Split case structure for a gas turbine engine

Abstract

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a plurality of walls and a plurality of case segments. Each of the walls extends axially along and circumferentially about an axial centerline. The walls include a first wall and a second wall radially outboard of and axially overlapping the first wall. Each of the case segments is configured to form a respective portion of the first wall and a respective portion of the second wall. The case segments include a first case segment and a second case segment circumferentially adjacent and attached to the first case segment at a joint.

What is claimed is: 
     
         1 . An assembly for a gas turbine engine, comprising:
 a split case structure including a plurality of walls and a plurality of case segments;   each of the plurality of walls extending axially along and circumferentially about an axial centerline, and the plurality of walls including a first wall and a second wall radially outboard of and axially overlapping the first wall; and   each of the plurality of case segments configured to form a respective portion of the first wall and a respective portion of the second wall, and the plurality of case segments including a first case segment and a second case segment circumferentially adjacent and attached to the first case segment at a joint.   
     
     
         2 . The assembly of  claim 1 , wherein each of the plurality of case segments is configured as a monolithic body. 
     
     
         3 . The assembly of  claim 1 , wherein one of the plurality of walls comprises a diffuser wall. 
     
     
         4 . The assembly of  claim 1 , wherein one of the plurality of walls comprises a combustor wall. 
     
     
         5 . The assembly of  claim 1 , wherein one of the plurality of walls comprises a compressor wall. 
     
     
         6 . The assembly of  claim 1 , wherein one of the plurality of walls comprises a turbine wall. 
     
     
         7 . The assembly of  claim 1 , wherein the first case segment includes a support member that extends between and connects the first wall to the second wall. 
     
     
         8 . The assembly of  claim 1 , wherein
 the first case segment includes a channel; and   the second case segment includes a seal element inserted within the channel to seal an interface between the first case segment and the second case segment at the joint.   
     
     
         9 . The assembly of  claim 1 , wherein the split case structure further includes a seal element arranged between and engaged with the first case segment and the second case segment to seal an interface between the first case segment and the second case segment at the joint. 
     
     
         10 . The assembly of  claim 1 , wherein the first case segment includes a crush seal element configured to engage the second case segment to seal an interface between the first case segment and the second case segment at the joint. 
     
     
         11 . The assembly of  claim 1 , wherein
 the split case structure forms a compressor section inlet and a turbine section outlet; and   each of the plurality of case segments extends axially along the axial centerline from the compressor section inlet to the turbine section outlet.   
     
     
         12 . An assembly for a gas turbine engine, comprising:
 a split case structure for the gas turbine engine, the split case structure including a compressor wall, a combustor wall, a turbine wall and a plurality of case segments;   each of the plurality of case segments configured to form a respective portion of the compressor wall, a respective portion of the combustor wall and a respective portion of the turbine wall.   
     
     
         13 . The assembly of  claim 12 , wherein the plurality of case segments includes a first case segment and a second case segment circumferentially adjacent and attached to the first segment at an axially extending joint. 
     
     
         14 . The assembly of  claim 12 , wherein at least one of
 each of the plurality of case segments forms a respective portion of an inlet to a compressor section of the gas turbine engine; or   each of the plurality of case segments forms a respective portion of an outlet from a turbine section of the gas turbine engine.   
     
     
         15 . The assembly of  claim 12 , wherein
 the split case structure includes a first wall and a second wall radially outboard of and axially overlapping the first wall; and   each of the plurality of case segments is configured to form a respective portion of the first wall and a respective portion of the second wall.