A convergent-divergent exhaust nozzle for a turbofan engine of a supersonic aircraft and method for adjusting the nozzle throat area in a thruster of a turbofan engine

摘要

The invention relates to a convergent-divergent exhaust nozzle (1) for a turbofan engine of a supersonic aircraft, wherein the exhaust nozzle (1) has an inner wall (11) and a flow channel (15) having a nozzle throat surface (A81, A82) and a nozzle exit surface (A9 ) trains. A lining ring (2) which is displaceable in the axial direction between a first position and a second position is provided, wherein the inside wall (11) of the exhaust nozzle (1) and the lining ring (2) are designed and positioned relative to one another such that the lining ring (2 ) in the first position radially spaced from the inner wall (11), wherein an annular bypass channel (3) is provided which extends between the lining ring (2) and the inner wall (11) of the exhaust nozzle (1), and the lining ring ( 2) abuts the inner wall (81) in the second position. According to a further aspect of the invention, the invention relates to a thrust nozzle with a displaceable in the axial direction nozzle outlet ring.