Axial non-contact seal

1. A gas turbine engine comprising:

a turbine section and an air moving section upstream of the turbine section; and

a seal between a static surface and a rotating surface in at least one of said turbine section and said air moving section;

said seal including a seal shoe which is biased at least in part by a spring force, with said spring force created by cuts formed to provide a gap to allow arms associated with said seal to provide said spring force, and the movement of said shoe being along a direction having at least a component parallel to an axis of rotation of the gas turbine engine; and

wherein the movement of said shoe is one of directly parallel to said axis of rotation, or the movement of said shoe also having a radial component, and said seal sealing on a generally conical shaped surface.

2. The gas turbine engine as set forth in claim 1 , wherein said air moving section includes one of a fan and a compressor.

3. The gas turbine engine as set forth in claim 1 , wherein said turbine section drives a fan through a gear reduction.

4. The gas turbine engine as set forth in claim 3 , wherein a gear ratio of said gear reduction is greater than or equal to about 2.4.

5. The gas turbine engine as set forth in claim 1 , wherein said movement of said shoe is directly parallel to said axis of rotation.

6. The gas turbine engine as set forth in claim 1 , wherein the movement of said show also having a radial component, and said seal sealing on a generally conical shaped surface.

7. The gas turbine engine as set forth in claim 1 wherein high pressure air is delivered into a cavity within said seal to drive said shoe toward an opposed surface.

8. The gas turbine engine as set forth in claim 7 , wherein a dynamic pressure between the seal and an opposed surface tends to bias said shoe away from said surface.

9. The gas turbine engine as set forth in claim 8 , wherein said seal is attached to said static structure, and said surface is a rotating surface that rotates with one of said air moving and turbine sections.

10. The gas turbine engine as set forth in claim 8 , wherein said shoe and said carrier are formed in segments by said gaps.

11. The gas turbine engine as set forth in claim 10 , wherein said shoes extend circumferentially, and are curved about said axis of rotation.

12. The gas turbine engine as set forth in claim 1 , wherein said shoes extend circumferentially, and are curved about said axis of rotation.

13. The gas turbine engine as set forth in claim 1 , wherein said seal is mounted to said static structure, and seals relative to said rotating surface.

14. A gas turbine engine comprising:

a turbine section, a fan and a compressor;

a seal between a static surface and a rotating surface in at least one of said turbine section, said fan and said compressor, said seal including a seal shoe which is biased forwardly and outwardly relative to a static structure at least in part by a spring force, with said spring force created by cuts formed to provide a gap to allow arms associated with said seal to provide said spring force, and the movement of said shoe being along a direction having at least a component parallel to an axis of rotation of the gas turbine engine;

said turbine section drives said fan through a gear reduction;

high pressure air is delivered into a cavity within said seal to drive said shoe toward an opposed surface, a dynamic pressure between the seals and the opposed surface tending to bias said shoe away from said surface;

said shoe extends circumferentially, and is curved about said axis of rotation; and

wherein the movement of said shoe is one of directly parallel to said axis of rotation, or the movement of said shoe also having a radial component, and said seal sealing on a generally conical shaped surface.

15. The gas turbine engine as set forth in claim 14 , wherein said movement of said shoe is directly parallel to said axis of rotation.

16. The gas turbine engine as set forth in claim 14 , wherein the movement of said shoe also having a radial component, and said seal sealing on a generally conical shaped surface.

17. The gas turbine engine as set forth in claim 14 , wherein said seal is mounted to said static structure and seals relative to said rotating surface.

18. The gas turbine engine as set forth in claim 14 , wherein a gear ratio of said gear reduction is greater than or equal to about 2.4.

19. The gas turbine engine as set forth in claim 14 , wherein said fan delivering a portion of air into a bypass duct, and a portion of air as core air flow to said compressor, with a bypass ratio being greater than or equal to about 6.

20. An axially moving non-contact seal comprising:

a seal body including a seal shoe which is biased axially forwardly and outwardly at least in part by a spring force, with said spring force created by cuts formed to provide a gap to allow arms associated with said seal to provide said spring force;

high pressure air delivered into a cavity within said seal to drive said shoe toward an opposed surface;

a dynamic pressure between the seal and the opposed surface tends to bias said shoe away from the surface;

said shoe extending circumferentially, and being curved about a central axis in a circumferential direction; and

wherein the movement of said shoe is one of directly parallel to said axis of rotation, or the movement of said shoe also having a radial component, and said seal sealing on a generally conical shaped surface.