Patent ID: 9683516
Date: 2017-06-20
CPC Classifications: F02K,F05D

Claim:
1. A turbine engine convergent-divergent propulsion nozzle comprising: an annular central element and an annular cap arranged coaxially around the annular central element so as to co-operate with the annular central element to define an annular flow channel for an engine gas stream, wherein between a throat section of the turbine engine convergent-divergent propulsion nozzle, which is the smallest cross-section of the annular flow channel, and an ejection section of the nozzle, which is a cross-section at a downstream end of the turbine engine convergent-divergent propulsion nozzle, an external profile of the annular central element and an internal profile of the annular cap in longitudinal section are modeled by curves, second derivatives of the curves relative to an axial position along the respective curve have respective radii that are identical in absolute value, and wherein the turbine engine convergent-divergent propulsion nozzle is a fixed nozzle in the annular flow channel.