Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor

Abstract

A compressor for a gas turbine having a rotor rotating about an axis and a housing coaxially surrounding the rotor, thereby defining a flow channel between the rotor and the housing for a fluid to be compressed. Alternating rows of vanes and blades are arranged within the flow channel, with the vanes being mounted in the inner wall of the housing, and the blades being mounted in the outer wall of the rotor.

1 . A compressor for a gas turbine, said compressor comprising;
 a rotor rotating about an axis;   a housing coaxially surrounding said rotor, thereby defining a flow channel between rotor and housing for a fluid to be compressed;   alternating rows of vanes and blades arranged within the flow channel, the vanes being mounted in the inner wall of the housing, and the blades being mounted in the outer wall of the rotor; and   intermediate rings provided in the inner wall of the housing between neighbouring rows of vanes such that the outer wall of the flow channel is formed by said vanes and intermediate rings.   
     
     
         2 . The compressor according to  claim 1 , wherein said intermediate rings are adjacent to the tips of the blades. 
     
     
         3 . The compressor according to  claim 2 , wherein said intermediate rings bear a coating on their inner side just opposite to the tips of the blades. 
     
     
         4 . The compressor according to  claim 3 , wherein said coating is an abradable coating. 
     
     
         5 . The compressor according to  claim 4 , wherein the inner side of the intermediate rings is completely covered by said abradable coating. 
     
     
         6 . The compressor according to  claim 4 , wherein the inner side of the intermediate rings is only covered by said abradable coating only in an area opposite to the tips of the respective blades. 
     
     
         7 . The compressor according to  claim 4 , wherein said abradable coating comprises a honeycomb structure filled with an abradable material. 
     
     
         8 . The compressor according to  claim 1 , wherein the intermediate rings are mounted in circumferential mounting grooves provided in the inner wall of the housing. 
     
     
         9 . The compressor according to  claim 1 , wherein the intermediate rings are segmented in circumferential direction. 
     
     
         10 . A method for repairing and/or changing the geometry of and/or servicing the compressor of  claim 1 , the method comprising:
 exchanging and/or removing the intermediate rings from the compressor, processed and put back into the compressor;   processing the intermediate rings; and   replacing the intermediate rings back into the compressor.   
     
     
         11 . Method according to  claim 10 , wherein the outer diameter of the flow channel is increased in an upgrade by exchanging the intermediate rings and vanes.