Aircraft propulsion assembly comprising a plate heat exchanger, of hexagonal longitudinal section, positioned in a bifurcation

An aircraft propulsion assembly comprising:

• an engine;
• a nacelle positioned around the engine;
• an annular duct, which is defined by the engine and the nacelle, in which a bypass flow of cold air can flow;
• at least one bifurcation connecting the engine and the nacelle, wherein the at least one bifurcation has:
• a leading edge;
• and
• a primary structure of a pylon housed in the at least one bifurcation, wherein the pylon is configured to connect the engine to an aircraft wing;
• and
• at least one heat exchange device, which comprises:
• a heat exchanger comprising a first hot air circuit connecting a first inlet and a first outlet, and comprising a second cold air circuit connecting a second inlet and a second outlet;
• a hot air supply duct connected to the first inlet and configured to take hot air from the engine;
• a hot air outlet duct connected to the first outlet and configured to convey hot air towards at least one item of aircraft equipment;
• a cold air supply duct connected to the second inlet and configured to take cold air from the bypass flow;
• and
• an exhaust duct connected to the second outlet and configured to expel the air out of the aircraft;
• wherein the heat exchanger is a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation.