A blade angle feedback ring assembly (200) for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly (200) comprises a feedback ring (204) coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring (204), and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.
PROPELLER BLADE ANGLE FEEDBACK ARRANGEMENT AND METHOD
ANORDNUNG UND VERFAHREN ZUR PROPELLERBLATTWINKELRÜCKMELDUNG
AGENCEMENT ET PROCÉDÉ DE RÉTROACTION D'ANGLE DE PALE D'HÉLICE
03.04.2024
Patent
Elektronische Ressource
Englisch
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