Compressor of a gas turbine system

Abstract

A compressor of a gas turbine system includes at least one inlet row having a plurality of inlet guide vanes. Also included is at least one stator row having a plurality of stator vanes. Further included is a first actuation mechanism operably connected to the at least one stator row, wherein the first actuation mechanism is configured to positionally manipulate the at least one stator row. Yet further included is a second actuation mechanism operably connected to the at least one stator row, wherein the second actuation mechanism is configured to positionally manipulate the at least one stator row.

1 . A compressor of a gas turbine system comprising:
 at least one inlet row having a plurality of inlet guide vanes;   at least one stator row having a plurality of stator vanes;   a first actuation mechanism operably connected to the at least one stator row, wherein the first actuation mechanism is configured to positionally manipulate the at least one stator row; and   a second actuation mechanism operably connected to the at least one stator row, wherein the second actuation mechanism is configured to positionally manipulate the at least one stator row.   
     
     
         2 . The compressor of  claim 1 , wherein the first actuation mechanism is hydraulically actuated. 
     
     
         3 . The compressor of  claim 1 , wherein at least one of the first actuation mechanism and the second actuation mechanism is driven by an electric motor. 
     
     
         4 . The compressor of  claim 1 , further comprising:
 a plurality of stator rows, each of the plurality of stator rows having the plurality of stator vanes;   a linkage operably connecting the first actuation mechanism to the plurality of stator rows; and   a plurality of second actuation mechanisms, each of the plurality of second actuation mechanisms operably connected to one of the plurality of stator rows.   
     
     
         5 . The compressor of  claim 4 , wherein each of the plurality of second actuation mechanisms is configured to independently positionally manipulate each of the plurality of stator rows. 
     
     
         6 . The compressor of  claim 4 , wherein the plurality of stator rows are operably coupled together. 
     
     
         7 . The compressor of  claim 6 , wherein the linkage operably couples the plurality of stator rows together. 
     
     
         8 . The compressor of  claim 1 , wherein the second actuation mechanism positionally manipulates the at least one stator row with greater precision than the first actuation mechanism. 
     
     
         9 . The compressor of  claim 1 , wherein the at least one stator row is positionally variable with respect to the at least one inlet row. 
     
     
         10 . A compressor of a gas turbine system comprising:
 a plurality of rows, each of the plurality of rows having a plurality of stator vanes;   a first actuation mechanism operably connected to the plurality of rows, wherein the first actuation mechanism is configured to positionally manipulate the plurality of rows; and   a second actuation mechanism operably connected to at least one row of the plurality of rows, wherein the second actuation mechanism is configured to positionally manipulate the at least one row.   
     
     
         11 . The compressor of  claim 10 , wherein the first actuation mechanism is electrically actuated. 
     
     
         12 . The compressor of  claim 10 , wherein the second actuation mechanism comprises a screw driven by an electric motor. 
     
     
         13 . The compressor of  claim 10 , further comprising at least one inlet row having a plurality of inlet vanes. 
     
     
         14 . The compressor of  claim 13 , wherein the plurality of rows is positionally variable with respect to at least one inlet row. 
     
     
         15 . The compressor of  claim 10 , further comprising:
 a linkage operably connecting the first actuation mechanism to the plurality of rows; and   a plurality of second actuation mechanisms, each of the plurality of second actuation mechanisms operably connected to one of the plurality of rows.   
     
     
         16 . The compressor of  claim 15 , wherein each of the plurality of second actuation mechanisms is configured to independently positionally manipulate each of the plurality of rows. 
     
     
         17 . The compressor of  claim 15 , wherein the linkage operably couples the plurality of rows together. 
     
     
         18 . A compressor of a gas turbine system comprising:
 at least one inlet row having a plurality of inlet guide vanes;   a plurality of stator rows, each of the plurality of stator rows having a plurality of stator vanes;   an electric actuator operably connected to the plurality of stator rows, wherein the hydraulic actuator is configured to positionally manipulate the plurality of stator rows; and   an electrically driven screw actuator operably connected to at least one stator row of the plurality of stator rows, wherein the electrically driven screw actuator is configured to positionally manipulate the at least one stator row.   
     
     
         19 . The compressor of  claim 18 , wherein the plurality of stator rows is positionally variable with respect to the at least one inlet row. 
     
     
         20 . The compressor of  claim 18 , further comprising a plurality of second actuation mechanisms, each of the plurality of second actuation mechanisms operably connected to one of the plurality of stator rows for independently positionally manipulating each of the plurality of stator rows.