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发明授权
CN101070858B 一种飞机发动机压气机的轮盘-叶片装置 有权

一种飞机发动机压气机的轮盘-叶片装置
摘要：
本发明涉及飞机发动机压气机的一种轮盘-叶片装置，包括一个轮盘(2)和若干采用锤形件连接的(6)叶片，每个叶片包括一个叶根，叶根带有一个位于翼面前缘的上游支撑面(32)和一个位于翼面后缘的下游支撑面(34)，轮盘提供有一个圆周槽(10)，槽内通过支撑面固定了每个叶片的叶根。根据本发明，对于每个叶片来讲，下游支撑面(34)在某个偏移(42)方向上与上游支撑面(32)形成圆周偏移，该偏移方向对应于翼面的后缘(22)和前缘(20)之间的偏移方向。
摘要（英）：

The invention relates to a disk/blade device for the engine compressor of an aircraft, comprising a disk (2), and a set of vanes (6) connected using hammer piece. Each blade comprises a vane foot with an upstream carrier surface (32) and a downstream carrier surface (34) that is located at the level of a side of the edge of the blade. The disk has a circumferential slot (10) in which the vane foot is retained. The surface (34) is shifted circumferentially from the surface (32) along a given shifting direction (42), for each vane, and the said offset direction is corresponding with the offset direction between posterior border (22) and anterior border (20) of airfoil.

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