Patent ID: 8235654
Filing Date: 2012-08-07
Classification: F01D,F04D,F05D

Abstract:
1. A gas turbine axial compressor comprising: a casing and a rotatable shaft, which form an annular duct; at least one stator having a plurality of stator vanes and a first rotor having a plurality of rotor blades positioned in the annular duct, the first rotor having a first rotor platform positioned at bases of the rotor blades; a shroud positioned at free ends of the stator vanes and which extends over only an incomplete portion of an axial span of the stator vanes to form an unshrouded vane portion including at least one of: leading portions of the stator vanes extending axially forward of an axially forward-most edge of the shroud, or trailing portions of the stator vanes extending axially rearward of an axially rearward-most edge of the shroud; wherein the first rotor platform is radially aligned with at least a portion of the shroud and extends axially below the unshrouded vane portion.