US 2014/0271158 A1 · COMPRESSOR STATOR

Abstract

Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).

Claims20

Dependent claims

A compressor stator comprising:

a circumferential array of stator vanes;
and
a shroud for supporting the stator vanes, the shroud having a circumferentially extending inner endwall exposed to an annular gas path of the compressor, the endwall having a circumferentially uniform axial cross-sectional profile, the axial cross-sectional profile comprising at least one deviation from a nominal axial cross-sectional profile defining an overall shape of the annular gas path, the at least one deviation comprising a concave deviation having a maximum deviation from the nominal profile at a position substantially corresponding to an axial position of a maximum thickness of at least one of the vanes.

Dependencies are inferred from the claim text.

Compressor stator

Life of this patent

Compressor stator

Life of this patent

Abstract

Claims20