Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine

Abstract

A gas turbine fan fairing platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.

1 . A gas turbine fan fairing platform comprising at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade. 
     
     
         2 . The gas turbine fan fairing platform of  claim 1 , wherein the at least one body is two bodies each having an opening such that the two bodies can attach to one another and the openings form a continuous border that surrounds the blade. 
     
     
         3 . The gas turbine fan fairing platform of  claim 1 , wherein the two bodies are detachable from one another to allow them to be replaced. 
     
     
         4 . The gas turbine fan fairing platform of  claim 1 , wherein the protrusion has a curved surface that blends into the surface of the at least one body. 
     
     
         5 . The gas turbine fan fairing platform of  claim 1 , wherein the protrusion serves as a fairing for the blade. 
     
     
         6 . The gas turbine fan fairing platform of  claim 1 , wherein the at least one body is made of at least one of a composite, a polymeric material, and a metal. 
     
     
         7 . The gas turbine fan fairing platform of  claim 1 , wherein the material of the body is more resilient than that of the blade. 
     
     
         8 . The gas turbine fan fairing platform of  claim 1 , wherein the at least one body seals to the blade. 
     
     
         9 . The gas turbine fan fairing platform of  claim 1 , wherein the protrusion improves aerodynamic flow at the root leading edge of the blade in comparison to a platform that does not include the protrusion. 
     
     
         10 . The gas turbine fan fairing platform of  claim 9 , wherein the improved aerodynamics allows the root leading edge of the blade to be thicker without sacrificing performance of a gas turbine engine employing the gas turbine fan fairing platform. 
     
     
         11 . The gas turbine fan fairing platform of  claim 1 , wherein the protrusion protects the root leading edge of the blade from being contacted directly with a foreign body. 
     
     
         12 . A method of fairing a root leading edge of a fan blade of a gas turbine engine, comprising positioning a platform having a protrusion near an opening in at least one body of the platform such that the protrusion is adjacent a root leading edge of the fan blade. 
     
     
         13 . The method of fairing a root leading edge of a fan blade of a gas turbine engine of  claim 12 , further comprising sealing the platform to the fan blade. 
     
     
         14 . The method of fairing a root leading edge of a fan blade of a gas turbine engine of  claim 12 , further comprising isolating the root leading edge of the fan blade from being struck by objects directly.