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1. 发明申请

US20140038770A1 GENERATING DEVICE FOR AIRCRAFT 有权
标题翻译：发动飞机装置
公开(公告)号：US20140038770A1
公开(公告)日：2014-02-06
申请号：US14110050
申请日：2012-04-04
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
IPC分类号： F16H15/00
CPC分类号： F16H15/00 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2260/4031 , F05D2260/532 , F05D2270/024 , F05D2270/304 , Y02T50/671
摘要： An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).
摘要翻译：能够抑制飞机发动机的前方面积的增大的发电装置（1）具有与发动机（E）的旋转轴（9）连接的变速器（22），发电机（34），由变速器（22）的输出驱动的输入轴（27）具有沿与所述旋转轴（9）相交并与所述旋转轴（9）连接的方向延伸的轴轴的输入轴（27），以及与所述传动机构输入轴（27）围绕围绕与输入轴（27）垂直的方向延伸的轴线驱动变速器（22）。变速器（22）和发电机（34）沿旋转轴（9）的周向方向彼此间隔开设置。

2. 发明申请

US20140026589A1 AIRCRAFT ENGINE 有权
标题翻译：飞机发动机
公开(公告)号：US20140026589A1
公开(公告)日：2014-01-30
申请号：US14110016
申请日：2012-04-04
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
IPC分类号： F02C7/32
CPC分类号： F16H15/00 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2260/4031 , F05D2260/532 , F05D2270/024 , F05D2270/304 , Y02T50/671
摘要： To provide an aircraft engine in which an accessory can be directly supported with no accessory gearbox intervening to thereby suppress an increase in size thereof, the aircraft engine (E) includes a take-out shaft (11) having a first end portion, connected with an engine rotary shaft (9) and extending in a radially outward direction, and also having a second end portion connected with an accessory (1), and a mounting pad (12) provided in an engine main body (EB) and to which the accessory (1) is fitted. The mounting pad (12) forms an outer perimeter of an opening (48) through which the take-out shaft (11) extends. The opening (48) is sealed by a covering (47), through which the take-out shaft (1) extends, and a sealing member (49) to seal between the covering (47) and the take-out shaft (11).
摘要翻译：为了提供一种飞机发动机，其中附件可以直接支撑，而没有中间的附件齿轮箱，从而抑制其尺寸的增加，飞行器发动机（E）包括具有第一端部的取出轴（11）发动机旋转轴（9）并且沿径向向外的方向延伸，并且还具有与附件（1）连接的第二端部，以及设置在发动机主体（EB）中的安装垫，配件（1）。安装垫（12）形成开口（48）的外周边，取出轴（11）通过该外周延伸。开口（48）由取出轴（1）延伸穿过的覆盖物（47）和用于密封覆盖物（47）和取出轴（11）之间的密封构件（49）密封，。

3. 发明授权

US09890839B2 Generating device for aircraft 有权
公开(公告)号：US09890839B2
公开(公告)日：2018-02-13
申请号：US14110050
申请日：2012-04-04
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
IPC分类号： F02C7/32 , F02C7/36 , F16H15/00 , F02C7/275
CPC分类号： F16H15/00 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2260/4031 , F05D2260/532 , F05D2270/024 , F05D2270/304 , Y02T50/671
摘要： An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

4. 发明授权

US09765861B2 Sealing arrangement of accessory to aircraft engine 有权
公开(公告)号：US09765861B2
公开(公告)日：2017-09-19
申请号：US14110016
申请日：2012-04-04
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe , Isao Fujii
IPC分类号： F16H15/00 , F02C7/32 , F02C7/36 , F02C7/275
CPC分类号： F16H15/00 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2260/4031 , F05D2260/532 , F05D2270/024 , F05D2270/304 , Y02T50/671
摘要： To provide an aircraft engine in which an accessory can be directly supported with no accessory gearbox intervening to thereby suppress an increase in size thereof, the aircraft engine (E) includes a take-out shaft (11) having a first end portion, connected with an engine rotary shaft (9) and extending in a radially outward direction, and also having a second end portion connected with an accessory (1), and a mounting pad (12) provided in an engine main body (EB) and to which the accessory (1) is fitted. The mounting pad (12) forms an outer perimeter of an opening (48) through which the take-out shaft (11) extends. The opening (48) is sealed by a covering (47), through which the take-out shaft (1) extends, and a sealing member (49) to seal between the covering (47) and the take-out shaft (11).

5. 发明授权

US08378510B2 Starting and generating apparatus for engine 有权
公开(公告)号：US08378510B2
公开(公告)日：2013-02-19
申请号：US12453107
申请日：2009-04-29
申请人： Kenichiro Tanaka , Tatsuhiko Goi , Kazushige Sugimoto , Masahide Nakamura , Yasutaka Hirota , Koji Watanabe
发明人： Kenichiro Tanaka , Tatsuhiko Goi , Kazushige Sugimoto , Masahide Nakamura , Yasutaka Hirota , Koji Watanabe
IPC分类号： H02K23/52 , H02P9/04 , F02N11/04
CPC分类号： F02N11/04 , F02D2400/12 , F02N15/025 , F02N15/043 , F02N2300/104 , F16H15/38 , F16H61/6649 , Y10T477/71
摘要： The invention is a starting and generating apparatus for an engine, including: a rotator configured to be used as a generator driven by an engine as well as used as a starter motor for starting the engine; a power transmission mechanism configured to connect the engine with the rotator; a starter drive unit configured to supply an electricity to the rotator to drive the rotator as the starter motor when the engine is to be started; a clutch mechanism configured to shut off a power transmission from the engine to the power transmission mechanism when the engine is to be started; and a clutch control unit configured to bring the clutch mechanism into a connected state when a rotational speed of the rotator has reached a given rotational speed at which the engine can be started.

6. 发明授权

US08449431B2 Aircraft electric generation system 有权
标题翻译：飞机发电系统
公开(公告)号：US08449431B2
公开(公告)日：2013-05-28
申请号：US12656565
申请日：2010-02-03
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Masahide Nakamura , Koji Watanabe
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Masahide Nakamura , Koji Watanabe
IPC分类号： F16H37/00
CPC分类号： F02C7/32 , F05D2260/40311 , F05D2270/024 , F05D2270/304 , F16H15/38 , F16H61/6648 , F16H61/6649 , Y02T50/671
摘要： This invention provides an aircraft electric generation system, which can achieve significantly increased capacity of electric generation, while adequately suppressing unwanted increase of a front face area of an aircraft engine as well as successfully dealing with considerably large changes of an engine spool speed. This electric generation system is driven by the engine and includes: a continuously variable transmission (CVT) connected with a rotation shaft of the engine; an electric generator located above the CVT and driven by an output of the CVT; and a lubricating oil pump unit located below the CVT and also driven by the output of the CVT.
摘要翻译：本发明提供了一种飞机发电系统，其能够实现显着增加的发电容量，同时充分地抑制飞机发动机的正面区域的不期望的增加以及成功地处理发动机滑阀速度的相当大的变化。该发电系统由发动机驱动，包括：与发动机的旋转轴连接的无级变速器（CVT）; 位于CVT上方并由CVT的输出驱动的发电机; 以及位于CVT下方并由CVT的输出驱动的润滑油泵单元。

7. 发明申请

US20100200692A1 Aircraft electric generation system 有权
标题翻译：飞机发电系统
公开(公告)号：US20100200692A1
公开(公告)日：2010-08-12
申请号：US12656565
申请日：2010-02-03
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Masahide Nakamura , Koji Watanabe
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Masahide Nakamura , Koji Watanabe
IPC分类号： B64D41/00
CPC分类号： F02C7/32 , F05D2260/40311 , F05D2270/024 , F05D2270/304 , F16H15/38 , F16H61/6648 , F16H61/6649 , Y02T50/671
摘要： This invention provides an aircraft electric generation system, which can achieve significantly increased capacity of electric generation, while adequately suppressing unwanted increase of a front face area of an aircraft engine as well as successfully dealing with considerably large changes of an engine spool speed. This electric generation system is driven by the engine and includes: a continuously variable transmission (CVT) connected with a rotation shaft of the engine; an electric generator located above the CVT and driven by an output of the CVT; and a lubricating oil pump unit located below the CVT and also driven by the output of the CVT.
摘要翻译：本发明提供了一种飞机发电系统，其能够实现显着增加的发电容量，同时充分地抑制飞机发动机的正面区域的不期望的增加以及成功地处理发动机滑阀速度的相当大的变化。该发电系统由发动机驱动，包括：与发动机的旋转轴连接的无级变速器（CVT）; 位于CVT上方并由CVT的输出驱动的发电机; 以及位于CVT下方并由CVT的输出驱动的润滑油泵单元。

8. 发明授权

US08500583B2 Aircraft starter generator 有权
标题翻译：飞机起动发电机
公开(公告)号：US08500583B2
公开(公告)日：2013-08-06
申请号：US12916898
申请日：2010-11-01
申请人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe
发明人： Tatsuhiko Goi , Kenichiro Tanaka , Koji Watanabe
IPC分类号： F16H3/72 , F16H37/08
CPC分类号： F02N11/04 , F02C7/275 , F02C7/36 , F02D2400/08 , F02N15/022 , F02N15/043 , F02N15/046 , Y02T50/671
摘要： A starter generator has an electric rotating machine having a rotating shaft and designed to carry two reverse operations—motor and generator. A first clutch is connected between the rotating machine and the first rotating shaft for transmitting rotations of the rotating machine to the first rotating shaft. A second clutch is connected between the rotating machine and the second rotating shaft for transmitting rotations of the second rotating shaft to the rotating machine. A continuously variable transmission is provided for changing the number of rotations transmitted from the second rotating shaft to the rotating machine. The rotating machine is supplied with electric power to rotate the rotating shaft, or the number of rotations of the rotating shaft is kept constant by controlling a transmission ratio of the continuously variable transmission.
摘要翻译：起动发电机具有旋转电机，其具有旋转轴，设计用于承载两个反向操作 - 电机和发电机。第一离合器连接在旋转机器和第一旋转轴之间，用于将旋转机器的旋转传递到第一旋转轴。第二离合器连接在旋转机器和第二旋转轴之间，用于将第二旋转轴的旋转传递到旋转机器。提供了一种无级变速器，用于改变从第二旋转轴传递到旋转机器的转数。通过控制无级变速器的传动比，旋转机器被供给电力以使旋转轴旋转，或者旋转轴的转数保持恒定。

9. 发明申请

US20130180803A1 GEAR TRAIN LUBRICATING DEVICE 有权
标题翻译：齿轮润滑装置
公开(公告)号：US20130180803A1
公开(公告)日：2013-07-18
申请号：US13809557
申请日：2011-07-11
申请人： Kenichiro Tanaka , Tatsuhiko Goi , Hidenori Arisawa , Motohiko Nishimura
发明人： Kenichiro Tanaka , Tatsuhiko Goi , Hidenori Arisawa , Motohiko Nishimura
IPC分类号： F16H57/04
CPC分类号： F16H57/0421 , F16H57/0409 , F16H57/0423 , F16H57/0495
摘要： A lubricating device for a gear train (5) including a plurality of gears meshing with each other includes a shroud (7) configured to cover the gear train (5) and a housing (9) configured to cover the shroud (7). The shroud (7) includes: an oil supply nozzle (25) configured to supply oil (OL) to a meshing position (21) of the gear train (5); and oil-drain ports (41) through which the oil (OL) is discharged from the shroud. The housing (9) includes, at its lower part, a draw-out port (43) through which the oil (OL) discharged from the oil-drain ports (41) is drawn to the outside of the housing. Guide members (47) are provided between the shroud (7) and the housing (9). The guide members (47) guide the oil (OL) discharged from the respective oil-drain ports (41) of the shroud (7) such that the oil (OL) flows downward through space (S) between the shroud (7) and the housing (9).
摘要翻译：一种用于包括彼此啮合的多个齿轮的齿轮系的润滑装置，包括构造成覆盖齿轮系（5）的护罩（7）和构造成覆盖罩（7）的壳体（9）。护罩（7）包括：供油喷嘴（25），其构造成将油（OL）供应到齿轮系（5）的啮合位置（21）; 和排油口（41），油（OL）通过该排油口从护罩排出。所述壳体（9）在其下部包括抽出口（43），从所述排油口（41）排出的油（OL）通过所述抽出口被抽吸到所述壳体的外部。引导构件（47）设置在护罩（7）和壳体（9）之间。引导构件（47）引导从护罩（7）的各个排油口（41）排出的油（OL），使得油（OL）向下流动通过护罩（7）与护罩（7）之间的空间（S）外壳（9）。

10. 发明授权

US09309958B2 Gear train lubricating device 有权
标题翻译：齿轮系润滑装置
公开(公告)号：US09309958B2
公开(公告)日：2016-04-12
申请号：US13809557
申请日：2011-07-11
申请人： Kenichiro Tanaka , Tatsuhiko Goi , Hidenori Arisawa , Motohiko Nishimura
发明人： Kenichiro Tanaka , Tatsuhiko Goi , Hidenori Arisawa , Motohiko Nishimura
IPC分类号： F16H57/04
CPC分类号： F16H57/0421 , F16H57/0409 , F16H57/0423 , F16H57/0495
摘要： A lubricating device for a gear train (5) including a plurality of gears meshing with each other includes a shroud (7) configured to cover the gear train (5) and a housing (9) configured to cover the shroud (7). The shroud (7) includes: an oil supply nozzle (25) configured to supply oil (OL) to a meshing position (21) of the gear train (5); and oil-drain ports (41) through which the oil (OL) is discharged from the shroud. The housing (9) includes, at its lower part, a draw-out port (43) through which the oil (OL) discharged from the oil-drain ports (41) is drawn to the outside of the housing. Guide members (47) are provided between the shroud (7) and the housing (9). The guide members (47) guide the oil (OL) discharged from the respective oil-drain ports (41) of the shroud (7) such that the oil (OL) flows downward through space (S) between the shroud (7) and the housing (9).
摘要翻译：一种用于包括彼此啮合的多个齿轮的齿轮系的润滑装置，包括构造成覆盖齿轮系（5）的护罩（7）和构造成覆盖罩（7）的壳体（9）。护罩（7）包括：供油喷嘴（25），其构造成将油（OL）供应到齿轮系（5）的啮合位置（21）; 和排油口（41），油（OL）通过该排油口从护罩排出。所述壳体（9）在其下部包括抽出口（43），从所述排油口（41）排出的油（OL）通过所述抽出口被抽吸到所述壳体的外部。引导构件（47）设置在护罩（7）和壳体（9）之间。引导构件（47）引导从护罩（7）的各个排油口（41）排出的油（OL），使得油（OL）向下流动通过护罩（7）与护罩（7）之间的空间（S）外壳（9）。

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