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1. 发明授权

US4035535A Sound attenuating structure 失效
标题翻译：声衰减结构
公开(公告)号：US4035535A
公开(公告)日：1977-07-12
申请号：US654706
申请日：1976-02-02
申请人： Maurice Ian Taylor
发明人： Maurice Ian Taylor
IPC分类号： E04B1/84 , G10K11/172 , B32B3/12
CPC分类号： G10K11/172 , Y10T428/236 , Y10T428/24149 , Y10T428/24273
摘要： Use of bulk sound absorber-backed spaced-cell honeycomb structures as sound attenuating liners in the flow ducts of gas turbine engines involves the disadvantage that the bulk absorber may soak up water or fuel present in the honeycomb after entry thereinto from the flow duct. In order to drain away liquid before it comes into contact with the bulk absorber, each honeycomb cell communicates with surrounding cells via apertures in the cell walls through which the liquid can drain, and a perforated sheet is provided between the honeycomb layer and the bulk absorber layer. The perforations are such that sound can enter the bulk absorber layer, but the liquid does not, each perforation being a hole having a peripheral flange which protrudes away from the bulk absorber layer into the interior of a respective cell.
摘要翻译：在燃气涡轮发动机的流动管道中使用大体积吸声器支撑的隔间蜂窝结构作为声音衰减衬垫的缺点在于，散料吸收器可以从进入管道的过程中吸收存在于蜂窝中的水或燃料。为了在与散料吸收器接触之前排出液体，每个蜂窝单元通过细胞壁中的孔通过其周围的细胞连通，液体可以通过该孔排出，并且在蜂窝层和散装吸收体之间设置穿孔片层。穿孔使得声音可以进入体吸收层，但是液体不是，每个穿孔是具有周边凸缘的孔，该周边凸缘从本体吸收层突出到相应电池的内部。

2. 发明授权

US07967219B1 Thrust nozzle for a gas turbine engine 失效
标题翻译：燃气轮机的推进喷嘴
公开(公告)号：US07967219B1
公开(公告)日：2011-06-28
申请号：US06116026
申请日：1980-01-11
申请人： Maurice Ian Taylor
发明人： Maurice Ian Taylor
IPC分类号： B63H11/10 , B64C15/00
CPC分类号： B64C29/0066 , B64D33/04 , F02K1/004 , F02K1/12 , F02K3/025
摘要： Elbow nozzles in VTOL aircraft engines, are highly stressed when operating, in that they act as high pressure vessels.The invention provides a means for varying the outlet area of such a nozzle without weakening its structure. A single flap is inserted inside the nozzle and connected to the nozzle extremity for pivoting about an axis which lies across the outlet between a position wherein its edges seal against the nozzle side and so restrict the nozzle outlet area and, a position wherein it lies parallel with a wall of the nozzle so that exhaust gas can pass both sides and out of a bigger outlet.
摘要翻译： VTOL飞机发动机的弯头喷嘴在运行时受到高度的压力，因为它们作为高压容器。本发明提供了一种用于改变这种喷嘴的出口面积而不削弱其结构的装置。单个翼片插入喷嘴内部并且连接到喷嘴末端，用于围绕位于出口处的轴线枢转，该轴线在其边缘与喷嘴侧密封并且因此限制喷嘴出口区域的位置以及其平行的位置具有喷嘴的壁，使得废气可以通过两侧并从更大的出口出来。

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