Segmented structural links for coupled disk frequency tuning

Abstract

A segmented structural link may comprise a base portion having a first face, a tail portion, and a distal end having a second face. The tail portion may extend at an angle relative to the first face. The tail portion may comprise a first bend and may further comprise a second bend. The base portion may comprise at least one of a captured nut, a nut plate, or a self-clinching nut.

What is claimed is: 
     
         1 . A segmented structural link, comprising:
 a hub;   a base portion having a first face;   a tail portion; and   a distal end having a second face.   
     
     
         2 . The segmented structural link of  claim 1 , wherein the tail portion extends at an angle relative to the first face. 
     
     
         3 . The segmented structural link of  claim 2 , wherein the tail portion comprises a first bend. 
     
     
         4 . The segmented structural link of  claim 3 , wherein the tail portion further comprises a second bend. 
     
     
         5 . The segmented structural link of  claim 2 , wherein the base portion further comprises at least one of a captured nut, a nut plate, or a self-clinching nut. 
     
     
         6 . The segmented structural link of  claim 2 , wherein the base portion is coupled at the first face to a first flange. 
     
     
         7 . The segmented structural link of  claim 6 , wherein the distal end is coupled at the second face to a second flange. 
     
     
         8 . The segmented structural link of  claim 7 , wherein the first flange is one of a J-flange or a scalloped flange. 
     
     
         9 . The segmented structural link of  claim 8 , wherein the second flange is a forward flange of the hub, wherein the hub further comprises a cone arm coupled to a blade ring at a web. 
     
     
         10 . The segmented structural link of  claim 9 , wherein the blade ring pivots over the cone arm about the web in response to a rotation of the hub. 
     
     
         11 . The segmented structural link of  claim 10 , wherein the first flange is coupled to the blade ring and, in response to the blade ring pivoting over the cone arm about the web, is driven toward the second flange. 
     
     
         12 . The segmented structural link of  claim 11 , wherein the segmented structural link is compressed in response to the first flange being driven toward the second flange. 
     
     
         13 . A gas turbine engine comprising:
 a fan section having a fan disk comprising a hub comprising a cone arm, a web, and a blade ring;   a compressor section configured to compress a gas;   a combustor section aft of the compressor section and configured to combust the gas;   a turbine section aft of the combustor section configured to extract energy from the gas;   and a segmented structural link wherein the segmented structural link comprises:   a base portion having a first face;   a tail portion; and   a distal end having a second face.   
     
     
         14 . The gas turbine engine of  claim 13 , wherein the tail portion extends at an angle relative to the first face. 
     
     
         15 . The gas turbine engine of  claim 14 , wherein the tail portion comprises a first bend. 
     
     
         16 . The gas turbine engine of  claim 15 , wherein the base portion is coupled at the first face to a first flange and the distal end is coupled at the second face to a second flange. 
     
     
         17 . The gas turbine engine of  claim 16 , wherein a plurality of segmented structural links are distributed symmetrically about a circumference of the fan disk. 
     
     
         18 . The gas turbine engine of  claim 16 , wherein the segmented structural link extends around a portion of a circumference of the fan disk between a J-flange and a scalloped flange. 
     
     
         19 . The gas turbine engine of  claim 16 , wherein the segmented structural link is compressed in response to the first flange being driven toward the second flange. 
     
     
         20 . A method of tuning a vibrational response of a fan disk, the method comprising:
 calculating a vibrational mode shape of the fan disk;   determining a point of maximum relative downward deflection of a blade ring of the fan disk; and   coupling a segmented structural link to the fan disk at the point of maximum relative downward deflection between a first flange and a second flange.