发明名称 Arrangement of a turbo fan gas turbine engine, a pylone for being attached on an aircraft structure and a suspension of the turbo fan gas turbine engine on the pylon
摘要 <p>The suspension has a front attachment unit (71) placed between a hub of an intermediate case (7) and an engine pylon (6) of an aircraft, and a rear attachment unit (81) placed between an exhaust casing (8) and the pylon. A connection unit i.e. connecting rod (11), rigidly connects the intermediate case to the pylon. The rear attachment unit includes a compensation unit to compensate variations of diameter of the exhaust casing in a manner to maintain an axis of the exhaust casing coaxial to an axis of the intermediate case during different flying phases of the aircraft.</p>
申请公布号 EP2082961(A1) 申请公布日期 2009.07.29
申请号 EP20090151190 申请日期 2009.01.23
申请人 SNECMA 发明人 BALK, WOUTER
分类号 B64D27/26 主分类号 B64D27/26
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