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Invention Publication
CN101772635A 用于飞行器涡轮喷气发动机的、装备有限制喷射噪音的用于产生主气流湍流的装置的气体喷射锥、和涡轮喷气发动机及其相关发动机组件 失效 - 权利终止

用于飞行器涡轮喷气发动机的、装备有限制喷射噪音的用于产生主气流湍流的装置的气体喷射锥、和涡轮喷气发动机及其相关发动机组件
Abstract:
本发明涉及一种用于飞行器的涡轮喷气发动机的气体喷射锥(8)，该锥具有空心主体(30)，该主体的外围限定主气流环形通道的径向内壳(36)。根据本发明，所述锥还包括用于产生主气流湍流的装置(34)，该装置限制喷射噪音，该装置可移动地安装在所述主体上，以便可以从展开位置向收缩位置移动，反之亦然，在该展开位置中，该装置相对于空心主体的下游端向下游伸出，在该收缩位置中，该装置缩回该空心主体中。此外，所述装置(34)包括：圆柱形支撑体(42)，该支撑体的轴线平行于喷射锥的轴线(32)；以及至少一个由支撑体(42)支撑的翼(46)。
Abstract(English):

The present invention relates to a gas ejection cone (8) for an aircraft turbojet, the cone having a hollow main body (30) defining, on the outside, a radially inner skin (36) of an annular primary flow channel. According to the invention, it further includes a device (34) for generating turbulence in the primary flow, limiting jet noise, which is mounted so as to move on the main body so as to be able to be displaced from an extracted position in which it projects towards the downstream relative to a downstream end of the hollow main body and a retracted position in which it is retracted into its hollow main body, and vice versa. In addition, the device (34) includes a cylindrical support body (42) having an axis parallel to an axis (32) of the ejection cone, and also at least one fin (46) supported by the body (42).

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