A gas turbine engine (10) comprises a support structure (43) for attaching the engine to an aircraft pylon (13) at front, middle and rear attachment locations of the aircraft pylon (13). The support structure includes a front mount (31) coupled to the engine and configured to be attached to the pylon at a front attachment location, and a rear mount coupled to the core housing (42) and configured to be attached to the pylon at a rear attachment location, each of the front and rear mounts is configured to transfer lateral and vertical loads from the engine to the pylon, and the rear mount is spaced apart from the front mount such that yaw and pitch torques are also transferred from the engine to the pylon through the front and rear mounts. The support structure further includes an axial load transfer device (29) configured to transfer an axial load from the engine to the pylon and a rolling torque transfer formation (33) configured to transfer a rolling torque from the core housing to the pylon.
一种气体涡轮引擎(10)包括支撑结构(43),该支撑结构用于将引擎在飞行器挂架(13)的前部、中部和后部附接位置处附接到飞行器挂架。该支撑结构包括前安装架(31)和后安装架,该前安装架接合到引擎并被构造成在前部附接位置处附接到挂架,该后安装架接合到核心壳体(42)并被构造成在后部附接位置处附接到挂架,前安装架和后安装架中的每一者被构造成将横向载荷和竖直载荷从引擎传递到挂架,并且后安装架与前安装架间隔开,使得偏航扭矩和俯仰扭矩也通过前安装架和后安装架从引擎传递到挂架。该支撑结构还包括被构造成将轴向载荷从引擎传递到挂架的轴向载荷传递装置(29)和被构造成将滚动扭矩从核心壳体传递到挂架的滚动扭矩传递构造(33)。
Support structure for attaching gas turbine engine to aircraft pylon
用于将气体涡轮引擎附接到飞行器挂架的支撑结构
2023-06-23
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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