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US 12,320,275 B2Granted
Stator vane assembly for an aircraft turbine engine compressor
AssigneeSafran Aero Boosters SA
InventorsThéo Robin Thomas Bour, Matthieu Edouard Henri Droeller, Christophe Joseph Richard Gillain Remy
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Abstract
A stator vane assembly for a compressor of an aircraft turbine engine includes an inner shroud, an outer shroud, and stator vanes. The stator vanes are attached only to the inner shroud and are in non-immobilizing mechanical contact with the outer shroud.
Claims12
An aircraft turbine engine comprising a first compressor having a stator vane assembly comprising:
- an internal shroud,
- an external shroud, and
- stator vanes,
- wherein the stator vanes are attached only to the internal shroud and are in non-immobilizing mechanical contact with the external shroud;
- wherein the external shroud comprises a groove receiving radially external ends of the stator vanes;
- wherein the groove extends axially to a downstream end of the external shroud.
3 more elements
Dependencies are inferred from the claim text.