Systems and Methods for Reducing or Limiting One or More Flows Between a Hot Gas Path and a Wheel Space of a Turbine

Abstract

A turbine assembly is disclosed herein. The turbine assembly may include a rotor with at least one bucket extending radially therefrom. The turbine assembly also may include a stator assembly positioned adjacent to the at least one bucket. Moreover, the turbine assembly may include a seal assembly. The seal assembly may include a first flange extending in a substantially axial direction from the at least one bucket. The seal assembly also may include a second flange extending from the stator assembly in the substantially axial direction opposite the first flange. The second flange may include at least one protuberance projecting towards the first flange.

That which is claimed: 
     
         1 . A turbine assembly, comprising:
 a rotor;   at least one bucket extending radially from the rotor;   a stator assembly positioned adjacent to the at least one bucket; and   a seal assembly, comprising:
 a first flange extending from the at least one bucket in a substantially axial direction; and 
 a second flange extending from the stator assembly in a substantially axial direction opposite the first flange, wherein the second flange comprises at least one protuberance projecting towards the first flange. 
   
     
     
         2 . The turbine assembly of  claim 1 , wherein the at least one protuberance is disposed about a distal end of the second flange. 
     
     
         3 . The turbine assembly of  claim 1 , wherein the at least one protuberance is disposed between a distal end of the second flange and the stator assembly. 
     
     
         4 . The turbine assembly of  claim 1 , further comprising a second at least one protuberance projecting from the distal end of the second flange in the substantially axial direction opposite the first flange. 
     
     
         5 . The turbine assembly of  claim 1 , wherein the second flange comprises a discourager seal. 
     
     
         6 . The turbine assembly of  claim 1 , wherein the first flange comprises an angle wing seal. 
     
     
         7 . The turbine assembly of  claim 1 , wherein the first flange and the second flange define a gap therebetween. 
     
     
         8 . The turbine assembly of  claim 1 , wherein the at least one protuberance comprises one or more teeth, wings, nubs, or fins. 
     
     
         9 . A turbine system, comprising:
 a compressor;   a combustion system in communication with the compressor;   a turbine in communication with the combustion system, wherein the turbine comprises:
 a rotor; 
 at least one bucket extending radially from the rotor; 
 a stator assembly positioned adjacent to the at least one bucket; and 
 a seal assembly, comprising:
 a first flange extending from the at least one bucket in a substantially axial direction; and 
 a second flange extending from the stator assembly in a substantially axial direction opposite the first flange, wherein the second flange comprises at least one protuberance projecting towards the first flange. 
 
   
     
     
         10 . The system of  claim 9 , wherein the at least one protuberance is disposed about a distal end of the second flange. 
     
     
         11 . The system of  claim 9 , wherein the at least one protuberance is disposed between a distal end of the second flange and the stator assembly. 
     
     
         12 . The system of  claim 9 , further comprising a second at least one protuberance projecting from the distal end of the second flange in the substantially axial direction opposite the first flange. 
     
     
         13 . The system of  claim 9 , wherein the second flange comprises a discourager seal. 
     
     
         14 . The system of  claim 9 , wherein the first flange comprises an angle wing seal. 
     
     
         15 . The system of  claim 9 , wherein the first flange and the second flange define a gap therebetween. 
     
     
         16 . The system of  claim 9 , wherein the at least one protuberance comprises one or more teeth, wings, nubs, or fins. 
     
     
         17 . A method to reduce or limit a flow to a wheel space and a hot gas path of a turbine, the method comprising:
 positioning a first flange about at least one bucket extending radially from a rotor;   positioning a second flange about a stator assembly positioned adjacent to the at least one bucket, wherein the first flange and the second flange are radially spaced apart to at least partially form a seal assembly; and   reducing the flow to the wheel space and the hot gas path of the turbine with at least one protuberance projecting from the second flange towards the first flange.   
     
     
         18 . The method of  claim 17 , further comprising disposing the at least one protuberance about a distal end of the second flange. 
     
     
         19 . The method of  claim 17 , further comprising disposing the at least one protuberance between a distal end of the second flange and the stator assembly. 
     
     
         20 . The method of  claim 17 , further comprising reducing the flow to the wheel space and the hot gas path of the turbine with a second at least one protuberance projecting from the distal end of the second flange in the substantially axial direction opposite the first flange.