Patent ID: 8166768

Claim:
A method for operating an aircraft engine, comprising: directing exhaust gas products from an aircraft turbofan engine along a first flow path of a corresponding engine nozzle; directing bypass air around the engine and along a second flow path of the engine nozzle; and passively directing gas (a) from the first flow path to the second flow path at intermittent circumferential locations, (b) from the second flow path to an ambient air stream at intermittent circumferentially extending and circumferentially spaced apart locations, or (c) both (a) and (b), wherein passively directing the gas includes: at a first circumferential location, directing a first quantity of gas through a first flow passage at a first angle having a greater circumferential component in a first circumferential direction than in a second circumferential direction opposite the first circumferential direction; and at a neighboring second circumferential location, directing a second quantity of gas through a second flow passage at a second angle having a greater circumferential component in the second circumferential direction than in the first circumferential direction.