Gas turbine engine
    2.
    发明专利
    Gas turbine engine 有权
    气体涡轮发动机

    公开(公告)号:JP2013181540A

    公开(公告)日:2013-09-12

    申请号:JP2013038265

    申请日:2013-02-28

    Abstract: PROBLEM TO BE SOLVED: To shorten a low shaft of an engine while increasing output density of the engine.SOLUTION: A gas turbine engine 20 includes a shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure turbine 62 includes inside blade sets 120 which are connected to a low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is rotated on a rotation axis in a direction opposite to the inside blade set 120 at a speed lower than the speed of the inside blade set 120. This configuration shortens the overall length of the engine 20, and makes the engine 20 have a desirable high-pressure core ratio, while maximizing the output density of the engine.

    Abstract translation: 要解决的问题:缩短发动机的低轴,同时增加发动机的输出密度。解决方案:燃气涡轮发动机20包括轴40,反向旋转低压压缩机60和反向旋转低压压缩机60, 反向旋转的低压涡轮62包括通过齿轮装置116连接到低轴40的内部叶片组120和插入在内侧叶片组120之间的外部叶片组122。 刀片组122以比内侧刀片组120的速度低的速度在旋转轴线上以与内侧刀片组120相反的方向旋转。该构造缩短了发动机20的总长度,并且使发动机20具有 期望的高压芯比,同时使发动机的输出密度最大化。

    Gas turbine engine
    4.
    发明专利
    Gas turbine engine 有权
    气体涡轮发动机

    公开(公告)号:JP2013181541A

    公开(公告)日:2013-09-12

    申请号:JP2013038266

    申请日:2013-02-28

    Abstract: PROBLEM TO BE SOLVED: To shorten the low shaft of an engine while increasing the output density of the engine.SOLUTION: A gas turbine engine 20 includes a shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure compressor 60 comprises a counter-rotating compressor hub 70 having blade stages 72, 74 and 76, and blade stages 78 and 80 of a low-speed spool 30 are inserted among the blade stages 72, 74 and 76. A transmission 82 counter-rotates the counter-rotating compressor hub 70 with respect to the low-speed spool 30. The counter-rotating low-pressure turbine 62 comprises inside blade sets 120 which are connected to a low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is rotated on a rotation axis in a direction opposite to the inside blade set 120 at a speed lower than the inside blade set 120.

    Abstract translation: 要解决的问题:缩短发动机的低轴,同时增加发动机的输出密度。解决方案:燃气涡轮发动机20包括轴40,反向旋转低压压缩机60和反向旋转低 反转式低压压缩机60包括具有叶片级72,74和76的反向旋转的压缩机毂70,并且低速线轴30的叶片级78和80插入在叶片级之间 传动装置82相对于低速卷轴30使反向旋转的压缩机毂70相对旋转。反向旋转的低压涡轮机62包括内叶片组120,其连接到低轴 通过齿轮装置116和外部刀片组122插入在内侧刀片组120之间。外侧刀片组122以与内侧刀片组120相反的方向在旋转轴线上以低于内侧刀片组120的速度旋转。 内刀片组120。

    Vane structure and low-pressure turbine for gas turbine engine
    5.
    发明专利
    Vane structure and low-pressure turbine for gas turbine engine 有权
    瓦斯结构和低压涡轮发动机

    公开(公告)号:JP2012246915A

    公开(公告)日:2012-12-13

    申请号:JP2012099334

    申请日:2012-04-25

    Abstract: PROBLEM TO BE SOLVED: To provide a full hoop ring structure that prevents leakage of fluid from between each segment of a vane structure.SOLUTION: A vane structure 64B includes: a ceramic matrix composite ring 66 on the outer peripheral side; a ceramic matrix composite ring 68 on the inner peripheral side; and a multiple of ceramic matrix composite airfoils 70 incorporated between the ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side. The ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side are basically wound around the multiple of incorporated airfoils 70 so as to form a full hoop. The design of the full hoop rings allows to maximize the utilization of the fiber strength of the ceramic matrix composite material in the full hoop configuration.

    Abstract translation: 要解决的问题:提供一种防止来自叶片结构的每个部分之间的流体泄漏的完整环形环结构。 解决方案:叶片结构64B包括:外周侧的陶瓷基复合环66; 内周侧的陶瓷基复合环68; 以及并列在外周侧的陶瓷基复合环66和内周侧的陶瓷基复合环68之间的多个陶瓷基复合翼型件70。 外周侧的陶瓷基复合环66和内周侧的陶瓷基复合环68基本上缠绕在多个配置的翼型件70上,以形成完整的箍。 全环环的设计允许最大限度地利用全环形结构中的陶瓷基复合材料的纤维强度。 版权所有(C)2013,JPO&INPIT

    Gas turbine engine
    6.
    发明专利
    Gas turbine engine 有权
    气体涡轮发动机

    公开(公告)号:JP2013181542A

    公开(公告)日:2013-09-12

    申请号:JP2013038267

    申请日:2013-02-28

    Abstract: PROBLEM TO BE SOLVED: To shorten the low shaft of an engine while increasing the output density of the engine.SOLUTION: A gas turbine engine 20 includes a low shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure turbine 62 includes inside blade sets 120 which are connected to the low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is fixed to an outside rotor 126; a front end of the outside rotor 126 is supported on a central turbine frame 134 by a bearing 150; and a rear end of the outside rotor 126 is supported on the low shaft 40 by the bearing 152. In addition, the gear device 116 comprises a sun gear 140, a splitter gear 142 which is meshed with the sun gear 140, and a ring gear 148 which is meshed with the splitter gear 142.

    Abstract translation: 要解决的问题:在增加发动机的输出密度的同时缩短发动机的低轴。解决方案:燃气涡轮发动机20包括低轴40,反向旋转低压压缩机60和反向旋转 低压涡轮机62.反向旋转的低压涡轮机62包括通过齿轮装置116连接到低轴40的内部叶片组120和插入在内部叶片组120之间的外部叶片组122。 外侧刀片组122固定在外侧转子126上; 外转子126的前端由轴承150支撑在中心涡轮机框架134上; 并且外转子126的后端由轴承152支撑在低轴40上。此外,齿轮装置116包括太阳齿轮140,与太阳齿轮140啮合的分动齿轮142和环 与分动齿轮142啮合的齿轮148。

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