System and method for controlling backbone bending in a gas turbine engine

Abstract

A flexible coupling for a gas turbine engine includes a fan hub frame having a first flange and a core engine having a second flange. The first flange includes a first plurality of fingers extending from a face of the flange and the second flange includes a second plurality of fingers extending from a face of the second flange. The second plurality of fingers of the second flange is complementary to the first plurality of fingers extending from the first flange. The first flange and the second flange are coupled together in form-fitting engagement such that the first plurality of fingers and the second plurality of fingers form an interdigitated configuration.

What is claimed is:  
     
         1 . A flexible coupling system for a turbine engine comprising:
 a fan hub frame comprising a first flange comprising a first plurality of fingers extending therefrom; and   a core engine comprising a second flange comprising a second plurality of fingers extending therefrom and complementary to said first plurality of fingers, wherein said first flange and said second flange are configured to couple together in form-fitting engagement, such that said first plurality of fingers and said second plurality of fingers form an interdigitated configuration.   
     
     
         2 . The flexible coupling system of  claim 1  further comprising a sealing member positioned between said fan hub frame and said core engine, said sealing member configured to regulate a predetermined flow rate of a process fluid between said first flange and said second flange. 
     
     
         3 . The flexible coupling system of  claim 1  further comprising a flange coupling member extending at least partially about a periphery of said first flange and a periphery of said second flange, said flange coupling member comprising a compliant element between said flange coupling member and at least one of said first flange and said second flange. 
     
     
         4 . The flexible coupling system of  claim 3 , wherein said flange coupling member is configured to couple said first flange and said second flange together in form-fitting engagement, said first flange and said second flange configured to facilitate limiting relative axial rotation between said fan hub frame and said core engine. 
     
     
         5 . The flexible coupling system of  claim 3 , wherein said compliant element is configured to facilitate a predetermined value of an angular displacement between said fan hub frame and said core engine. 
     
     
         6 . The flexible coupling system of  claim 3 , wherein said compliant element is configured to regulate a predetermined flow rate of a process fluid between said first flange and said second flange. 
     
     
         7 . The flexible coupling system of  claim 1 , wherein said core engine further comprises a bearing structure coupled to said core engine. 
     
     
         8 . A turbine engine assembly comprising:
 a nacelle;   a fan assembly coupled to said nacelle and comprising:
 an array of fan blades; and 
 a fan hub frame comprising a first flange comprising a first plurality of fingers extending therefrom; and 
   a core engine comprising:
 a second flange comprising a second plurality of fingers extending therefrom and complementary to said first plurality of fingers, wherein said first flange and said second flange are configured to couple together in form-fitting engagement, such that said first plurality of fingers and said second plurality of fingers form an interdigitated configuration, wherein an applied aerodynamic load acting on said fan assembly is at least partially transmitted to said nacelle. 
   
     
     
         9 . The engine assembly of  claim 8 , wherein said fan assembly further comprises a fan case and a plurality of outlet guide vanes extending between said fan hub frame and said fan case. 
     
     
         10 . The engine assembly of  claim 9 , wherein said fan hub frame is configured to transmit the applied aerodynamic load through said outlet guide vanes to said fan case. 
     
     
         11 . The engine assembly of  claim 8  further comprising a sealing member positioned between said fan assembly and said core engine, said sealing member configured to regulate a predetermined flow rate of a process fluid between said first flange and said second flange. 
     
     
         12 . The engine assembly of  claim 8  further comprising a flange coupling member extending at least partially about a periphery of said first flange and a periphery of said second flange, said flange coupling member comprising a compliant element between said flange coupling member and at least one of said first flange and said second flange. 
     
     
         13 . The engine assembly of  claim 12 , wherein said flange coupling member is configured to couple said first flange and said second flange together in form-fitting engagement, said first flange and said second flange configured to facilitate limiting relative axial rotation between said fan hub frame and said core engine. 
     
     
         14 . The engine assembly of  claim 12 , wherein said compliant element is configured to facilitate a predetermined value of an angular displacement between said fan assembly and said core engine. 
     
     
         15 . The engine assembly of  claim 12 , wherein said compliant element is configured to regulate a predetermined flow rate of a process fluid between said first flange and said second flange. 
     
     
         16 . The engine assembly of  claim 8 , wherein said core engine further comprises a bearing structure coupled to said core engine. 
     
     
         17 . A method of controlling backbone bending of a gas turbine engine, said method comprising:
 coupling a first plurality of fingers to a first flange of a fan hub frame having a first longitudinal axis, wherein the first plurality of fingers extend axially therefrom;   coupling a second plurality of fingers to a second flange of a core engine having a second longitudinal axis, wherein the second plurality of fingers extend axially therefrom complementary to the first plurality of fingers;   non-rigidly coupling the first flange and the second flange together in form-fitting engagement, such that the first plurality of fingers and the second plurality of fingers form an interdigitated configuration, wherein the first longitudinal axis and the second longitudinal axis are substantially coaxial; and   applying an aerodynamic load to the fan hub frame such that the fan hub frame is displaced an angular value with respect to the second longitudinal axis.   
     
     
         18 . The method of  claim 17  further comprising coupling a sealing member between the fan hub frame and the core engine to regulate a predetermined flow rate of a process fluid between the first flange and the second flange. 
     
     
         19 . The method of  claim 17 , wherein non-rigidly coupling the first flange to the second flange comprises non-rigidly coupling the first flange to the second flange with a flange coupling member, wherein the first flange has a first periphery and the second flange has a second periphery, the flange coupling member extending at least partially about the first periphery and the second periphery of the first flange and the second flange respectively, wherein the flange coupling member includes a compliant element between the flange coupling member and at least one of the first flange and the second flange. 
     
     
         20 . The method of  claim 17 , wherein coupling a second plurality of fingers to a second flange of a core engine includes coupling a second plurality of fingers to a second flange of a core engine including a bearing structure coupled to the core engine.