Turbine engine case attachment and a method of using the same

Abstract

The present disclosure relates generally to a turbine engine case assembly, the turbine engine case assembly including a fan case including an outer frame encircling an axis, the outer frame including an outer frame exterior surface and an outer frame interior surface, at least two mounts disposed on the outer frame exterior surface, wherein the at least two mounts are circumferentially spaced along the outer frame exterior surface, and a compliant attachment device operably coupled to the at least two mounts.

What is claimed is: 
     
         1 . A method of reducing load transfer from a turbine engine case to a portion of an airframe, the method comprising:
 securing a compliant attachment device to the turbine engine case to create a turbine engine case assembly; and   securing the turbine engine case assembly to the portion of the airframe.   
     
     
         2 . The method of  claim 1 , wherein the turbine engine case comprises:
 an outer frame encircling an axis, the outer frame including an outer frame exterior surface and an outer frame interior surface;   at least two mounts disposed on the outer frame exterior surface, wherein the at least two mounts are circumferentially spaced along the outer frame exterior surface.   
     
     
         3 . The method of  claim 2 , wherein securing the compliant attachment device to the turbine engine case comprises:
 coupling the compliant attachment device between the at least two mounts disposed on the outer frame exterior surface of the outer frame.   
     
     
         4 . The method of  claim 1 , wherein the compliant attachment device comprises a spring. 
     
     
         5 . The method of  claim 4 , wherein the spring is a leaf spring. 
     
     
         6 . The method of  claim 1 , wherein the compliant attachment device is frangible. 
     
     
         7 . The method of  claim 2  wherein the turbine engine case assembly further comprises:
 a center frame encircling the axis, wherein the center frame is positioned radially inward from the outer frame; and 
 a plurality of struts, each coupled at a first end to the center frame, and at a second end to the outer frame interior surface. 
 
     
     
         8 . A method of reducing load transfer from a turbine engine case to a portion of an airframe of a gas turbine engine, the method comprising:
 securing a compliant attachment device to the turbine engine case to create a turbine engine case assembly; and   securing the turbine engine case assembly to the portion of the airframe, wherein the gas turbine engine comprises: a fan section; a low pressure compressor; and the turbine engine case assembly is disposed aft the fan section; and
 wherein the turbine engine case assembly comprises: 
 an outer frame encircling an axis, the outer frame including an outer frame exterior surface and an outer frame interior surface; 
 at least two mounts operably coupled to the outer frame exterior surface, wherein the at least two mounts are circumferentially spaced along the outer frame exterior surface; and 
 the compliant attachment device is operably coupled to the at least two mounts. 
   
     
     
         9 . The method of  claim 8 , wherein the compliant attachment device comprises a spring. 
     
     
         10 . The method of  claim 9 , wherein the spring is a leaf spring. 
     
     
         11 . The method of  claim 8 , wherein the compliant attachment device is frangible. 
     
     
         12 . The method of  claim 8 , wherein the turbine engine case assembly further comprises:
 a center frame encircling the axis, wherein the center frame is positioned radially inward from the outer frame; and   a plurality of struts, each coupled at a first end to the center frame, and at a second end to the outer frame interior surface.