FIELD: engines and pumps.
SUBSTANCE: angular sector of a stator for a turbine engine compressor comprises outer and inner shrouds and at least one vane. Vane extends radially between shrouds and connected to them. Outer shroud has a mounting device at each axial end for mounting angular sector of a stator on engine casing. At one axial end outer shroud includes cavity open towards axial end. Cavity extends between a radially outer shroud to which radially-outer end of vane is connected, and a radially-outer tongue of outer shroud carrying a mounting mechanism for mounting stator angular sector to an engine casing. An abutment-forming insert is housed at least in part in cavity, abutment-forming insert configured to limit radial movements of radially-inner tongue by contact and thus to modify vibratory behavior of radially-inner tongue. Other group inventions relate to gas turbine engine stator comprising abovementioned angular sector and a gas turbine engine comprising such stator.
EFFECT: group of inventions allows limiting of mechanical stresses to which each vane of stator sector is subjected in operation.
15 cl, 4 dwg
