Aircraft turboshaft engine compressor comprising a device for immobilising a retaining annulus

• Main Authors: Dumas, Lilian Yann, Robin, Noël Joseph Camille, Sevi, Guillaume, Bergon, Blaise, Van De Kerckhove, Thomas Etienne Camille Marie, Delahaye, Thomas Nolwenn Emmanuel, Jablonski, Laurent
• Format: Patent
• Language: English
• Published: 02.01.2024
• Subjects: BLASTING; ENGINE PLANTS IN GENERAL; HEATING; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.