System and method for cooling a fluid of a lubrication or cooling circuit of a drive unit of an aircraft, and aircraft propulsion engine provided with such a cooling system

Abstract

The invention relates to a system for cooling a fluid of a circuit () for lubricating a propulsion engine () of an aircraft, the engine comprising a nacelle () which extends in a longitudinal direction (X) between an air inlet opening () and an ejection nozzle (), a turbomachine () having a casing () secured inside said nacelle by rectifier arms (), and a fan () arranged at said air inlet opening () of said nacelle, upstream of said turbomachine (), and designed to be able to generate a primary air flow feeding said turbomachine and a secondary air flow feeding a channel, referred to as a secondary channel (), formed between said nacelle () and said casing () of said turbomachine, characterized in that said cooling system comprises a skin exchanger () which is arranged on an inner wall of said nacelle (), longitudinally between said air inlet opening () of said nacelle and said rectifier arms (), said skin exchanger being in fluid communication with said fluid circuit and designed to be able to provide heat exchanges between said lubricating fluid and the air flowing through said secondary channel.