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US 7,094,033 B2Granted
Methods and apparatus for assembling gas turbine engines
AssigneeGeneral Electric Company
InventorsGerald Alexander Pauley, Brian Paul Overbeck
Life of this patent
Estimating the term…
Abstract
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.
Claims15
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.
1 more element
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.
Dependencies are inferred from the claim text.