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1.发明申请公开(公告)号：US20120198853A1
公开(公告)日：2012-08-09
申请号：US13501526
申请日：2010-10-06
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23D11/36 , F23D2900/00016 , F23R3/343
摘要： A fuel injector device for an annular combustion chamber of a turbine engine, including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular ring mounted in an annular chamber, together with a thermal insulation mechanism insulating the front face and including an annular cavity formed around the injection orifices between the front face of the annular ring and a front wall of the annular chamber and configured to be filled in operation with air or with coked fuel.
摘要翻译： 一种用于涡轮发动机的环形燃烧室的燃料喷射器装置，包括供给喷射器的先导电路和形成在安装在环形室中的环形圈的前面中的多点回路进料喷射孔以及绝热机构绝缘 前表面并且包括围绕环形环的前表面和环形室的前壁之间的注入孔周围形成的环形空腔，并被构造成在空气或焦化燃料中充满操作。
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2.发明申请公开(公告)号：US20120055164A1
公开(公告)日：2012-03-08
申请号：US13255772
申请日：2010-03-15
CPC分类号： F23R3/10
摘要： Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated with each injection system (32), comprising at least one wall (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), and an air inlet opening (88) formed at the upstream end of the air manifold (100) and opening radially outwards from an axis (44) of said injection system.
摘要翻译： 安装在涡轮机上的环形燃烧室（10），包括腔室端壁（22），围绕燃烧室（10）的轴线（34）周向分布的多个空气和燃料喷射系统（32），并安装 在所述腔室端壁（22）上，以及与每个注射系统（32）相关联的空气歧管（100）包括安装在腔室端壁（22）上并在上游侧突出的至少一个壁（96,98） 形成围绕燃烧室（10）的轴线（34）的圆周气流的障碍物，以及形成在空气歧管（100）的上游端并从轴线径向向外开口的空气入口（88） （44）。
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