Rotating assembly for a turbomachine

Abstract

A rotating assembly for a turbomachine includes a plurality of rotating members that extend radially outward from a central hub. Each of the plurality of rotating members includes a base portion detachably mounted to the central hub, a tip portion, a mid-span portion that extends between the base portion and the tip portion, and a shroud portion positioned at one of the tip portion and the mid-span portion. The shroud portion includes a pressure side and a suction side. At least one hard face interface member is secured to at least one of the suction side and the pressure side of the shroud portion. The at least one hard face interface member is both mechanically interlocked with, and metallurgically bonded to, the shroud portion.

1 . A rotating assembly for a turbomachine comprising:
 a central hub;   a plurality of rotating members extending radially outward from the central hub, each of the plurality of rotating members including:
 a base portion detachably mounted to the central hub; 
 a tip portion; 
 a mid-span portion extending between the base portion and the tip portion; 
 a shroud portion positioned at one of the tip portion and the mid-span portion, the shroud portion including a pressure side and a suction side; and 
 at least one hard face interface member secured to at least one of the suction side and the pressure side of the shroud portion, the at least one hard face interface member being both mechanically interlocked with, and metallurgically bonded to the shroud portion. 
   
   
   
       2 . The rotating assembly according to  claim 1 , wherein the shroud portion includes at least one recess formed in one of the pressure side and suction side, the hard face interface member being mechanically interlocked with the shroud portion in the at least one recess. 
   
   
       3 . The rotating assembly according to  claim 2 , wherein the at least one recess includes a first recess formed in the pressure side of the shroud portion and a second recess formed in the suction side of the shroud portion. 
   
   
       4 . The rotating assembly according to  claim 3 , wherein the at least one hard face interface member includes a first hard face interface member mechanically interlocked with and metallurgically bonded to the shroud portion in the first recess and a second hard face interface member mechanically interlocked with and metallurgically bonded to the shroud portion in the second recess. 
   
   
       5 . The rotating assembly according to  claim 2 , wherein the at least one recess includes a base portion and a peripheral wall portion, the base portion including a plurality of surface elements. 
   
   
       6 . The rotating assembly according to  claim 5 , wherein the plurality of surface elements are indentations formed in the base portion. 
   
   
       7 . The rotating assembly according to  claim 5 , wherein the plurality of surface elements comprise at least one of a plurality of continuous grooves, a plurality of discontinuous grooves, a plurality of continuous protuberances and a plurality of discontinuous protuberances. 
   
   
       8 . The rotating assembly according to  claim 1 , wherein the shroud portion is mounted to the mid-span portion of each of the plurality of rotating members. 
   
   
       9 . The rotating assembly according to  claim 1 , wherein the shroud portion is mounted to the tip portion of each of the plurality of rotating members. 
   
   
       10 . The rotating assembly according to  claim 1 , wherein the shroud portion is mounted to both the mid-span portion and the tip portion of each of the plurality of rotating members. 
   
   
       11 . The rotating assembly according to  claim 1 , wherein the hard face interface member is formed from a pre-sintered preformed material. 
   
   
       12 . The rotating assembly according to  claim 1 , wherein the rotating assembly is mounted in a turbine engine. 
   
   
       13 . A method of securing a hard face interface member to a shroud portion of a rotating member for a turbomachine, the method comprising:
 forming a rotating member including a base portion, a mid-span portion and a tip portion;   forming a shroud portion on at least one of the mid-span portion and the tip portion of the rotating member, the shroud portion including a pressure side and a suction side; and   securing a hard face interface member to at least one of the pressure side and the suction side of the shroud portion, the hard face interface member being both mechanically interlocked with, and metallurgically bonded to, the shroud portion.   
   
   
       14 . The method of  claim 13 , further comprising:
 forming at least one recess in the one of the pressure side and the suction side of the shroud portion; and   securing the hard face interface member to the shroud portion at the recess.   
   
   
       15 . The method of  claim 13 , further comprising: brazing the hard face interface member in the recess formed in the one of the pressure side and the suction side of the shroud portion to secure the hard face interface member to the shroud portion. 
   
   
       16 . The method of  claim 15 , further comprising: machining the hard face interface member to establish a final finish. 
   
   
       17 . The method of  claim 13 , further comprising: forming a plurality of indentations within the recess formed in the one of the pressure side and the suction side of the shroud portion, the indentations providing additional surface area in the recess to strengthen the mechanical interlock. 
   
   
       18 . The method of  claim 13 , further comprising:
 forming a first recess in the pressure side of the shroud portion and a second recess in the suction side of the shroud portion; and   securing a first hard face interface member to the shroud portion at the first recess and a second hard face interface member at the second recess.   
   
   
       19 . The method of  claim 13 , further comprising:
 forming a first shroud portion on the mid-span portion of the rotating member and a second shroud portion on the tip portion of the rotating member; and   securing a hard face interface member to each of the first and second shroud portions with both a mechanical interlock and a metallurgical bond.   
   
   
       20 . The method of  claim 13 , further comprising: mounting the rotating member in a turbine-engine.