System for regulating a cooling fluid within a turbomachine

Abstract

Embodiments of the present invention provide a system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to a wheelspace area. The system includes a plurality of angular passages that aid in the mixing of a cooling fluid with a working fluid in the wheelspace area.

1 . A system for regulating a cooling fluid, the system comprising:
 a turbomachine comprising:
 a compressor section comprising an inner barrel casing; a compressor discharge casing; and bypass chambers that allow a cooling fluid to pass from the inner barrel casing to the compressor discharge casing; 
 a turbine section comprising rotating components; stationary components; and wheelspace areas, wherein each wheelspace area comprises a rotating component and a stationary component and each bypass chamber allows for the cooling fluid to pass from the compressor section to the wheelspace area; and 
 a nozzle cooling circuit comprising a primary passage and a header, which are both substantially located within each stationary component, wherein a first end of the primary passage receives the cooling fluid and a second end of the primary passage is connected to the header such that the cooling fluid flows from the primary passage to the header; 
 wherein the header comprises an upstream port and a downstream port that allows the cooling fluid to discharge from the header. 
   
     
     
         2 . The system of  claim 1 , wherein a downstream end of each port is connected to a tuning plug that comprises an opening which directs the cooling fluid out of the nozzle cooling circuit. 
     
     
         3 . The system of  claim 2 , wherein the tuning plug determines mechanical properties of the cooling fluid. 
     
     
         4 . The system of  claim 1 , wherein the stationary component comprises multiple nozzle cooling circuits. 
     
     
         5 . The system of  claim 6 , wherein each of the multiple nozzle cooling circuits comprises: a designated primary passage and a designated header. 
     
     
         6 . The system of  claim 1 , wherein each port is offset from the header at an angle which pre-swirls the cooling fluid in a manner that aids in mixing with the working fluid. 
     
     
         7 . The system of  claim 6 , wherein the angle orients the flow of the cooling fluid in a direction similar to that of the working fluid and the rotating components. 
     
     
         8 . The system of  claim 1 , wherein the header is the form of a hole extending through the stationary component. 
     
     
         9 . The system of  claim 8 , wherein each end of the header is enclosed by a cap. 
     
     
         10 . A system for regulating a cooling fluid, the system comprising:
 a gas turbine comprising:
 a combustion system that generates a working fluid; 
 a compressor section comprising an inner barrel casing; a compressor discharge casing; and bypass chambers; wherein the cooling fluid flows through the inner barrel casing to the compressor discharge casing; 
 a turbine section comprising rotating components; stationary components; and wheelspace areas, wherein each wheelspace area comprises a rotating component and a stationary component and each bypass chamber allows for the cooling fluid to pass from the compressor section to the wheelspace area; and 
 a nozzle cooling circuit substantially located within each stationary component, wherein the nozzle cooling circuit comprises a primary passage and a header; wherein a first end of the primary passage receives the cooling fluid and a second end of the primary passage is connected to the header and the cooling fluid flows from the primary passage to the header; 
 wherein the header comprises an upstream port and a downstream port that allows the cooling fluid to discharge from the header and mixing with the working fluid. 
   
     
     
         11 . The system of  claim 10  further comprising a tuning plug located downstream of the header, which allows the cooling fluid to exit the nozzle cooling circuit. 
     
     
         12 . The system of  claim 11 , wherein each port is integrated with a dedicated tuning plug. 
     
     
         13 . The system of  claim 11 , wherein the dedicated tuning plug comprise a variable internal diameter through which the cooling fluid discharges the header. 
     
     
         14 . The system of  claim 13 , wherein the dedicated tuning plug determines at least one of the following properties of the cooling fluid: velocity, flowrate, or pressure. 
     
     
         15 . The system of  claim 10 , wherein the stationary component comprises multiple nozzle cooling circuits. 
     
     
         16 . The system of  claim 15 , wherein each of the multiple nozzle cooling circuits comprises: a designated primary passage and a designated header. 
     
     
         17 . The system of  claim 11 , wherein the dedicated tuning plug directs the cooling fluids towards an outer surface of the stationary component. 
     
     
         18 . The system of  claim 10 , wherein each port is offset from the header at an angle which pre-swirls the cooling fluid in a manner that aids in mixing with the working fluid. 
     
     
         19 . The system of  claim 18 , wherein the angle orients the flow of the cooling fluid in a direction similar to that of the working fluid and the rotating components. 
     
     
         20 . The system of  claim 11 , wherein the header is the form of a circular opening that extends through the stationary component in an upstream to downstream orientation, and wherein each end of the header is enclosed by a cap.