Hole for rotating component cooling system

Abstract

A rotor for a gas turbine engine comprises an annular body and a plurality of holes. The annular body is configured to rotate in a circumferential direction about an axis extending through a center of the annular body. The annular body comprises an outer diameter surface and an inner diameter surface. The plurality of holes extends through the annular body. Each of the holes comprises an elongate profile in the circumferential direction, and a side wall extending between the outer diameter surface and the inner diameter surface. The side wall is slanted in the circumferential direction.

1 . A rotor for a gas turbine engine, the rotor comprising:
 an annular body configured to rotate in a circumferential direction about an axis extending through a center of the annular body, the annular body comprising:
 an outer diameter surface; and 
 an inner diameter surface; and 
   a plurality of holes extending through the annular body, each of the holes comprising:
 an elongate profile in the circumferential direction; and 
 a side wall extending between the outer diameter surface and the inner diameter surface, the side wall being slanted in the circumferential direction. 
   
     
     
         2 . The rotor of  claim 1  wherein the elongate profile of each of the plurality of holes is racetrack shaped. 
     
     
         3 . The rotor of  claim 2  wherein the elongate profile of each of the plurality of holes includes a width in the circumferential direction that is approximately twice as large as a length in the axial direction. 
     
     
         4 . The rotor of  claim 1  wherein the side wall of each of the plurality of holes includes arcuate leading and trailing edge segments that are angled in the circumferential direction with respect to a radial direction. 
     
     
         5 . The rotor of  claim 4  wherein the side walls are angled between approximately fifteen degrees and approximately seventy-five degrees. 
     
     
         6 . The rotor of  claim 4  wherein the side walls are angled between approximately thirty degrees and approximately forty degrees. 
     
     
         7 . The rotor of  claim 1  wherein the elongate profile of each of the plurality of holes comprises:
 an arcuate leading edge; 
 an arcuate trailing edge; 
 a first side edge extending straight between the arcuate leading and trailing edges; and 
 a second side edge extending straight between the arcuate leading and trailing edges. 
 
     
     
         8 . The rotor of  claim 7  wherein the first side edge and the second side edge are parallel to each other. 
     
     
         9 . The rotor of  claim 7  wherein the arcuate leading edge and the arcuate trailing edge are circular. 
     
     
         10 . The rotor of  claim 7  wherein the arcuate leading edge and the arcuate trailing edge extend straight between the inner diameter surface and the outer diameter surface. 
     
     
         11 . The rotor of  claim 7  wherein the arcuate leading edge and the arcuate trailing edge are extend arcuately between the inner diameter surface and the outer diameter surface. 
     
     
         12 . The rotor of  claim 7  wherein the arcuate leading edge and the arcuate trailing edge are angled in the circumferential direction with respect to a radial direction. 
     
     
         13 . The rotor of  claim 1  wherein the plurality of holes is arranged in a circumferential row spaced evenly about the outer diameter surface. 
     
     
         14 . The rotor of  claim 1  wherein the plurality of holes increases the swirl ratio across the annular body while decreasing pressure loss when the annular body is rotating. 
     
     
         15 . The rotor of  claim 1  wherein the rotor further comprises:
 a disk comprising:
 an outer diameter edge having slots for receiving airfoils; and 
 an inner diameter bore surrounding the axis; and 
 
 a hub extending from the inner diameter bore of the disk to form the annular body, the plurality of holes being positioned on the hub. 
 
     
     
         16 . The rotor of  claim 15  and further comprising a mini-disk disposed opposite the outer diameter surface to form a cooling channel, the mini-disk comprising:
 an axially extending portion extending opposite the hub; and 
 a radially extending portion extending along the disk; 
 wherein cooling air directed into the hole from the inner diameter surface flows along the hub and along the disk to the slots. 
 
     
     
         17 . The rotor of  claim 16  wherein the mini-disk further comprises:
 a lap joint coupling the axially extending portion to the hub; and 
 a face seal adjoining the radially extending portion with the slots of the outer diameter edge of the disk. 
 
     
     
         18 . A rotor for a gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the rotor, the rotor comprising:
 a disk comprising:
 an outer diameter edge having slots for receiving airfoils; and 
 an inner diameter bore surrounding the axis; 
   a hub extending from the inner diameter bore of the disk to form an annular body;   a plurality of holes extending through the hub, each of the plurality of holes comprising:
 an arcuate leading edge; 
 an arcuate trailing edge; 
 first and second elongate side edges extending between the arcuate leading and trailing edges; 
 wherein the first and second elongate side edges are parallel; and 
 wherein the arcuate leading edge and the arcuate trailing edge are angled with respect to a radial direction. 
   
     
     
         19 . The rotor of  claim 18  wherein:
 the arcuate leading edge and arcuate trailing edge define a width that is approximately twice as large as a distance between the first and second elongate side edges; and 
 the arcuate leading edge and the arcuate trailing edge are angled approximately fifteen to approximately seventy-five degrees. 
 
     
     
         20 . The rotor of  claim 18  wherein the plurality of holes is arranged in a circumferential row spaced evenly about the hub. 
     
     
         21 . The rotor of  claim 18  wherein the plurality of holes increases the swirl ratio across the hub while decreasing pressure loss when the rotor is rotating about the axis. 
     
     
         22 . The rotor of  claim 18  and further comprising a mini-disk disposed opposite the rotor to form a cooling channel therebetween, the mini-disk comprising:
 an axially extending portion extending opposite the hub; and 
 a radially extending portion extending along the disk; 
 wherein cooling air directed into the hole from the inner diameter surface flows along the hub and along the disk to the slots. 
 
     
     
         23 . The rotor of  claim 18  wherein the arcuate leading edge and the arcuate trailing edge are contoured radially as they pass through the hub. 
     
     
         24 . A method of passing flowing cooling air through a rotating annular body, the method comprising:
 rotating an annular body about an axis in a circumferential direction;   passing cooling air through the annular body in an axial direction;   turning the cooling air in a radial direction to pass through a plurality of holes in the annular body that are wider in the circumferential direction than in the axial direction; and   bending the cooling air in a circumferential direction by passing over angled walls of the plurality of holes.   
     
     
         25 . The method of  claim 24  wherein:
 the holes are angled into the direction of rotation approximately thirty to approximately forty degrees; and 
 each of the cooling holes has a racetrack shape profile. 
 
     
     
         26 . The method of  claim 25  wherein turning and bending of the cooling air with the plurality of holes increases the swirl ratio across the annular body and decreases pressure loss with respect to holes having circular profiles and un-angled walls.