Aircraft fluid cooling system and an aircraft provided with...

B - Operations – Transporting – 64 – D

Patent

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Details

B64D 33/10 (2006.01)

Patent

CA 2546685

The inventive fluid cooling system for an aircraft (30) comprises an air-cooled heat exchanger (40) through which said fluid passes and which is provided with air intake means (52) and air exhaust means (54). Said air-cooled heat exchanger (40) is placed in a reception area of the fairing (34) of a guiding rail of wing flaps (36) connected to a wing (32) of said aircraft. Said means (52) for air intake into the air-cooled heat exchanger (40) is connected to air intake means (42) crossing the external covering (46) of the fairing (34) and said air exhaust means (54) of the air-cooled heat exchanger (40) is connected to air exhaust means (44) which exits from said external covering (46) in such a way that the air outside the aircraft (30) passes through said air-cooled heat exchanger (40), thereby cooling said fluid.

Le système de refroidissement d'un fluide d'un aéronef (30) comporte un échangeur de chaleur à air (40) traversé par ce fluide, ledit échangeur de chaleur à air (40) comprenant un moyen d'introduction d'air (52) et un moyen d'évacuation d'air (54). Cet échangeur de chaleur à air (40) est implanté dans un logement situé dans un carénage (34) de rail de guidage de volets (36) associés à une aile (32) de cet aéronef, ledit moyen d'introduction d'air (52) dans l'échangeur de chaleur à air (40) étant raccordé à un moyen d'entrée d'air (42) traversant le revêtement extérieur (46) du carénage (34) et ledit moyen d'évacuation d'air (54) dudit échangeur de chaleur à air (40) étant raccordé à un moyen de sortie d'air (44) débouchant à l'extérieur dudit revêtement extérieur (46) de façon à ce que de l'air extérieur à l'aéronef (30) traverse cet échangeur de chaleur à air (40) pour refroidir ledit fluide.

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