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1. 发明申请

US20060254255A1 Aircraft propulsion system 有权
公开(公告)号：US20060254255A1
公开(公告)日：2006-11-16
申请号：US11336828
申请日：2006-01-23
申请人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
发明人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
IPC分类号： F02K3/04
CPC分类号： H02K7/1823 , B64D27/24 , F01D15/10 , F02K3/06 , H02K55/00 , Y02T50/44 , Y02T50/62 , Y02T50/671
摘要： To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment. An electrical generator is coupled to a turbofan engine, the electrical generator is driven by output power of the turbofan engine to output electric power, and an electromagnetic driving fan is driven by the electric power. On the other hand, after bringing each of coils in the electromagnetic driving fan to a superconductive state, liquid hydrogen is introduced to a heat exchanger, collects the energy of exhaust as heat, is then vaporized, and thereafter supplied to a combustor and to a fuel cell. Further, the electromagnetic driving fan is changed in its rotational phase by a rotating mechanism portion, is made movable in a width direction of a wing and a wing chord direction by a slide mechanism portion, and can be stored inside or outside the wing by a storage mechanism portion.

2. 发明申请

US20090226297A1 HIGH BYPASS-RATIO TURBOFAN JET ENGINE 有权
标题翻译：高比例涡轮喷气式发动机
公开(公告)号：US20090226297A1
公开(公告)日：2009-09-10
申请号：US12392203
申请日：2009-02-25
申请人： Ryoji Yanagi , Hitoshi Fujiwara
发明人： Ryoji Yanagi , Hitoshi Fujiwara
IPC分类号： F01D25/24
CPC分类号： F02K3/065 , B64C7/02 , B64D29/02 , F02C7/04 , F05D2250/14 , Y02T50/671
摘要： To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan duct that introduces air into an aft fan are disposed such as to change cross-sectional shapes thereof by rotating around a core engine in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.
摘要翻译：为了提供一种涡轮风扇喷气发动机，其能够在不增加风扇直径的同时增加旁路比，并且降低作用在发动机上的空气阻力，将由前风扇压缩的空气排出到大气的前风扇管道和向后排出的风扇导管将空气引入后风扇的方式设置成通过围绕核心发动机沿逆时针方向旋转来改变其横截面形状，使得前风扇管道和后风扇管道在位置处的横截面几何关系紧靠前风扇的后方，在风扇前方的前方风扇管道与后风扇管道之间的截面几何关系被反转。

3. 发明申请

US20060176009A1 Electromagnetic rotating machine 有权
标题翻译：电磁旋转机
公开(公告)号：US20060176009A1
公开(公告)日：2006-08-10
申请号：US11336830
申请日：2006-01-23
申请人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
发明人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
IPC分类号： H02P1/24
CPC分类号： F02K3/06 , F02K3/04 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2260/4041 , F05D2260/85 , F05D2260/903 , H02K17/16 , H02K17/165 , H02K41/025 , Y02T50/671
摘要： In order to obtain an electromagnetic rotating machine of lightweight and high energy efficiency, which produces big torque for rotating a large-diameter fan, a coil A and coil B as excitation coils are disposed on an inner peripheral surface of a fan casing so as to face an outer circumference of the fan, and a coil M as an armature coil crosses at a central portion and is disposed on the outer circumference of the fan. The relationships |Iai|=|Iai+1| and Iai=−Iai+1, or |Ibi|=|Ibi+1| and Ibi=−Ibi+1 are obtained respectively for the coil A or coil B by a current control device (not shown). Moreover, the coil A and coil B are subjected to excitation control such that the direction of effective electromagnetic force, which is generated by an interaction between an effective magnetic field formed by the coil A and effective induced current applied to the coil M by the coil B, corresponds to the direction of rotation of the fan.
摘要翻译：为了获得轻量且高能效的电磁旋转机，其产生用于旋转大直径风扇的大扭矩，作为励磁线圈的线圈A和线圈B设置在风扇壳体的内周面上，从而面对风扇的外周，作为电枢线圈的线圈M与中心部交叉配置在风扇的外周。关系|我 ai | = | I＆lt; ai + 1＆lt; / SUB＆gt; 或者I i + 1，或I i + 1，...，...，B i + 1，...，并且通过电流控制装置（未示出）分别获得对于线圈A或线圈B的I和B + B + 1 +。此外，对线圈A和线圈B进行励磁控制，使得由线圈A形成的有效磁场与由线圈施加到线圈M的有效感应电流之间的相互作用产生的有效电磁力的方向 B对应于风扇的旋转方向。

4. 发明授权

US07555893B2 Aircraft propulsion system 有权
标题翻译：飞机推进系统
公开(公告)号：US07555893B2
公开(公告)日：2009-07-07
申请号：US11336828
申请日：2006-01-23
申请人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
发明人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
IPC分类号： F02K1/00
CPC分类号： H02K7/1823 , B64D27/24 , F01D15/10 , F02K3/06 , H02K55/00 , Y02T50/44 , Y02T50/62 , Y02T50/671
摘要： To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment.An electrical generator is coupled to a turbofan engine, the electrical generator is driven by output power of the turbofan engine to output electric power, and an electromagnetic driving fan is driven by the electric power. On the other hand, after bringing each of coils in the electromagnetic driving fan to a superconductive state, liquid hydrogen is introduced to a heat exchanger, collects the energy of exhaust as heat, is then vaporized, and thereafter supplied to a combustor and to a fuel cell. Further, the electromagnetic driving fan is changed in its rotational phase by a rotating mechanism portion, is made movable in a width direction of a wing and a wing chord direction by a slide mechanism portion, and can be stored inside or outside the wing by a storage mechanism portion.
摘要翻译：提供飞机推进系统，其可以确保用于飞行条件的最佳推力和推力矢量以及用于发动机的最佳截面积，并且其与环境高度兼容。发电机与涡扇发动机相连，发电机由涡扇发动机的输出功率驱动，输出电力，电磁驱动风扇由电力驱动。另一方面，在电磁驱动风扇中的线圈中的每个线圈成为超导状态之后，将液态氢引入到热交换器中，将热量收集排气的能量，然后蒸发，然后供给到燃烧器和燃料电池。此外，电磁驱动风扇通过旋转机构部在其旋转相位上变化，通过滑动机构部在翼的宽度方向和翼弦方向上可移动，并且可以通过一个存储机构部分。

5. 发明授权

US07921637B2 High bypass-ratio turbofan jet engine 有权
标题翻译：高旁通比涡轮风扇喷气发动机
公开(公告)号：US07921637B2
公开(公告)日：2011-04-12
申请号：US12392203
申请日：2009-02-25
申请人： Ryoji Yanagi , Hitoshi Fujiwara
发明人： Ryoji Yanagi , Hitoshi Fujiwara
IPC分类号： F02K3/02
CPC分类号： F02K3/065 , B64C7/02 , B64D29/02 , F02C7/04 , F05D2250/14 , Y02T50/671
摘要： To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan duct that introduces air into an aft fan are disposed such as to change cross-sectional shapes thereof by rotating around a core engine in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.
摘要翻译：为了提供一种涡轮风扇喷气发动机，其能够在不增加风扇直径的同时增加旁路比，并且降低作用在发动机上的空气阻力，将由前风扇压缩的空气排出到大气的前风扇管道和向后排出的风扇导管将空气引入后风扇的方式设置成通过围绕核心发动机沿逆时针方向旋转来改变其横截面形状，使得前风扇管道和后风扇管道在位置处的横截面几何关系紧靠前风扇的后方，在风扇前方的前方风扇管道与后风扇管道之间的横截面几何关系被反转。

6. 发明授权

US07423405B2 Electromagnetic rotating machine 有权
标题翻译：电磁旋转机
公开(公告)号：US07423405B2
公开(公告)日：2008-09-09
申请号：US11336830
申请日：2006-01-23
申请人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
发明人： Keiichi Okai , Takeshi Tagashira , Ryoji Yanagi , Hiroshi Nomura
IPC分类号： H02P1/24
CPC分类号： F02K3/06 , F02K3/04 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2260/4041 , F05D2260/85 , F05D2260/903 , H02K17/16 , H02K17/165 , H02K41/025 , Y02T50/671
摘要： In order to obtain an electromagnetic rotating machine of lightweight and high energy efficiency, which produces big torque for rotating a large-diameter fan, a coil A and coil B as excitation coils are disposed on an inner peripheral surface of a fan casing so as to face an outer circumference of the fan, and a coil M as an armature coil crosses at a central portion and is disposed on the outer circumference of the fan. The relationships |Iai|=|Iai+1| and Iai=−Iai+1, or |Ibi|=|Ibi+1| and Ibi=−Ibi+1 are obtained respectively for the coil A or coil B by a current control device (not shown). Moreover, the coil A and coil B are subjected to excitation control such that the direction of effective electromagnetic force, which is generated by an interaction between an effective magnetic field formed by the coil A and effective induced current applied to the coil M by the coil B, corresponds to the direction of rotation of the fan.
摘要翻译：为了获得轻量且高能效的电磁旋转机，其产生用于旋转大直径风扇的大扭矩，作为励磁线圈的线圈A和线圈B设置在风扇壳体的内周面上，从而面对风扇的外周，作为电枢线圈的线圈M与中心部交叉配置在风扇的外周。关系|我 ai | = | I＆lt; ai + 1＆lt; / SUB＆gt; 或者I i + 1，或I i + 1，...，...，B i + 1，...，并且通过电流控制装置（未示出）分别获得对于线圈A或线圈B的I和B + B + 1 +。此外，对线圈A和线圈B进行励磁控制，使得由线圈A形成的有效磁场与由线圈施加到线圈M的有效感应电流之间的相互作用产生的有效电磁力的方向 B对应于风扇的旋转方向。

7. 发明申请

US20080075580A1 Turbofan jet engine 有权
标题翻译： Turbofan喷气发动机
公开(公告)号：US20080075580A1
公开(公告)日：2008-03-27
申请号：US11902564
申请日：2007-09-24
申请人： Ryoji Yanagi , Hisao Futamura , Hitoshi Fujiwara
发明人： Ryoji Yanagi , Hisao Futamura , Hitoshi Fujiwara
IPC分类号： F01N1/00
CPC分类号： F02K3/065 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/026 , F02K3/075 , F02K3/077 , Y02T50/44 , Y02T50/671
摘要： To provide a turbofan jet engine for a supersonic aircraft, which enables a supersonic cruise with small additional drag due to engine installation while minimizing the jet noise at takeoff. In the turbofan jet engine, two fans, i.e., a front fan and an aft fan, are disposed, and an air inlet and an air outlet are provided on each of the front and aft fans, whereby at takeoff, air is introduced to each of the air inlets of the front and aft fans to drive the front and aft fans in parallel, and the air is then ejected from each of the outlets. On the other hand, during a supersonic cruise, an inlet of an aft fan duct is coupled to an outlet of a front fan duct, where external air is introduced only to an air inlet of the front fan duct and the air compressed through the front fan is fed to the aft fan duct and further compressed through the aft fan, and ejected from a nozzle, so that the front and aft fans are driven in series.
摘要翻译：为超音速飞机提供涡轮风扇喷气发动机，由于发动机安装，能够实现超短距离巡航，同时使起飞时的喷气噪声最小化。在涡轮风扇喷气发动机中，设置有两个风扇，即前风扇和后风扇，并且在前风扇和后风扇中的每一个上设置有空气入口和空气出口，由此在起飞时，空气被引入到每个的前风扇和后风扇的进气口并联驱动前后风扇，然后从每个出口排出空气。另一方面，在超音速巡航期间，后风扇通道的入口连接到前风扇通道的出口，其中外部空气仅被引入前风扇通道的空气入口，并且通过前部压缩的空气风扇被送入后风扇风管，并通过后风扇进一步压缩，并从喷嘴喷出，使得前后风扇被串联驱动。

8. 发明授权

US07887287B2 Turbofan jet engine 有权
标题翻译： Turbofan喷气发动机
公开(公告)号：US07887287B2
公开(公告)日：2011-02-15
申请号：US11902564
申请日：2007-09-24
申请人： Ryoji Yanagi , Hisao Futamura , Hitoshi Fujiwara
发明人： Ryoji Yanagi , Hisao Futamura , Hitoshi Fujiwara
IPC分类号： F02K3/02
CPC分类号： F02K3/065 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/026 , F02K3/075 , F02K3/077 , Y02T50/44 , Y02T50/671
摘要： To provide a turbofan jet engine for a supersonic aircraft, which enables a supersonic cruise with small additional drag due to engine installation while minimizing the jet noise at takeoff. In the turbofan jet engine, two fans, i.e., a front fan and an aft fan, are disposed, and an air inlet and an air outlet are provided on each of the front and aft fans, whereby at takeoff, air is introduced to each of the air inlets of the front and aft fans to drive the front and aft fans in parallel, and the air is then ejected from each of the outlets. On the other hand, during a supersonic cruise, an inlet of an aft fan duct is coupled to an outlet of a front fan duct, where external air is introduced only to an air inlet of the front fan duct and the air compressed through the front fan is fed to the aft fan duct and further compressed through the aft fan, and ejected from a nozzle, so that the front and aft fans are driven in series.
摘要翻译：为超音速飞机提供涡轮风扇喷气发动机，由于发动机安装，能够实现超短距离巡航，同时使起飞时的喷气噪声最小化。在涡轮风扇喷气发动机中，设置有两个风扇，即前风扇和后风扇，并且在前风扇和后风扇中的每一个上设置有空气入口和空气出口，由此在起飞时，空气被引入到每个的前风扇和后风扇的进气口并联驱动前后风扇，然后从每个出口排出空气。另一方面，在超音速巡航期间，后风扇通道的入口连接到前风扇通道的出口，其中外部空气仅被引入前风扇通道的空气入口，并且通过前部压缩的空气风扇被送入后风扇风管，并通过后风扇进一步压缩，并从喷嘴喷出，使得前后风扇被串联驱动。

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