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Hydraulic system for adjustable pitch aeronautical propeller

机译:可调螺距航空螺旋桨液压系统

摘要

868,419. Variable pitch propellers. UNITED AIRCRAFT CORPORATION. Dec. 16, 1957 [Dec. 18,1956], No. 39014/57. Class 114. Variable-pitch propellers are adjusted by an hydraulic motor fed with fluid under the action of a control valve, normally adjusted by a speed governor driven from the engine, and a feathering valve. The housing 14 contains the hydraulic motor which varies the pitch of the blades 12 through suitable cam and gear mechanism. The feathering valve 32 when in its " closed position (as shown) allows communication between the fluid supply source fed to conduit 28 and conduit 28a, which leads to control valve 34, and also connects conduits 26a, 26 and 30a, 30, conduit 26 feeding fluid to the hydraulic motor to decrease the pitch and conduit 30 supplying fluid to increase the pitch. The control valve 34 when in its " central " position (as shown) terminates the flow through conduit 28a from the supply source and this valve is moved by a governor 48, driven from gearing 42, against the action of spring 52 to connect conduits 28a, 30a to provide fluid to the hydraulic motor to increase the pitch, and when the spring loading is sufficient to overcome the governor action conduit 28a communicates with conduit 26a to decrease the pitch. The supply of hydraulic fluid is provided by a main pump 62 and a standby pump 64 which deliver fluid from a tank 56 supplied by pumps 58 from a tank 54. The main pump 62 delivers fluid past filter 66 and conduit 22 to the conduit 28 which is provided with a branch conduit 94 leading to a normally closed valve 92. The standby pump 64 delivers past filter 68 to a conduit 70 which communicates when valve 32 is " closed " with a conduit 70a leading to a spring loaded valve 72 having a small orifice 88, the main delivery flows through conduit 78 to a drain conduit 80 communicating with the tank 56 while part of the flow passes through the orifice 88 to conduit 82 which communicates through passage 84 of control valve 34, when in its " central " position, with conduit 86 which leads to the drain conduit 80. When control valve 34 is moved to vary the pitch it closes conduit 82 and the pressure in this conduit increases to the value existing in conduit 70a thus allowing valve 72 to close under the influence of its spring, thus the pressure in conduit 70 increases and opens a non-return valve 74 thus permitting the delivery from standby pump 64 to join the delivery from the main pump 62 whenever the pitch is changed. Similarly, when the feathering valve 32 is " opened " conduit 70 is closed and the two deliveries combine as above. Specifications 683,906, 724,284 and 824,078 are referred to.
机译:868,419。可变螺距螺旋桨。联合飞机公司。 1957年12月16日18,1956],第39014/57号。 114类。在控制阀的作用下,由液压马达对可变螺距螺旋桨进行供油,控制阀通常由发动机驱动的限速器和羽化阀进行调节。壳体14包含液压马达,该液压马达通过合适的凸轮和齿轮机构来改变叶片12的螺距。羽状阀32在其“关闭位置”(如图所示)时,允许输送到导管28的流体供应源和导管28a之间的连通,通向控制阀34,并且还连接导管26a,26和30a,30,导管26将液压油输送到液压马达以减小螺距,导管30输送流体以增加螺距当控制阀34处于“中心”位置(如图所示)时,它终止了从供应源通过导管28a的流动,该阀被移动由调速器48驱动,该调速器由齿轮42驱动,抵抗弹簧52的作用以连接导管28a,30a,以向液压马达提供流体以增加螺距,并且当弹簧载荷足以克服调速器作用时,导管28a与液压流体的供应由主泵62和备用泵64提供,主泵62和备用泵64从储罐56输送流体,主泵62从储罐54输送泵58。通过过滤器66和导管22到达导管28,导管28设有通向常闭阀92的分支导管94。备用泵64将经过过滤器68的流体输送到导管70,当阀32被导管“关闭”时,导管70连通。在通向具有小孔88的弹簧加载阀72的图70a中,主输送流经导管78流到与水箱56连通的排放导管80,而一部分流量通过孔88流向导管82,该导管82通过阀的通道84连通。控制阀34在其“中心”位置时,具有通向排放导管80的导管86。当控制阀34移动以改变螺距时,它关闭导管82,并且该导管中的压力增加到导管中存在的值因此,阀70a使阀72在其弹簧的作用下关闭,从而导管70中的压力增加并打开单向阀74,从而允许备用泵64的输送与阀70的输送相结合。每当改变螺距时,主泵62就运转。类似地,当羽化阀32“打开”时,导管70关闭,并且两个输送如上所述结合。参考规格683,906、724,284和824,078。

著录项

  • 公开/公告号GB868419A

    专利类型

  • 公开/公告日1961-05-17

    原文格式PDF

  • 申请/专利权人 UNITED AIRCRAFT CORPORATION;

    申请/专利号GB19570039014

  • 发明设计人

    申请日1957-12-16

  • 分类号B64C11/34;B64C11/42;

  • 国家 GB

  • 入库时间 2022-08-23 18:21:25

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