Axial turbocompressor

Abstract

An axial turbocompressor having an annular compressor passage which is arranged concentrically around a rotational axis, is delimited radially on the outside by a passage wall, and in which rotor blades, which may be assembled to form a ring, are arranged in a rotatably mounted manner around the rotational axis, is provided. The free-ending tips of the rotor blades lie opposite the passage wall in each case, forming a gap, and the passage wall, in the axial section of the tips, at least partially has a wall structuring and wherein a bleed opening of a bleed passage is provided in the passage wall for the tapping of medium flowing in the compressor passage. In order to enable an exceptionally efficient bleed of medium flowing in the compressor passage, the bleed opening is located in the wall structuring.

1 . An axial turbocompressor, comprising:
 an annular compressor passage which is arranged concentrically around a rotational axis, is delimited radially on the outside by a passage wall, and in which a plurality of rotor blades, which may be assembled to form a ring, are arranged in a rotatably mounted manner around the rotational axis,   wherein the free-ending tips of the plurality of rotor blades lie opposite the passage wall in each case, forming a gap, and the passage wall, in the axial section of the free-ending tips, at least partially has a wall structuring,   wherein a bleed opening of a bleed passage is provided in the passage wall for the tapping of medium flowing in the compressor passage, and   wherein the bleed opening is located in the wall structuring.   
     
     
         2 . The axial turbocompressor as claimed in  claim 1 , wherein the wall structuring is variable in its extent and form and as a result the bleed opening is at least partially uncovered. 
     
     
         3 . The axial turbocompressor as claimed in  claim 1 , wherein the wall structuring is variable in its extent or form and as a result the bleed opening is at least partially uncovered. 
     
     
         4 . The axial turbocompressor as claimed in  claim 2 , wherein the wall structuring is variable in its extent and form by means of a movable insert and the bleed opening is located in a sidewall of the recess which accommodates the insert. 
     
     
         5 . The axial turbocompressor as claimed in  claim 3 , wherein the wall structuring is variable in its extent or form by means of a movable insert and the bleed opening is located in a sidewall of the recess which accommodates the insert. 
     
     
         6 . The axial turbocompressor as claimed in  claim 1 , wherein the bleed passage is connected on the flow discharge side to a blow-off air system and/or cooling air system. 
     
     
         7 . The axial turbocompressor as claimed in  claim 1 , wherein provision is made for a plurality of bleed openings per rotor blade ring. 
     
     
         8 . A gas turbine, comprising:
 an axial turbocompressor as claimed in  claim 1 .   
     
     
         9 . The gas turbine as claimed in  claim 8 , wherein the wall structuring is variable in its extent and form and as a result the bleed opening is at least partially uncovered. 
     
     
         10 . The axial gas turbine as claimed in  claim 8 , wherein the wall structuring is variable in its extent or form and as a result the bleed opening is at least partially uncovered. 
     
     
         11 . The axial gas turbine as claimed in  claim 9 , wherein the wall structuring is variable in its extent and form by means of a movable insert and the bleed opening is located in a sidewall of the recess which accommodates the insert. 
     
     
         12 . The axial gas turbine as claimed in  claim 10 , wherein the wall structuring is variable in its extent or form by means of a movable insert and the bleed opening is located in a sidewall of the recess which accommodates the insert. 
     
     
         13 . The axial gas turbine as claimed in  claim 8 , wherein the bleed passage is connected on the flow discharge side to a blow-off air system and/or cooling air system. 
     
     
         14 . The axial gas turbine as claimed in  claim 8 , wherein provision is made for a plurality of bleed openings per rotor blade ring.