The invention belongs to the field of application of large turboprop passenger aircraft engine vibration reduction mounting technologies, and particularly relates to a large turboprop passenger aircraft engine vibration reduction mounting system. The turboprop engine is provided with a front mounting surface close to one side of a propeller and a rear mounting surface close to one side of a turbine combustion chamber, the front mounting surface is provided with two mounting points and three front mounting joints, the rear mounting surface is provided with two rear mounting joints, and mechanical or hydraulic torque compensation devices are mounted at the two mounting points; the three front mounting sections comprise a first front mounting section and two second front mounting sections, the first front mounting section is located at the vertex of the front mounting surface, the two second front mounting sections are arranged in a bilateral symmetry mode along the longitudinal vertical plane of the engine, a front upper damping device is mounted at the first front mounting section, and front side damping devices are mounted at the second front mounting sections; the two rear installation joints are arranged in a bilateral symmetry mode along the longitudinal vertical plane of the engine, and rear side vibration reduction devices are installed at the two rear installation joints.
本申请属于大型涡桨客运飞机发动机减振安装技术应用领域,特别涉及一种大型涡桨客运飞机发动机减振安装系统。包括:涡桨发动机具有靠近螺旋桨一侧的前安装面,以及靠近涡轮燃烧室一侧的后安装面,前安装面上具有两个安装点以及三个前安装节,后安装面上具有两个后安装节,其中,在两个安装点处安装有机械式或液压式扭矩补偿装置;三个前安装节包括一个第一前安装节以及两个第二前安装节,第一前安装节位于前安装面的顶点,两个第二前安装节分别沿发动机纵垂面左右对称布置,在第一前安装节处安装有前上减振装置,在第二前安装节处安装有前侧减振装置;两个后安装节分别沿发动机纵垂面左右对称布置,在两个后安装节处安装有后侧减振装置。
Large turboprop passenger aircraft engine vibration reduction installation system
一种大型涡桨客运飞机发动机减振安装系统
2023-05-02
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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