| 摘要 |
<p>Disclosed is a compressor guide-vane stage for a turbine engine. The stage comprises two coaxial shrouds, respectively an inner shroud 20 and an outer shroud, with vanes 24, 124 extending between them. The radially inner ends or roots of the vanes are engaged with clearance in orifices 25, 125 in the inner shroud and are connected to the inner shroud by means of a polymerizable sealing resin which is used to seal the vane in place. A gasket 140 is mounted on the radially inner end of each vane, the gasket including a slit through which the vane passes and bearing against the radially inside surface of the shroud in order to limit the passage of resin through the clearance while the resin is being applied to the inside surface of the shroud. An associated method of assembly and a gasket are also disclosed.</p> |
