FIELD: machine building.
SUBSTANCE: invention relates to a unit of gas turbine engine guide vanes with an axial compressor. Blade unit of guide vanes comprises annular rim of blades (26) extending radially, inner ring (30) located at inner ends of blades (26). Inner ring (30) comprises annular sealing gasket (36) of elastomer or silicone, which is located on one of the sides located upstream or downstream of said ring (30), in order to provide tightness with sealing surface (44) of intermediate casing (34) of gas turbine engine. Inner ring (30) comprises cavity (45), in which sealing gasket (36) is arranged, wherein the cavity is formed as an integral part in the material of the inner ring and/or using one or more additional elements (46).
EFFECT: invention increases degree of tightness at action of vibrations and at the same time increases stiffness of inner ring (30) without increasing manufacturing costs.
12 cl, 3 dwg
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