Blade attachment retention device

Abstract

A component for a gas turbine engine includes a rotor disk, a plurality of blade attachments, a plurality of retention flanges, and a plurality of retention tabs. The rotor disk has a plurality of slots formed in an outer surface thereof. Each blade attachment has an attachment region configured to be partially disposed within one of the slots. The plurality of retention flanges extend from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot. A retention tab extends from each attachment region and engages one of the retention flanges.

1 . A component for a gas turbine engine, the component comprising:
 a rotor disk having a plurality of slots formed in an outer surface thereof;   a plurality of blade attachments, each blade attachment having an attachment region configured to be partially disposed within one of the slots;   a plurality of retention flanges extending from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot; and   a retention tab extending from each attachment region and engaging one of the retention flanges.   
   
   
       2 . The component of  claim 1 , wherein the attachment region of each blade attachment is configured to be slidably disposed within one of the slots. 
   
   
       3 . The component of  claim 2 , wherein the attachment regions of each blade attachment are configured to be slidably disposed within a different slot. 
   
   
       4 . The component of  claim 1 , wherein the plurality of retention flanges are made at least in part from one or more of the following metals: titanium, steel, or a nickel-based alloy. 
   
   
       5 . The component of  claim 4 , wherein the retention tabs are made at least in part from one or more of the following metals: titanium, steel, or a nickel-based alloy. 
   
   
       6 . The component of  claim 1 , wherein:
 the retention flanges each extend at least partially radially from the rotor disk outer surface; and   the retention tabs each extend at least partially axially from a respective attachment region.   
   
   
       7 . The component of  claim 1 , wherein the component is configured to be implemented in a fan section of an engine. 
   
   
       9 . The component of  claim 1 , wherein the component is configured to be implemented in a turbine section of an engine. 
   
   
       10 . The component of  claim 1 , wherein the component is configured to be implemented in an axle section of an engine. 
   
   
       11 . The component of  claim 1 , wherein the component is configured to be implemented in a compressor section of an engine. 
   
   
       12 . A fan section for a gas turbine engine, the fan section comprising:
 an inlet adapted to receive air from a surrounding environment;   a rotor disk having a plurality of slots formed in an outer surface thereof;   a plurality of blade attachments, each blade attachment having an attachment region configured to be partially disposed within one of the slots;   a plurality of retention flanges extending from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot; and   a retention tab extending from each attachment region and engaging one of the retention flanges.   
   
   
       13 . The fan section of  claim 12 , wherein the attachment region of each blade attachment is configured to be slidably disposed within one of the slots. 
   
   
       14 . The fan section of  claim 12 , wherein the plurality of retention flanges are made at least in part from one or more of the following metals: titanium, steel, or a nickel-based alloy. 
   
   
       15 . The fan section of  claim 12 , wherein the retention tabs are made at least in part from one or more of the following metals: titanium, steel, or a nickel-based alloy. 
   
   
       16 . The fan section of  claim 12 , wherein:
 the retention flanges each extend at least partially radially from the rotor disk outer surface; and   the retention tabs each extend at least partially axially from a respective attachment region.   
   
   
       17 . A gas turbine engine comprising:
 a compressor having an inlet and an outlet and operable to receive accelerated air through the inlet, compress the accelerated air, and supply the compressed air through the outlet;   a combustor coupled to receive at least a portion of the compressed air from the compressor outlet and operable to supply combusted air;   a turbine coupled to receive the combusted air from the combustor and at least a portion of the compressed air from the compressor and to generate energy therefrom; and   a fan section comprising:
 an inlet adapted to receive air from a surrounding environment; 
 a rotor disk having an outer surface forming a plurality of slots; 
 a plurality of blades attached to the rotor disk, each blade having an attachment region configured to attach the blade to the rotor disk by fitting within a corresponding slot, the plurality of blades configured to accelerate a portion of the air and supply the accelerated air to the compressor; 
 a plurality of retention flanges extending from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot; and 
 a retention tab extending from each attachment region and engaging one of the retention flanges. 
   
   
   
       18 . The gas turbine engine of  claim 17 , wherein the attachment region of each blade attachment is configured to be slidably disposed within one of the slots. 
   
   
       19 . The gas turbine engine of  claim 17 , wherein the plurality of retention flanges and the retention tabs are made at least in part from one or more of the following metals: titanium, steel, or a nickel-based alloy. 
   
   
       20 . The gas turbine engine of  claim 17 , wherein:
 the retention flanges each extend at least partially radially from the rotor disk outer surface; and   the retention tabs each extend at least partially axially from a respective attachment region.