Compressor guide-vane stage for a turbine engine including a gasket between a vane and a shroud of the guide-vane stage
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United States of America Patent
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Jan 30, 2018
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N/A
app pub date -
Apr 4, 2013
filing date -
Apr 5, 2012
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Abstract
A compressor guide-vane stage for a turbine engine, the stage comprising two coaxial shrouds, respectively an inner shroud (120) and an outer shroud, with vanes (124) extending between them, the radially inner ends of the vanes being engaged with clearance (125) in orifices in the inner shroud and being secured to the inner shroud by means of a polymerizable sealing resin (126), the guide-vane stage being characterized in that 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 or in the proximity of said surface, in order to limit the passage of resin through the above-mentioned clearance while the resin is being applied to the inside surface of the shroud.
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