Patent ID: 8328513
Filing Date: 2012-12-11
Classification: F01D,F04D,F05D

Abstract:
1. A row of stator blades in an axial compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located axially downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch; wherein: each stator blade within the row of stator blades connects, at an outer radial edge, to an outer wall and, at an inner radial edge, to an inner wall; the outer wall defining an outer flowpath boundary of a main flowpath of the compressor and the inner wall defining an inner flowpath boundary of the main flowpath of the compressor; the inboard forward notch comprises a cut-out section that extends rearward a first predetermined distance from a leading edge of the stator blade along the inner wall, the first predetermined distance comprising a distance less than a length of the stator blade; and the outboard forward notch comprises a cut-out section that extends rearward a second predetermined distance from a leading edge of the stator blade along the outer wall, the second predetermined distance comprising a distance less than the length of the stator blade.