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公开(公告)号：US4235303A
公开(公告)日：1980-11-25
申请号：US962714
申请日：1978-11-20
CPC分类号： B64D33/02 , F02C7/045 , F04D29/663 , B64D2033/0206 , F05D2250/283 , Y02T50/671 , Y10T428/24149
摘要： Combination bulk absorber-honeycomb acoustic panels particularly adapted for use in the inlet and fan air duct of a fan jet engine are disclosed. Each panel comprises a broadband noise-suppressing bulk absorber layer mounted between a back sheet and a perforated septum; and, a narrow band noise-suppressing honeycomb layer mounted between the septum and a perforated face sheet. The panels are mounted in an engine such that the perforated face sheet interfaces with airflow in the inlet or the fan air duct, as the case may be, whereby the face sheet, honeycomb layer and septum protect the bulk absorber from deterioration by isolating the high speed inlet and fan air duct airflows from the bulk absorber layer.
摘要翻译： 公开了特别适用于风扇喷气发动机的入口和风扇风道的组合散装吸收器 - 蜂窝式隔音板。 每个面板包括安装在背板和穿孔隔膜之间的宽带噪声抑制散装吸收层; 以及安装在隔膜和穿孔面片之间的窄带噪声抑制蜂窝层。 面板安装在发动机中，使得穿孔面板与入口或风扇空气管道中的气流（视情况而定）相接触，由此面板，蜂窝层和隔膜通过隔离高度 高速入口和风扇风道从散装吸收层的气流。
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公开(公告)号：US4155221A
公开(公告)日：1979-05-22
申请号：US754140
申请日：1976-12-27
CPC分类号： F02C7/045 , F04D29/681
摘要： This invention is an improved turbofan engine having a variable geometry fan duct which reduces stator source noise emitted from the engine. Attached to the inner wall of the fan casing near the fan stators is a pneumatically actuated annular membrane having two operating positions. In the cruise position, the membrane is forced radially inward to press against the radially outermost tips of the fan stators. In the second position, used during approach and takeoff, the membrane is drawn against a recessed portion in the fan casing, thereby creating an annular passageway between the stator tips and the casing. When the membrane is in this position, turbulent flow from the rotor blade tips which would normally impinge on the stators is directed through the annular passageway.
摘要翻译： 本发明是一种改进的涡轮风扇发动机，其具有可变几何形状的风扇管道，其减少了从发动机排出的定子源噪声。 在风扇定子附近的风扇壳体的内壁附近是具有两个操作位置的气动致动的环形膜。 在巡航位置，膜被径向向内压迫以抵抗风扇定子的径向最外端。 在第二位置，在接近和起飞期间使用的膜被拉到风扇壳体中的凹陷部分，从而在定子尖端和壳体之间形成环形通道。 当膜处于该位置时，来自转子叶片尖端的通常冲击定子的湍流被引导通过环形通道。
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