Device and method for sealing a gas path in a turbine

Abstract

A device for sealing a gas path in a turbine includes a first shroud segment and a slot in a surface of the first shroud segment. A barrier extends inside the slot, and a bypass channel in the slot provides fluid communication between the barrier and the slot to the gas path in the turbine. A method for sealing a gas path in a turbine includes placing a barrier between a first slot in a first shroud segment and a second slot in a second shroud segment and flowing a fluid between the barrier and the first slot to the gas path in the turbine, wherein the fluid flows through a first bypass channel in the first slot.

What is claimed is: 
     
         1 . A device for sealing a gas path in a turbine, comprising:
 a. a first shroud segment;   b. a slot in a surface of said first shroud segment;   c. a barrier extending inside said slot; and   d. a bypass channel in said slot, wherein said bypass channel provides fluid communication between said barrier and said slot to the gas path in the turbine.   
     
     
         2 . The device as in  claim 1 , further comprising a second shroud segment adjacent to said first shroud segment, wherein said first and second shroud segments have adjacent surfaces. 
     
     
         3 . The device as in  claim 1 , wherein said barrier comprises a plurality of sections that extends between said slot. 
     
     
         4 . The device as in  claim 1 , wherein said bypass channel extends substantially perpendicular to a fluid flow in the gas path in the turbine. 
     
     
         5 . The device as in  claim 1 , wherein said bypass channel comprises a plurality of uniformly spaced grooves in said slot. 
     
     
         6 . The device as in  claim 1 , wherein said bypass channel has an arcuate shape. 
     
     
         7 . The device as in  claim 1 , further comprising a fluid port through said first shroud segment to said slot in said first shroud segment. 
     
     
         8 . A device for sealing a gas path in a turbine, comprising:
 a. a first shroud segment, wherein said first shroud segment has a first slot;   b. a second shroud segment adjacent to said first shroud segment, wherein said second shroud segment has a second slot;   c. a barrier extending from inside said first slot to inside said second slot, wherein said barrier has a substantially flat surface facing the gas path and in contact with each of said first and second slots; and   d. a first fluid passage to the gas path in the turbine between said barrier and said first slot.   
     
     
         9 . The device as in  claim 8 , wherein said barrier has a dimension that is larger inside said first and second slots than between said first and second shroud segments. 
     
     
         10 . The device as in  claim 8 , wherein said barrier comprises a plurality of sections that extend from inside said first slot to inside said second slot. 
     
     
         11 . The device as in  claim 8 , wherein said first fluid passage extends in the direction of said second shroud segment. 
     
     
         12 . The device as in  claim 8 , wherein said first fluid passage comprises a plurality of uniformly spaced grooves in said first slot. 
     
     
         13 . The device as in  claim 8 , wherein said first fluid passage comprises a plurality arcuate grooves in said first slot. 
     
     
         14 . The device as in  claim 8 , further comprising a fluid port through said first shroud segment to said first slot in said first shroud segment. 
     
     
         15 . The device as in  claim 8 , further comprising a second fluid passage between said barrier and said second slot to the gas path in the turbine. 
     
     
         16 . A method for sealing a gas path in a turbine, comprising:
 a. placing a barrier between a first slot in a first shroud segment and a second slot in a second shroud segment; and   b. flowing a fluid between said barrier and said first slot to the gas path in the turbine, wherein said fluid flows through a first bypass channel in said first slot.   
     
     
         17 . The method as in  claim 16 , further comprising flowing said fluid through a plurality of grooves in said first slot. 
     
     
         18 . The method as in  claim 16 , further comprising flowing said fluid through a fluid port in said first shroud segment to said first slot in said first shroud segment. 
     
     
         19 . The method as in  claim 16 , further comprising flowing the fluid between said barrier and said second slot to the gas path in the turbine, wherein said fluid flows through a second bypass channel in said second slot.