The invention provides a gas turbine engine (10) comprising a support structure (43) for attaching the engine (10) to an aircraft pylon (13). The support structure (43) comprises an engine-side abutment member (31), a pylon-side abutment member (33) abutting the engine-side abutment member (31), and a top V-shaped connection configuration (37) above the engine core (11) and a pair of side V-shaped connection configurations (39) on opposite lateral sides of the engine core (11), each V-shaped connection configuration (37, 39) being formed by a pair of connection members intersecting at an apex, the apex of the top V-shaped connection configuration (37) is joined to the top of the engine-side abutment member (31), the apex of the side V-shaped connection configuration (39) is joined to the bottom end of the engine-side abutment member (33), respectively, and the connection members extend forward from their respective apex to be joined to respective front fixing points at the core housing (42).
本发明提供了一种气体涡轮引擎(10),该气体涡轮引擎包括用于将该引擎(10)附接到飞行器挂架(13)的支撑结构(43)。该支撑结构(43)包括:引擎侧对接构件(31)、与该引擎侧对接构件(31)对接的挂架侧对接构件(33)以及位于引擎核心(11)上方的顶部V形连接构造(37)和位于该引擎核心(11)的相对横向侧上的一对侧面V形连接构造(39),每个V形连接构造(37,39)由在顶点处相交的一对连接构件形成,该顶部V形连接构造(37)的顶点接合到该引擎侧对接构件(31)的顶部,该侧面V形连接构造(39)的顶点分别接合到该引擎侧对接构件(33)的底端,并且该连接构件从其相应顶点向前延伸以接合到核心壳体(42)处的相应前固定点。
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
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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