초록 ▼

A method for assembling a fan platform for a gas turbine engine is provided. The method includes determining an area of vulnerability to impact and erosion damage across the platform, forming a sheet of cladding metal to substantially conform to a contour of the identified area of vulnerability of t

A method for assembling a fan platform for a gas turbine engine is provided. The method includes determining an area of vulnerability to impact and erosion damage across the platform, forming a sheet of cladding metal to substantially conform to a contour of the identified area of vulnerability of the platform, and bonding the cladding metal to the identified area of vulnerability.

대표청구항 ▼

What is claimed is: 1. A fan platform for a gas turbine engine, said platform comprising: a body portion; a flow path surface coupled to said body portion, said body portion and said flow path surface defining at least a portion of a flow path extending through the engine; and an impact barrier rei

What is claimed is: 1. A fan platform for a gas turbine engine, said platform comprising: a body portion; a flow path surface coupled to said body portion, said body portion and said flow path surface defining at least a portion of a flow path extending through the engine; and an impact barrier reinforcing said flow path surface, said impact barrier comprising a layer of cladding metal having a contour that substantially conforms to a contour of a portion of said flow path surface, said impact barrier is bonded to said flow path surface. 2. A fan platform in accordance with claim 1 wherein said body and said flow path surface are each fabricated from a composite material. 3. A fan platform in accordance with claim 2 wherein said body and said flow path surface are each fabricated from a composite material that includes carbon fiber. 4. A fan platform in accordance with claim 1 wherein said cladding metal comprises aluminum. 5. A fan platform in accordance with claim 4 wherein said cladding metal has a thickness of about twenty thousandths inches. 6. A fan platform in accordance with claim 1 wherein said cladding metal comprises an anodized coating. 7. A fan platform in accordance with claim 1 wherein said cladding metal is etched. 8. A fan platform in accordance with claim 1 wherein said cladding metal is bonded to said flow path surface with an adhesive. 9. A gas turbine engine comprising: a fan comprising a plurality of circumferentially-spaced fan blades; and a fan platform extending between a pair of circumferentially-adjacent fan blades and defining a fan flow path therebetween, said platform comprising a flow path surface, a portion of said flow path surface comprising a layer of cladding metal bonded thereto, said cladding metal having a contour that substantially conforms to a contour of said flow path surface. 10. An engine in accordance with claim 9 wherein said fan platform is fabricated from a composite material. 11. An engine in accordance with claim 9 wherein said fan platform is fabricated from a composite material that includes carbon fiber. 12. An engine in accordance with claim 9 wherein said cladding metal comprises aluminum. 13. An engine in accordance with claim 12 wherein said cladding metal has a thickness of about twenty thousandths inches. 14. An engine in accordance with claim 9 wherein said cladding metal comprises an anodized coating. 15. An engine in accordance with claim 9 wherein said cladding metal is etched.