Patent ID: 7614848
Filing Date: 2009-11-10
Classification: B23P,F01D,F04D,Y02T,Y10T

Abstract:
1. A replacement fan exit guide vane assembly for installation between an inner case and an outer case of a gas turbine engine, the assembly comprising: an airfoil structure having an outer end and an inner end; a wedge structure connected to the outer end of the airfoil structure; a base plate configured to be positioned between the outer end of the airfoil structure and the outer case; a slip collar having an opening therethrough and a recess formed along the opening, wherein the airfoil structure is positioned to extend through the opening, and wherein the recess is configured to accept the wedge structure to create an interference fit between the slip collar and the base plate; and a conformable material disposed along the opening and the recess in the slip collar and also along the base plate in order to provide dampening relative to the airfoil structure and the wedge structure.