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Improvements relating to ram air turbine driven auxiliary power generators

机译:与冲压空气涡轮机驱动的辅助发电机有关的改进

摘要

829,100. Ram air turbines. PLESSEY CO. Ltd. April 17, 1957 [Jan. 17, 1956], No. 1526/56. Class 110 (3). [Also in Group XXXIII] A generator of auxiliary power for an aircraft is arranged to be driven through gearing alternatively by a ram air turbine and a self-contained emergency power unit. A ram air turbine 1 drives through a hollow shaft 5 a member 8 attached to the planet gears 11 of an epicyclic gear formed by the sunwheel 9, a ring gear 10 and planet gears 11. The ring gear 10 is locked by freewheel mechanism 12 against rotation in the direction in which the turbine wheel 1 rotates so that the turbine drives the output shaft 7 connected to a generator unit 13 which must be driven by a prime mover to produce output and which may be, for example, an electrical generator, an hydraulic pump, a compressor, or any other source of servo-power for the aircraft. When the speed of the aircraft is insufficient to supply the required power, a supplementary turbine 14 is put into service. This turbine is preferably a gas turbine and is driven by the combustion of a monofuel such as isopropyl nitrate. The turbine 14 drives the shaft 7 through an epicyclic gear formed by the sun-wheel 15, planet-wheels 18, and outer ring gear 16. The ring gear 16 is prevented from rotating in the direction of rotation of the shaft 6 by the freewheel mechanism 17. During flight at high speeds, the member 19 can freely rotate so that no power is used to drive the turbine 14. At low air speeds, the ring gear 10 freely rotates so that no power is used to drive the turbine 1. In a modification, the member 19 drives the ring gear 10, the freewheel mechanisms 12 and 17 are omitted, the ring gear 16 fixed in the housing 3 and freewheel mechanisms are provided to prevent reverse rotations of the shafts 5, 6. In this case, the amount of power required from the turbine 14 is reduced at those speeds where the power of the turbine 1 is only slightly less than the power required for driving the generator 13.
机译:829,100。冲压空气涡轮机。 PLESSEY CO。Ltd. 1957年4月17日[Jan. 1956年1月17日],第1526/56号。 110级(3)。 [也属于第XXXIII组]飞机辅助动力发电机被布置为通过齿轮传动来替代地由冲压空气涡轮机和独立的应急动力装置驱动。冲压空气涡轮机1通过空心轴5驱动连接到由太阳轮9,齿圈10和行星齿轮11形成的行星齿轮的行星齿轮11的构件8。齿圈10通过飞轮机构12锁定在沿涡轮机叶轮1旋转方向旋转,从而涡轮机驱动输出轴7,该输出轴连接至发电机单元13,该发电机单元13必须由原动机驱动以产生输出,并且该输出轴7例如可以是发电机,液压泵,压缩机或飞机的任何其他伺服动力源。当飞机的速度不足以提供所需的功率时,辅助涡轮机14投入使用。该涡轮机优选是燃气涡轮机,并且通过单燃料例如硝酸异丙酯的燃烧来驱动。涡轮14通过由太阳轮15,行星齿轮18和外齿圈16形成的行星齿轮来驱动轴7。通过飞轮防止齿圈16沿轴6的旋转方向旋转。在高速飞行中,构件19可以自由旋转,从而不使用动力来驱动涡轮14。在低空气速度下,齿圈10自由旋转,从而不使用动力来驱动涡轮1。在一种变型中,构件19驱动齿圈10,省去了飞轮机构12和17,固定在壳体3中的齿圈16,并且设置了飞轮机构以防止轴5、6的反向旋转。因此,在涡轮1的功率仅略小于驱动发电机13所需的功率的那些速度下,涡轮14所需的功率量减少。

著录项

  • 公开/公告号GB829100A

    专利类型

  • 公开/公告日1960-02-24

    原文格式PDF

  • 申请/专利权人 THE PLESSEY COMPANY LIMITED;

    申请/专利号GB19560001526

  • 发明设计人 MOSS NORMAN;TROWBRIDGE DAVID ROY;

    申请日1956-01-17

  • 分类号F01D15/10;

  • 国家 GB

  • 入库时间 2022-08-23 19:05:37

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