Bypass lip seal

Abstract

A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided.

1 . A seal assembly for a gas turbine engine bypass duct cooler, said assembly comprising:
 a bypass duct cooler having a peripheral recess;   a body having an opening, said opening bounded by a peripheral flange arranged angularly to a surface of said body, said recess and flange being configured such that said flange is receivable within said recess; and   a seal disposed within said recess substantially continuously around the periphery, said seal adapted to sealingly engage said flange when said recess is mated with said flange.   
     
     
         2 . The assembly as defined in  claim 1 , wherein said cover means includes a peripheral groove for receiving said secondary seal. 
     
     
         3 . The assembly as defined in  claim 1 , wherein said seal includes a groove having a V-shaped profile.