Panel for supporting abradable material in a turbomachine

1. A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure carrying a layer of abradable material, the laminated structure comprising sheets of fibers embedded in a polymer, wherein the laminated structure comprises a first or upstream portion covered by the abradable material and a second or downstream portion that extends beyond the abradable material, a thickness of the downstream portion being greater than a thickness of the upstream portion and being capable of withstanding ice impacts.

2. A panel according to claim 1 , wherein the upstream portion of the laminated structure is of constant thickness over a major fraction of its length and is connected to the downstream portion by a zone of thickness that increases progressively going downstream.

3. A panel according to claim 2 , wherein the upstream portion of constant thickness extends over about two-thirds of the axial extent of the abradable material.

4. A panel according to claim 1 , wherein the rigid support is of cellular structure.

5. A panel according to claim 4 , wherein the rigid support comprises two superposed layers of cellular structure, separated by a plate.

6. A panel according to claim 4 , wherein cells carrying the downstream portion of the laminated structure are of smaller section than cells carrying the upstream portion of the laminated structure.

7. A panel according to claim 4 , wherein cells at the upstream and downstream ends of the support are closed by a layer of polymer foam.

8. A panel according to claim 1 , wherein the rigid support is of honeycomb structure.

9. A panel according to claim 1 , wherein the upstream portion of the laminated structure comprises a stack of four to seven sheets of fibers.

10. A panel according to claim 1 , wherein the downstream portion of the laminated structure comprises a stack of 11 to 18 sheets of fibers.

11. A panel according to claim 1 , wherein the sheets of fibers are sheets of glass fibers embedded in an epoxy resin.

12. A panel according to claim 1 , in a form of a cylindrical or conical sector.

13. A turbojet nacelle, including panels according to claim 1 for supporting abradable material.

14. A nacelle according to claim 13 , including four to six panels mounted end to end.

15. An airplane turbojet, including panels according to claim 1 for supporting abradable material, the panels being disposed in register with blades of a fan in such a manner that the downstream portions of the laminated structures of said panels extend downstream from the fan blades as far as soundproofing panels.