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1.发明申请公开(公告)号：US20150285500A1
公开(公告)日：2015-10-08
申请号：US14353966
申请日：2012-10-24
申请人： SNECMA
摘要： A combustion chamber module for an aircraft turbomachine, including an annular combustion chamber in which each of primary and dilution ports of an outer annular wall, which is located at least partly in a wake of a fuel injector, has a discharge coefficient higher than that of its homologous port of an inner annular wall. A method for designing such a module includes determining wakes generated by fuel injectors, and then geometrically defining air inlet ports of coaxial walls of the combustion chamber such that an air flow rate actually entering through ports of the outer wall is substantially equal to an air flow rate entering through ports of the inner wall.
摘要翻译： 一种用于飞机涡轮机的燃烧室模块，包括环形燃烧室，其中位于燃料喷射器至少部分地位于外部环形壁的主要和稀释端口中的每一个具有高于 其内部环形壁的同源端口。 用于设计这种模块的方法包括确定由燃料喷射器产生的醒来，然后确定燃烧室的同轴壁的空气入口端口，使得通过外壁的端口实际进入的空气流量基本上等于气流 速率通过内壁的港口进入。
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公开(公告)号：US09413141B2
公开(公告)日：2016-08-09
申请号：US13861825
申请日：2013-04-12
申请人： SNECMA
摘要： A spark plug for combustion chamber of a gas turbine engine including: an external body forming ground electrode, intended to be received mainly in a bypass of the combustion chamber; an internal central electrode; and an interposed insulator with clearance between the external body and the internal electrode, is provided. The spark plug terminates in a nose forming portion to be received in the flame tube of the chamber of the combustion chamber, and a semi-conductor element being interposed between the central electrode and the ground electrode at the level of said nose forming portion. The external body includes at least one cooling air inlet which communicates inside the spark plug with at least one outlet arranged at the level of the nose forming portion.
摘要翻译： 一种燃气涡轮发动机的燃烧室用火花塞，其特征在于，具有主要形成在所述燃烧室的旁路中的接地电极的外部主体， 内部中心电极; 并且提供了在外部主体和内部电极之间具有间隙的插入绝缘体。 火花塞终止在鼻部形成部分中，以容纳在燃烧室的腔室的火焰管中，并且在所述鼻部形成部分的水平处插入在中心电极和接地电极之间的半导体元件。 外部主体包括至少一个在火花塞内部连通的冷却空气入口和布置在鼻部形成部分的高度处的至少一个出口。
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