Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses

Abstract

An axial turbo-compressor for a gas turbine having a stator vane assembly that is formed by stator vanes having vane tips exposed on the hub side and a stationary shaft cover on the hub side and delimits the flow channel of the axial compressor is provided. A radial gap is designed between the shaft cover and the van tips that is minimally sized such that the axial turbo-compressor may still be assembled, and there is a plurality of recesses in the shaft cover, wherein one of the recesses is allocated to each vane tip that is arranged directly neighboring the vane tip allocated thereto and is sized such that during operation of the axial turbo compressor every vane tip may be plunged into the recess allocated thereto without one of the vane tips significantly contacting the shaft cover.

1 .- 5 . (canceled) 
     
     
         6 . An axial turbocompressor for a gas turbine, comprising:
 a guide vane cascade, which is formed by a plurality of guide vanes including a plurality of vane tips which are free standing on a hub side; and   a stationary shaft cover, which is arranged directly adjacent to the plurality of vane tips on the hub side and delimits a flow passage of the axial compressor,   wherein a radial gap is formed between the shaft cover and the plurality of vane tips and is minimally dimensioned in such a way that an assembly of the axial turbocompressor may only just be accomplished, and provision is made in the shaft cover for a plurality of recesses, and   wherein one of the plurality of recesses is associated with each vane tip and is arranged directly adjacent to the vane tip which is associated therewith, and dimensioned in such a way that during operation of the axial turbocompressor each vane tip may sink into the associated recess without one of the plurality of vane tips coming into appreciable contact with the shaft cover.   
     
     
         7 . The axial turbocompressor as claimed in  claim 6 , wherein a honeycomb-like structure, which may yield during contact by the vane tips, is applied to a base of each recess. 
     
     
         8 . The axial turbocompressor as claimed in  claim 6 , wherein a felt-like structure, which may yield during contact by the vane tips, is applied to a base of each recess. 
     
     
         9 . The axial turbocompressor as claimed in  claim 6 , wherein a honeycomb-like and felt-like structure, which may yield during contact by the vane tips, is applied to a base of each recess. 
     
     
         10 . The axial turbocompressor as claimed in  claim 6 , wherein each recess includes a contour shape on a surface of the shaft cover which is adapted to a profile of the plurality of guide vanes at the vane tip, and includes a prespecified depth. 
     
     
         11 . The axial turbocompressor as claimed in  claim 10 , wherein the depth of the plurality of recesses is determined in such a way that during operation of the axial turbocompressor the radial relative movements between the plurality of vane tips and the shaft cover may be compensated. 
     
     
         12 . The axial turbocompressor as claimed in  claim 10 , wherein the contour shape of the plurality of recesses is determined in such a way that during operation of the axial turbocompressor the axial relative movements between the plurality of vane tips and the shaft cover may be compensated.