Patent ID: 8157050
Filing Date: 2012-04-17
Classification: F02K,F05D

Abstract:
1. An aircraft jet engine, comprising: a wall surrounding a first gas stream that is ejected at a downstream end of the wall along a longitudinal axis, a second gas stream flowing outside the wall in a direction of ejection of the first gas stream; at least one duct arranged at a periphery of the downstream end of the wall and configured to eject a fluid jet to interact with the first or the second gas stream, the at least one duct comprising a terminal part including at a free end thereof an outlet opening through which the fluid jet is ejected, wherein the terminal part successively comprises a first straight duct portion aligned along a median axis and a second duct portion forming a bend in relation to the straight portion, the second duct portion including the free end including the outlet opening and being sufficiently close to the median axis of the first portion so as to impart to the terminal part a reduced space requirement in a direction of formation of the bend, and the outlet opening of the second duct portion is at a distance measured between the median axis and a middle of the outlet opening which is not greater than twice a value of a radius of the first duct portion.