Aircraft engine exhaust nozzle

Abstract From the Canadian patent

Aircraft engine exhaust nozzle, including a tubular body with two output channels delimiting a primary upstream flow vein for gas divided downstream into two parallel secondary gas flow veins the output channels including the means to direct the thrust comprising gas injection housings in the pre-cited secondary veins these housings being affixed onto the lateral walls of the output channels in an intermediate space formed between the downstream parts of the output channels and each including a window aligned with a slit formed in a lateral wall of the corresponding output channel and the controlled regulation means for the rate of gas injected by the window into the secondary vein.