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instabilities to the combustion in a combustion chamber; the combustion chamber of a gas turbine engine according to this

机译：燃烧室内燃烧的不稳定性;根据此的燃气涡轮发动机的燃烧室

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The method involves carburizing a combustion air supplying system with an axial conduit and a spin part (6) inducing component azimuth speed at air flow. The axial conduit is emerged out from a bottom wall (2) of an annular combustion chamber (21). The spin part is arranged at distance (L) of the bottom wall of the chamber. The distance of the bottom wall is adjusted to create phase difference between an acoustic wave and an aerodynamic oscillation generated through the spin part by the acoustic wave. An independent claim is also included for a combustion chamber of a gas turbine engine, comprising a basic wall.

机译：该方法包括使具有轴向导管和旋转部分（6）的燃烧空气供应系统渗碳，该旋转空气在空气流处引起分量方位角速度。轴向导管从环形燃烧室（21）的底壁（2）伸出。旋转部分布置在腔室的底壁的距离（L）处。调节底壁的距离以在声波和通过声波通过旋转部分产生的空气动力学振荡之间产生相位差。还包括具有基本壁的燃气涡轮发动机的燃烧室的独立权利要求。

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公开/公告号FR2961292B1

专利类型
公开/公告日2014-01-31

原文格式PDF
申请/专利权人 SNECMA;CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE;ECOLE CENTRALE DE PARIS;
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申请/专利号FR20100054691
发明设计人 THIERRY SCHULLER;SEBASTIEN ROUX;PAUL PALIES;DANIEL DUROX;SEBASTIEN CANDEL;THOMAS OLIVIER MARIE NOEL;
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申请日2010-06-14
分类号F23R3/16;F23R3/50;F02C7/22;
国家 FR
入库时间 2022-08-21 15:36:47

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