Turbine Shroud Cooling Assembly for a Gas Turbine System

Abstract

A turbine shroud cooling assembly for a gas turbine system includes an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a base portion in direct contact with the hot gas path. Also includes is a rib protruding radially away from the base portion and disposed proximate at least one cavity configured to receive a cooling flow from a cooling source, wherein the cooling flow passes through the main passage of the rib for cooling the inner shroud component.

1 . A turbine shroud cooling assembly for a gas turbine system comprising:
 an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a base portion in direct contact with the hot gas path; and   at least one rib protruding radially away from the base portion and disposed proximate at least one cavity configured to receive a cooling flow from a cooling source, wherein the cooling flow passes through the main passage of the at least one rib for cooling the inner shroud component.   
     
     
         2 . The turbine shroud cooling assembly of  claim 1 , further comprising a first side portion passage disposed within a first side portion and a second side portion passage disposed within a second side portion. 
     
     
         3 . The turbine shroud cooling assembly of  claim 2 , wherein the main passage extends from the first side portion passage to the second side portion passage, wherein the cooling flow is transferred between the first side portion passage and the second side portion passage by passing through the main passage. 
     
     
         4 . The turbine shroud cooling assembly of  claim 2 , further comprising a leading edge of the inner shroud component and a trailing edge of the inner shroud component. 
     
     
         5 . The turbine shroud cooling assembly of  claim 2 , further comprising at least one fore passage disposed proximate a leading edge and at least one aft passage disposed proximate a trailing edge, wherein the main passage extends from the at least one fore passage to the at least one aft passage. 
     
     
         6 . The turbine shroud cooling assembly of  claim 5 , wherein the at least one fore passage extends from the first side portion passage to the second side portion passage, wherein the at least one aft passage extends from the first side portion passage to the second side portion passage. 
     
     
         7 . The turbine shroud cooling assembly of  claim 5 , wherein the cooling flow is free to transfer between the first side portion passage, the second side portion passage, the at least one fore passage, the at least one aft passage, and the main passage in a continuous interconnected cooling flow circuit. 
     
     
         8 . The turbine shroud cooling assembly of  claim 1 , further comprising a plurality of channels extending from the at least one cavity to the main passage to direct the cooling flow into the main passage. 
     
     
         9 . The turbine shroud cooling assembly of  claim 1 , wherein the main passage includes at least one break forming a plurality of main passages. 
     
     
         10 . A turbine shroud cooling assembly for a gas turbine system comprising:
 an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a leading edge and a trailing edge disposed at an aft location of the inner shroud component relative to the leading edge;   a base portion extending from the leading edge to the trailing edge, wherein the base portion is in direct contact with the hot gas path; and   a rib extending from a first side portion to a second side portion and radially outward from the base portion, wherein the rib includes a main passage extending between the first side portion and the second side portion and configured to receive a cooling flow from a cooling source.   
     
     
         11 . The turbine shroud cooling assembly of  claim 10 , wherein the rib is at least partially surrounded by at least one cavity configured to receive the cooling flow from the cooling source. 
     
     
         12 . The turbine shroud cooling assembly of  claim 11 , further comprising a plurality of channels extending from the at least one cavity to the main passage to direct the cooling flow into the main passage. 
     
     
         13 . The turbine shroud cooling assembly of  claim 12 , wherein the plurality of channels are drilled through holes. 
     
     
         14 . The turbine shroud cooling assembly of  claim 12 , further comprising a first side portion passage disposed within the first side portion and a second side portion passage disposed within the second side portion, wherein the main passage extends from the first side portion passage to the second side portion passage, wherein the cooling flow is transferred between the first side portion passage and the second side portion passage by passing through the main passage. 
     
     
         15 . The turbine shroud cooling assembly of  claim 14 , further comprising a fore passage disposed proximate the leading edge and an aft passage disposed proximate the trailing edge. 
     
     
         16 . The turbine shroud cooling assembly of  claim 15 , wherein the fore passage extends from the first side portion passage to the second side portion passage, wherein the aft passage extends from the first side portion passage to the second side portion passage. 
     
     
         17 . The turbine shroud cooling assembly of  claim 15 , wherein the cooling flow is free to transfer between the first side portion passage, the second side portion passage, the fore passage, the aft passage, and the main passage in a continuous interconnected cooling flow circuit. 
     
     
         18 . A gas turbine system comprising:
 a compressor for distributing a cooling flow at a high pressure;   a turbine casing operably supporting a turbine shroud assembly for receiving the cooling flow for cooling therein;   an inner shroud component comprising a leading edge, a trailing edge spaced axially rearward of the leading edge, and a base portion connecting the leading edge to the trailing edge; and   a rib disposed between the leading edge and the trailing edge, and extending between a first side portion and a second side portion, wherein the rib includes a main passage configured to receive the cooling flow for cooling the inner shroud component.   
     
     
         19 . The gas turbine system of  claim 18 , further comprising a first side portion passage disposed within the first side portion and a second side portion passage disposed within the second side portion, wherein the main passage extends from the first side portion passage to the second side portion passage, wherein the cooling flow is transferred between the first side portion passage and the second side portion passage by passing through the main passage. 
     
     
         20 . The gas turbine system of  claim 18 , wherein the rib is at least partially surrounded by an impingement cavity configured to receive the cooling flow, and further comprising a plurality of channels extending from the impingement cavity to the main passage to direct the cooling flow into the main passage.