Vortex reducing device for a gas turbine engine

Abstract

A gas turbine engine has a vortex reducing device therein that includes a retainer and paddles. The retainer is arcuate in shape and has a plurality of circumferentially spaced slots that extend through it. The paddles are circumferentially spaced about the retainer and extend outward thereform. Each paddle is disposed between adjacent slots.

1 . A vortex reducing device for a gas turbine engine, comprising:
 an arcuate retainer with a plurality of circumferentially spaced slots extending therethrough; and   a plurality of paddles circumferentially spaced about the retainer to extend outward therefrom, each paddle is disposed between adjacent slots.   
     
     
         2 . The device of  claim 1 , wherein the retainer comprises a ring extending 360° about an axis of symmetry and the paddle extends from the retainer radially outward away from the axis of symmetry of the retainer, and wherein the plurality of slots allow for passage of air to a bore of the gas turbine engine. 
     
     
         3 . The device of  claim 1 , wherein the paddle is electron beam, inertia bond, or friction welded to the retainer. 
     
     
         4 . The device of  claim 1 , wherein an outward extending main body portion of the paddle has a semi-circular cross-sectional shape. 
     
     
         5 . The device of  claim 4 , wherein the paddle defines or is disposed adjacent to an aperture that extends through the retainer or paddle. 
     
     
         6 . The device of  claim 4 , wherein the paddle extends through an aperture in the retainer and has a base that is larger than the aperture. 
     
     
         7 . The device of  claim 6 , further comprising a snap ring that connects to the retainer to prevent the paddle from rotating. 
     
     
         8 . The device of  claim 1 , wherein an outward extending main body portion of the paddle has a flat cross-sectional shape. 
     
     
         9 . A vortex reducing device assembled within compressor of a gas turbine engine, the assembly comprising:
 a first disk and a second disk, each disk extending from adjacent core flowpath into a bore of the gas turbine engine and forming a compressor disk interspace therebetween, the first disk having a tab projection on a middle portion thereof;   an arcuate retainer with a plurality of circumferentially spaced slots extending therethrough; and   a plurality of paddles circumferentially spaced about the retainer to extend outward therefrom, each paddle is disposed between adjacent slots.   
     
     
         10 . The assembly of  claim 9 , wherein the retainer has a groove that is adapted to be snap fit into the tab projection. 
     
     
         11 . The assembly of  claim 9 , wherein the paddle rotates with the first disk and a bleed air from the core flowpath passes through the first slot and the second slot to the bore of the gas turbine engine. 
     
     
         12 . The assembly of  claim 9 , wherein the retainer comprises a ring that is disposed about a centerline of the gas turbine engine and the paddle extends from the retainer outward away from the centerline within the compressor disk interspace. 
     
     
         13 . The assembly of  claim 9 , wherein an outward extending main body portion of the paddle has a semi-circular cross-sectional shape. 
     
     
         14 . The assembly of  claim 13 , wherein the paddle defines or is disposed adjacent to an aperture that extends through the retainer or paddle. 
     
     
         15 . The assembly of  claim 9 , wherein an outward extending main body portion of the paddle has a flat cross-sectional shape. 
     
     
         16 . A rotor portion of a high pressure compressor for a gas turbine engine, comprising:
 a plurality of blades disposed within a core flowpath of the gas turbine engine;   a plurality of disks, each disk connected to one of the plurality of blades and extending from the blade into a bore of the gas turbine engine;   a retainer connected at least one of the plurality of disks and having a plurality of circumferentially spaced slots extending therethrough; and   a plurality of paddles circumferentially spaced about the retainer to extend outward therefrom, each paddle is disposed between adjacent slots;   wherein the paddle rotates with the at least one of the plurality of disks and a bleed air from the core flowpath passes through the first slot and the second slot to a bore of the gas turbine engine.   
     
     
         17 . The compressor of  claim 16 , wherein the at least one of the plurality of disks has a tab projection and the retainer has a groove that is adapted to be snap fit into the tab projection. 
     
     
         18 . The compressor of  claim 16 , wherein the retainer comprises a ring that is disposed fully about a centerline of the gas turbine engine and the paddle extends from the retainer radially outward away from the centerline.