Components for gas turbine engines and methods for manufacturing components for gas turbine engines

Abstract

A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique.

1 . A method of manufacturing a turbine engine component, the method comprising the steps of:
 fabricating an inner hub;   casting a plurality of blades, each blade comprising:
 a blade root; and 
 an airfoil body extending from the blade root; 
   forming a blade ring comprising, at least in part, the plurality of blades coupled using a first bonding technique; and   bonding the blade ring to the inner hub using a second bonding technique.   
   
   
       2 . The method of  claim 1 , wherein the step of forming a blade ring comprises bonding the blade roots together using the first bonding technique. 
   
   
       3 . The method of  claim 1 , wherein the step of forming a blade ring comprises bonding the blade roots to a rung member using the first bonding technique. 
   
   
       4 . The method of  claim 1 , further comprising the step of:
 removing material from the blade ring or the inner hub, or both.   
   
   
       5 . The method of  claim 4 , further comprising the step of:
 forming a cavity in the blade root.   
   
   
       6 . The method of  claim 5 , wherein the cavity is formed prior to bonding the blade ring to the inner hub. 
   
   
       7 . The method of  claim 1 , wherein the step of forming a blade ring comprises coupling the plurality of blades via brazing. 
   
   
       8 . The method of  claim 1 , wherein the step of forming a blade ring comprises coupling the plurality of blades via diffusion bonding. 
   
   
       9 . The method of  claim 1 , wherein the step of forming a blade ring comprises coupling the plurality of blades via transient liquid phase bonding. 
   
   
       10 . The method of  claim 1 , wherein the step of forming a blade ring comprises coupling the plurality of blades via welding. 
   
   
       11 . The method of  claim 1 , wherein the step of bonding the blade ring to the inner hub comprises diffusion bonding the blade ring to the inner hub. 
   
   
       12 . The method of  claim 1 , further comprising the step of:
 vacuum brazing a bonding region between the blade ring and the inner hub.   
   
   
       13 . A turbine engine component for a gas turbine engine, the turbine engine component comprising:
 an inner hub; and   a blade ring bonded to the inner hub, the blade ring comprising a plurality of blades, each blade comprising:
 a blade root; and 
 an airfoil body extending from the blade root; 
   wherein the blade ring further comprises a plurality of cavities, each cavity disposed proximate the blade root of one of the plurality of blades.   
   
   
       14 . The turbine engine component of  claim 13 , wherein the blade ring further comprises:
 a rung member bonded to the inner hub.   
   
   
       15 . The turbine engine component of  claim 13 , further comprising:
 a cover plate at least partially surrounding at least one of the plurality of cavities.   
   
   
       16 . The turbine engine component of  claim 13 , wherein the blade ring is bonded to the inner hub via diffusion bonding. 
   
   
       17 . A gas turbine engine, comprising:
 a compressor having an inlet and an outlet and operable to supply compressed air;   a combustor coupled to receive at least a portion of the compressed air from the compressor and operable to supply combusted air; and   a turbine coupled to receive the combusted air from the combustor and at least a portion of the compressed air from the compressor, the turbine comprising:
 an inner hub; and 
 a blade ring bonded to the inner hub, the blade ring comprising a plurality of blades, each blade comprising:
 a blade root; and 
 an airfoil body extending from the blade root; 
 
   wherein the blade ring further comprises a plurality of cavities, each cavity disposed proximate the blade root of one of the plurality of blades.   
   
   
       18 . The gas turbine engine of  claim 17 , wherein the blade ring further comprises:
 a rung member bonded to the inner hub.   
   
   
       19 . The gas turbine engine of  claim 17 , further comprising:
 a cover plate at least partially surrounding one of the plurality of cavities.   
   
   
       20 . The gas turbine engine of  claim 17 , wherein the blade ring is bonded to the inner hub via diffusion bonding.