between said forward and aft edges;

a surface portion comprising a portion of said axially extending surface and extending between said forward and aft circumferential edges and between said pair of axial edges, said surface portion extending generally parallel to said axis of said turbine engine in contact with high velocity gases flowing therethrough; and

each said axial edge comprising a radial surface extending radially from said surface portion;

said segments arranged such that a gap is defined between facing axial edges of adjacent ones of said segments;

a sealing element extending within said gap from said surface portions of said adjacent segments radially along at least a portion of said facing axial edges, said sealing element comprising a compliant material in the circumferential direction to span said gap during reduction and expansion of said gap; and

wherein said sealing element is non-homogeneous including a first layer and a second layer, said first layer comprising a non-woven fibrous layer compressed in the circumferential direction between said facing axial edges to a thickness reduced from its uncompressed thickness and at least a portion of said second layer defining a protective erosion resistant surface located adjacent to and spanning between said surface portions of said adjacent segments.

2. The seal arrangement of claim 1 , wherein said first layer is radially displaced from said erosion resistant surface.

3. The seal arrangement of claim 1 , wherein said non-woven fibrous layer comprises a ceramic felt.

4. The seal arrangement of claim 1 , wherein said second layer of said sealing element comprises a woven layer of material.

5. The seal arrangement of claim 4 , wherein said second layer of said sealing element is formed of one of Nextel 610 and Nextel 720.

6. The seal arrangement of claim 1 , wherein said second layer comprises a portion of said non-woven fibrous material adjacent said surface portions infiltrated with a hardener, where said first layer comprises a portion of said non-woven fibrous material that does not include said hardener.

7. The seal arrangement of claim 6 , wherein said hardener comprises at least one of an alumina slurry and an alumina precursor.

8. The seal arrangement of claim 1 , wherein said non-woven fibrous layer is compressed between said facing axial edges to a thickness of about one-third the uncompressed thickness of said non-woven fibrous layer.

9. The seal arrangement of claim 1 , wherein each of said adjacent segments comprises a ceramic material and said seal element comprises a ceramic material and is bonded to at least one of said facing axial edges.

10. A seal arrangement for reducing seal gaps within a turbine engine including a circumferentially extending structure having an axially extending surface forming a gas flow path extending parallel to an axis of said turbine engine, said seal arrangement comprising:

a plurality of circumferentially disposed segments defining said circumferentially extending structure, each said segment including:

an axially forward circumferential edge, an axially aft circumferential edge, and a pair of circumferentially spaced axial edges extending between said forward and aft edges;

a surface portion comprising a portion of said axially extending surface and extending between said forward and aft circumferential edges and between said pair of axial edges, said surface portion extending generally parallel to said axis of said turbine engine in contact with high velocity gases flowing therethrough; and

each said axial edge comprising a radial surface extending radially from said surface portion;

said segments arranged such that a gap is defined between facing axial edges of adjacent ones of said segments;

a sealing element extending within said gap from said surface portions of said adjacent segments radially along at least a portion of said facing axial edges, said sealing element comprising a compliant material in the circumferential direction to span said gap during reduction and expansion of said gap; and

wherein said sealing element comprises a first layer and a second layer, said first layer comprising a ceramic felt compressed in the circumferential direction between said facing axial edges to a thickness reduced from its uncompressed thickness, at least a portion of said second layer defining a protective erosion resistant surface located adjacent to and spanning between said surface portions of said adjacent segments, wherein each of said adjacent segments comprises a ceramic material and said seal element is bonded to at least one of said facing axial edges.

11. The seal arrangement of claim 10 , wherein said first layer is radially displaced from said erosion resistant surface.

12. The seal arrangement of claim 11 , wherein said second layer of said sealing element comprises a woven layer of material.

13. The seal arrangement of claim 10 , wherein said second layer comprises a portion of said ceramic felt adjacent said surface portions infiltrated with a hardener, where said first layer comprises a portion of said ceramic felt that does not include said hardener.

14. The seal arrangement of claim 13 , wherein said hardener comprises at least one of an alumina slurry and an alumina precursor.

15. The seal arrangement of claim 10 , wherein said ceramic felt is compressed between said facing axial edges to a thickness of about one-third the uncompressed thickness of said ceramic felt.

16. A seal arrangement for reducing seal gaps within a turbine engine including a circumferentially extending structure having an axially extending surface forming a gas flow path extending parallel to an axis of said turbine engine, said seal arrangement comprising:

a plurality of circumferentially disposed segments defining said circumferentially extending structure, each said segment including:

an axially forward circumferential edge, an axially aft circumferential edge, and a pair of circumferentially spaced axial edges extending between said forward and aft edges;

a surface portion comprising a portion of said axially extending surface and extending between said forward and aft circumferential edges and between said pair of axial edges, said surface portion extending generally parallel to said axis of said turbine engine in contact with high velocity gases flowing therethrough; and

each said axial edge comprising a radial surface extending radially from said surface portion;

said segments arranged such that a gap is defined between facing axial edges of adjacent ones of said segments;

a sealing element extending within said gap from said surface portions of said adjacent segments radially along at least a portion of said facing axial edges, said sealing element comprising a compliant material in the circumferential direction to span said gap during reduction and expansion of said gap;

wherein said sealing element comprises a corrugated seal located adjacent to and spanning between said surface portions of said adjacent segments; and

wherein said sealing element is affixed to at least one of said facing axial edges.

17. The seal arrangement of claim 16 , wherein said sealing element comprises a first corrugated CMC layer, a second corrugated CMC layer and a layer of ceramic felt disposed between said first corrugated CMC layer and said second corrugated CMC layer.

18. The seal arrangement of claim 16 , wherein each of said adjacent segments comprises a ceramic material.

19. The seal arrangement of claim 16 , wherein corrugations of said corrugated seal extend in the radial direction, and said corrugated seal is formed from one of a CMC and an oxide dispersion strengthened super alloy.