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公开(公告)号：US4863354A
公开(公告)日：1989-09-05
申请号：US253760
申请日：1988-10-05
CPC分类号： B64C11/14 , F02C7/047 , F05D2200/221 , Y02T50/672
摘要： A nose cowl or spinner is provided for a fixed, non-rotatable central hub of a turbojet engine having assembly means that facilitate the attachment and detachment of the nose cowl to the central hub, and provides a readily visible indication of whether or not the nose cowl has been properly assembled to the hub. The nose cowl has a smooth outer surface to provide undisturbed air flow into the turbojet engine compressor and defines means to circulate heated air to prevent icing of the external surface. An inner cowl member is attached to a bearing cover of the central hub in a non-rotatable manner, an outer cowl member is axially locked to the central hub so as to be concentrally arranged about the inner cowl member, and a locking device is used to lock the inner and outer cowl members together to prevent inadvertent rotation of the outer cowl member.
摘要翻译： 提供了一种用于涡轮喷气发动机的固定的，不可旋转的中心轮毂的鼻罩或旋转器，其具有便于将鼻罩安装和拆卸到中心轮毂的组装装置，并且提供了鼻子 整流罩已正确组装到集线器。 鼻罩具有光滑的外表面，以提供未受干扰的空气流入涡轮喷气发动机压缩机，并且限定了循环加热空气以防止外表面结冰的装置。 内罩壳部件以不可旋转的方式附接到中心轮毂的轴承盖上，外整流罩部件轴向地锁定到中心轮毂，以便围绕内整流罩部件同心地布置，并且使用锁定装置 以将内外罩组件锁定在一起以防止外罩组件的意外旋转。
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公开(公告)号：US4972671A
公开(公告)日：1990-11-27
申请号：US349759
申请日：1989-05-10
CPC分类号： F01D25/16 , F01D17/162 , F01D9/065
摘要： An aircraft turbo-engine having an intake grille formed by radial struts disposed between inner and outer rings, each of said radial struts being in two parts, an upstream, fixed structural first part, and a downstream second part pivoted on said first part and forming an adjustable flap which constitutes an intake guide vane, all of said struts having the same cross-section as each other and at least some of the struts incorporating a pipe for the passage of oil, those oil pipe carrying struts each having its structural first part divided by a radial portion into an upstream chamber for the passage of hot air and a downstream chamber which is open along the length of its trailing edge and which receives the oil pipe.
摘要翻译： 一种飞机涡轮发动机，其具有由设置在内环和外环之间的径向支柱形成的进气格栅，每个所述径向支柱分成两部分，上游固定结构第一部分和在所述第一部分上枢转的下游第二部分，并形成 构成进气引导叶片的可调整的挡板，所有的支柱具有彼此相同的横截面，并且至少一些支柱结合有用于油通过的管子，那些承载支柱的油管各自具有其结构的第一部分 由径向部分分成用于热空气通过的上游室和沿其后缘的长度敞开并接收油管的下游室。
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