Aircraft dual-flow turbine engine assembly, the assembly being equipped with incidence-controlled air discharge fins

An aircraft dual-flow turbine engine assembly, comprising:

• an inner shell configured to externally define a primary flow path of gas flow of the turbine engine;
• an outer shell configured to internally define a secondary flow path of gas flow of the turbine engine;
• at least one air discharge duct extending between the inner shell and the outer shell the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins,
• wherein at least one of said discharge fins are movably mounted so as to be able to be incidence-controlled between a propulsion position, and a thrust reversal position,
• wherein the assembly is designed to move the discharge fins in the propulsion position, such that the discharge air flow, from the primary flow, is introduced into the secondary flow path from the outlet orifice along an introduction direction comprising an axial component from upstream to downstream, axially co-current with the secondary air flow flowing in the secondary flow path of the turbine engine in the normal propulsion configuration, and
• wherein the assembly is also designed to move the discharge fins in the thrust reversal position, such that the discharge air flow, from the primary flow, is introduced into the secondary flow path from the outlet orifice along an introduction direction comprising an axial component from downstream to upstream, axially co-current with the counter-thrust gas flow flowing in the secondary flow path of the turbine engine in the thrust reversal configuration.