Gas turbine engine compressor undercut spacer

Abstract

A gas turbine engine compressor spacer ( 230 ) includes a body ( 229 ) with a hollow cylinder shape. The body ( 229 ) includes an outer surface ( 232 ) with an axially forward end. The body ( 229 ) also includes a forward face ( 233 ) extending radially inward from the axially forward end. A forward lip ( 237 ) extends axially from the body ( 229 ). The forward lip ( 237 ) includes a forward lip surface ( 239 ) located radially inward from the forward face ( 233 ). The forward lip surface ( 239 ) is the radially outer circumferential surface of the forward lip ( 237 ). The spacer ( 230 ) also includes a forward undercut ( 235 ). The forward undercut ( 235 ) is located between the forward face ( 233 ) and the forward lip surface ( 239 ).

What is claimed is: 
     
         1 . A gas turbine engine compressor spacer ring configured for mounting between compressor rotor disks, comprising:
 a body with a hollow cylinder shape, the body having
 an outer surface, the outer surface being a radially outermost circumferential surface of the body, the outer surface including
 an axially forward end, and 
 an axially aft end, and 
 
 a forward face extending radially inward from the axially forward end of the outer surface; 
   a forward lip extending axially from the body, the forward lip having
 a forward lip surface located radially inward from the forward face, wherein the forward lip surface is the radially outer circumferential surface of the forward lip; and 
   a forward undercut, the forward undercut located between the forward face and the forward lip surface.   
     
     
         2 . The spacer of  claim 1 , wherein the forward undercut includes a curved profile. 
     
     
         3 . The spacer of  claim 2 , wherein the curved profile of the forward undercut comprises multiple radii including a first radius and a second radius. 
     
     
         4 . The spacer of  claim 1 , wherein the forward undercut has a height between 0.20 inches and 0.30 inches. 
     
     
         5 . The spacer of  claim 1 , wherein the ratio between a height of the forward undercut and a thickness of a forward end of the spacer is between forty percent and fifty percent. 
     
     
         6 . The spacer of  claim 1 , further comprising:
 the body having an aft face extending radially inward from the axially aft end of the outer surface, distal to the forward face;   an aft lip extending axially aft from the body, distal to the forward lip and located radially inward from the aft face, the aft lip having
 an aft lip surface, the aft lip surface being the radially outer circumferential surface of the aft lip; 
   an aft undercut located between the aft face and the aft lip surface, the aft undercut having a curved profile.   
     
     
         7 . The spacer of  claim 6 , wherein a ratio between a height of the forward undercut and a thickness of a forward end of the spacer is between forty percent and fifty percent and a ratio between a height of the aft undercut and a thickness of an aft end of the spacer is between five percent and fifteen percent. 
     
     
         8 . The spacer of  claim 6 , wherein a ratio between a height of the aft undercut and the forward undercut is between ten percent and twenty percent. 
     
     
         9 . The spacer of  claim 8 , wherein the ratio between a height of the aft undercut and the forward undercut is between sixteen percent and seventeen percent. 
     
     
         10 . The spacer of  claim 1 , further comprising a thickened portion extending radially inward from an axially forward portion of the body, wherein a portion of the forward lip extends from the thickened portion. 
     
     
         11 . The spacer of  claim 1 , wherein the forward face, the forward lip, and the forward undercut circumferentially extend completely around the spacer. 
     
     
         12 . The spacer of  claim 1 , wherein the spacer comprises incoloy 901. 
     
     
         13 . A gas turbine engine compressor spacer ring configured for mounting between compressor rotor disks, comprising:
 a body with an annular ring shape, the body having
 an outer surface, the outer surface being the radially outermost circumferential surface of the body, the outer surface including
 an axially forward end, and 
 an axially aft end 
 
 an aft face extending radially inward from the axially aft end of the outer surface, and 
   an aft lip extending axially aft from the body and located radially inward from the aft face, the aft lip having
 an aft lip surface, the aft lip surface being the radially outer circumferential surface of the aft lip; and 
   an aft undercut located between the aft face and the aft lip surface, the aft undercut having a curved profile.   
     
     
         14 . The spacer of  claim 13 , wherein a ratio between a height of the aft undercut and a thickness of an aft end of the spacer is between five percent and fifteen percent. 
     
     
         15 . The spacer of  claim 11 , the aft face, the aft lip, and the aft undercut circumferentially extend completely around the spacer. 
     
     
         16 . A compressor of a gas turbine engine, comprising:
 a first compressor rotor disk and a second compressor rotor disk, each having
 a rim located at a radially outer circumference of the compressor rotor disk, the rim including
 a forward extension extending axially forward, and 
 an aft extension extending axially aft, 
 
 a forward arm extending axially forward, wherein the forward arm is located radially inward from the rim, and 
 an aft arm extending axially aft, wherein the aft arm is located radially inward from the rim, 
 wherein the forward arm of the first compressor rotor disk radially aligns with and couples to the aft arm of the second compressor rotor disk, the second compressor rotor disk being located axially forward of and adjacent to the first compressor rotor disk; and 
   a spacer is between the rim of the first compressor rotor disk and the rim of the second compressor rotor disk, the spacer having
 a body with a hollow cylinder shape, the body including
 an outer surface, the outer surface being the radially outermost circumferential surface of the body, the outer surface including
 an axially forward end, and 
 an axially aft end, 
 
 a forward face, the forward face extending radially inward from the axially forward end of the outer surface, 
 an aft face, the aft face extending radially inward from the axially aft end of the outer surface, distal to the forward face, and 
 an axially forward portion, 
 
 a thickened portion extending radially inward from the axially forward portion of the body, 
 a forward lip extending axially forward from the thickened portion and the body, the forward lip having
 a forward lip surface located radially inward from the forward face, wherein the forward lip surface is the radially outer circumferential surface of the forward lip, 
 
 an aft lip extending axially aft from the body, distal to the forward lip, the aft lip having
 an aft lip surface located radially inward from the aft face, wherein the aft lip surface is the radially outer circumferential surface of the aft lip, 
 
 a forward undercut, the forward undercut located between the forward face and the forward lip surface, and 
 an aft undercut, the aft undercut being located between the aft face and the aft lip surface; 
   a rear hub having a hub arm extending axially forward, wherein the hub arm radially aligns with and couples to the aft arm of a compressor rotor disk.   
     
     
         17 . The compressor of  claim 16 , wherein the spacer is installed with a radial interference fit with the first compressor rotor disk. 
     
     
         18 . The compressor of  claim 17 , wherein a maximum radial interference between the spacer and the first compressor rotor disk is between 0.010″ to 0.014″. 
     
     
         19 . The compressor of  claim 18 , wherein the maximum radial interference between the spacer and the first compressor rotor disk is 0.012″. 
     
     
         20 . The compressor of  claim 17 , wherein the spacer is installed with a slip fit with a second compressor rotor disk.