A system (10) is provided for an aircraft. This aircraft system (10) includes a heat exchanger (20), a lubricant flow circuit (16) and a bypass valve (24). The lubricant flow circuit (16) includes an inlet passage, an outlet passage, a heat exchanger passage (34) and a bypass passage (36). The heat exchanger passage (34) extends through the heat exchanger (20). The bypass passage (36) bypasses the heat exchanger (20). The heat exchanger passage (34) and the bypass passage (36) are fluidly coupled in parallel between the inlet passage and the outlet passage. The bypass valve (24) is fluidly coupled inline along the lubricant flow circuit (16). The bypass valve (24) is operable to regulate lubricant flow through the bypass passage (36). The bypass valve (24) includes a rotary electric motor (52).
AIRCRAFT HEAT EXCHANGER BYPASS FLOW CONTROL WITH ELECTRIC MOTOR
BYPASS-FLUSSSTEUERUNG FÜR EINEN FLUGZEUGWÄRMETAUSCHER MIT ELEKTROMOTOR
COMMANDE DE FLUX DE DÉRIVATION D'ÉCHANGEUR DE CHALEUR D'AÉRONEF AVEC MOTEUR ÉLECTRIQUE
28.05.2025
Patent
Elektronische Ressource
Englisch
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