Invention Grant
US09249755B2 Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle 有权
用于定义涡轮机会聚发散喷嘴的形状的方法以及相应的会聚发散喷嘴

Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle
Abstract:
According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.
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