Helicopter turbine engine subassembly and helicopter turbine engine comprising such a subassembly

Abstract

Turbine engine subassembly (10) intended for a helicopter, comprising a primary outlet nozzle (12) for discharging an exhaust gas stream (F1), which comprises an outer casing (14) and an inner cone (16), these being arranged concentrically around a longitudinal axis (X) and connected to one another by radial arms (18), the casing (14) surrounding the cone (16) and defining between them an annular duct (C) for the flow of the stream (F1). The subassembly comprises a distributor (20) surrounding the casing (14) and configured so that at its inlet (20a) it receives a cooling-air stream (F2) having a temperature lower than the temperature of the stream (F1) and at its outlet it distributes the stream (F2) to inside the radial arms (18). The inner cone has an outer wall (16a; 16b') in which one or more openings (O) are arranged to allow the air of (F1).