Gas turbine case and reinforcement strut for same

Abstract

A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components. A stress dissipation mass projecting from a continuous surface of at least one of the struts at the intersection with a corresponding annular case component, the stress absorption mass being on either side of a plane passing through the radial axis of the strut and the central axis of the corresponding annular case component. A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine is also provided.

1 . A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine comprising:
 determining a location of substantial thermal and mechanical stresses,   determining a volume of mass required to dissipate the thermal and mechanical stresses at the location, and   forming a discrete mass on the strut protruding from a continuous surface of the strut, at the determined location on either side of the strut.   
     
     
         2 . The method as defined in  claim 1 , wherein forming the discrete mass comprises machining the discrete mass from material native to strut. 
     
     
         3 . The method as defined in  claim 1 , wherein forming the discrete mass comprises forming the discrete mass at an intersection of the strut and an annular radial component.