Gas turbine engine fan blade platform seal

Abstract

A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.

What is claimed is: 
     
         1 . A fan section for a gas turbine engine comprising:
 a fan blade having an airfoil with an exterior surface; and   a platform seal adhered to the airfoil.   
     
     
         2 . The fan section according to  claim 1 , wherein the seal extends about a perimeter of the airfoil. 
     
     
         3 . The fan section according to  claim 2 , wherein the perimeter includes pressure and suction sides and leading and trailing edges. 
     
     
         4 . The fan section according to  claim 1 , wherein the seal includes a base and a flap adjoining the base, the flap is canted toward a root of the blade, which supports the airfoil. 
     
     
         5 . The fan section according to  claim 4 , wherein the seal has a generally U-shaped cross-section. 
     
     
         6 . The fan section according to  claim 4 , wherein the seal has a generally Y-shaped cross-section. 
     
     
         7 . The fan section according to  claim 6 , wherein the seal includes a notch provided between the base and flap to provide a weakened area increasing flexibility of the flap relative to the base. 
     
     
         8 . The fan section according to  claim 4 , wherein the seal is generally L-shaped. 
     
     
         9 . The fan section according to  claim 1 , wherein the seal is constructed from an elastomeric material. 
     
     
         10 . The fan section according to  claim 9 , wherein the elastomeric material is a silicone rubber. 
     
     
         11 . The fan section according to  claim 9 , comprising an epoxy securing the seal to the fan blade. 
     
     
         12 . The fan section according to  claim 9 , wherein the seal is covered in a fabric, the fabric adhered to the airfoil. 
     
     
         13 . The fan section according to  claim 1 , comprising a fan hub, and a root of the fan blade received by a slot in the fan hub, and a platform secured to the fan hub and arranged between adjacent fan blades, a seal provided on opposing sides of the fan blade and engaging the platform to provide a sealed inner flow path. 
     
     
         14 . A fan section for a gas turbine engine comprising:
 a fan hub having a slot;   a fan blade including an airfoil extending from a root to a tip, the root received in the slot;   a platform secured to the fan hub and arranged between adjacent fan blades; and   a seal having a base secured to opposing sides of the fan blade, and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.   
     
     
         15 . The fan section according to  claim 14 , wherein the seal extends about the perimeter of the airfoil. 
     
     
         16 . The fan section according to  claim 14 , wherein the seal has a generally U-shaped cross-section. 
     
     
         17 . The fan section according to  claim 14 , wherein the seal has a generally Y-shaped cross-section. 
     
     
         18 . The fan section according to  claim 14 , wherein the seal is generally L-shaped.