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HONDA FOR A TWO-CIRCUIT TURBOREACTIVE ENGINE WITH A HIGH DEGREE OF TWO-CIRCUIT

机译：具有两回路高度的两回路涡轮发动机的本田

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摘要

1. A nacelle (100, 200) for a two-circuit turbojet engine with a high bypass ratio, containing an inner channel (9) through which a secondary flow created by the turbojet flows, and having an outer casing containing a thrust reversing device made with the possibility of alternate switching from a closed position providing the secondary flow in the inner channel in the direct jet mode (3a), to the open position with the opening in the outer casing of the hole redirecting the secondary flow into the deflected jet (3b) by actuating the means (111, 211) for thrust reversal, when In this case, the thrust reversal device in the open position partially overlaps the internal channel with the formation of a leakage flow area (S2, S3) in it, which makes it possible to flow with an adjustable leakage rate, and the specified nacelle is characterized in that in the open position the thrust reverser has a flow area (3b) reversers flow into the deflected jet and the flow area (S2, S3) of the leakage through the inner channel (9), the sum of which is essentially equal to the flow area of the secondary flow in the direct flow mode (3a) with the thrust reverser closed. ! 2. The nacelle (100, 200) according to claim 1, characterized in that the reversing flow area is obtained by displacing the movable fairing (10) having a reduced thickness and providing in the closed position the outer and inner aerodynamic continuity of the nacelle (100, 200). ! 3. The nacelle (100, 200) according to claim 1, characterized in that it is designed to accommodate a turbojet engine with a bypass ratio

机译：1.一种用于具有高旁通比的二回路涡轮喷气发动机的机舱（100、200），其包括内部通道（9），由涡轮喷气发动机产生的二次流通过所述内部通道（9）流动，并且具有包含推力反向装置的外壳可以交替选择，从处于直接喷射模式（3a）的内部通道中提供二次流的关闭位置切换到打开位置，孔的外壳中的开口将二次流重定向到偏转的喷射流中（3b）通过致动推力反向装置（111、211），在这种情况下，当推力反向装置在打开位置时部分与内部通道重叠，并在其中形成泄漏流动区域（S2，S3），这使得可以以可调节的泄漏率流动，并且特定的机舱的特征在于，在反向位置，推力反向器具有一个流动区域（3b），反向器流入偏转的射流，而反向流动区域（S2，S3）泄漏通过内部通道（9），其总和基本上等于在推力反向器关闭时在直流模式（3a）中二次流的流动面积。！ 2.根据权利要求1所述的机舱（100、200），其特征在于，通过移动具有减小的厚度的可动整流罩（10）并在闭合位置提供机舱的外部和内部空气动力学连续性来获得所述反向流动区域。（100，200）。！ 3.根据权利要求1所述的机舱（100、200），其特征在于，其被设计成容纳具有旁通比的涡轮喷气发动机。

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公开/公告号RU2008147844A

专利类型
公开/公告日2010-06-20

原文格式PDF
申请/专利权人 ЭРСЕЛЬ (FR);
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申请/专利号RU20080147844
发明设计人 ВОШЕЛЬ ГИ БЕРНАР (FR);ПОРТАЛЬ ЖАН-ФАБРИС МАРСЕЛЬ (FR);БЛЕН ЛОРАН АЛЬБЕРТ (FR);ТОРЕЛЬ КРИСТОФ (FR);
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申请日2007-04-12
分类号F02K1/72;
国家 RU
入库时间 2022-08-21 18:30:07

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