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1. 发明申请

US20080143115A1 ELECTRIC POWER GENERATION USING POWER TURBINE AFT OF LPT 失效
标题翻译：使用LPT的动力涡轮机进行电力发电
公开(公告)号：US20080143115A1
公开(公告)日：2008-06-19
申请号：US11611485
申请日：2006-12-15
申请人： John M. Kern , KiYoung Chung , Ronghai Qu , Wei Wu , Craig D. Young , Peter D. Toot , Christopher Glynn , Tom Compton
发明人： John M. Kern , KiYoung Chung , Ronghai Qu , Wei Wu , Craig D. Young , Peter D. Toot , Christopher Glynn , Tom Compton
IPC分类号： F01D15/10
CPC分类号： H02K7/1823 , F01D15/10 , F02C7/32 , F02K3/06 , H02K1/02 , H02K19/20 , Y02T50/672
摘要： An inside out generator disposed aft of the low-pressure turbine spool to generate power for the electrical demands of an aircraft system. The low-pressure turbine discharge flow is used to drive the power turbine, which is coupled to the generator. The generator is able to extract power at idle conditions of the aircraft engine from ducting the discharge through the inside out generator. The system eliminates the placement of a generator in the hot gas path of the discharge, and enables the injection of power directly to the accessory gear box of the engine.
摘要翻译：设置在低压涡轮阀芯的后方的内出发电机，以产生用于飞机系统的电气需求的动力。低压涡轮机排放流被用于驱动耦合到发电机的动力涡轮机。发电机能够在飞机发动机的怠速状态下提取动力，从而将排放管道通过内向外发生器。该系统消除了发生器在放电的热气路径中的放置，并且能够将动力直接喷射到发动机的附件齿轮箱。

2. 发明授权

US07514810B2 Electric power generation using power turbine aft of LPT 失效
标题翻译：使用LPT动力涡轮机的发电
公开(公告)号：US07514810B2
公开(公告)日：2009-04-07
申请号：US11611485
申请日：2006-12-15
申请人： John M. Kern , KiYoung Chung , Ronghai Qu , Wei Wu , Craig D. Young , Peter D. Toot , Christopher Glynn , Tom Compton
发明人： John M. Kern , KiYoung Chung , Ronghai Qu , Wei Wu , Craig D. Young , Peter D. Toot , Christopher Glynn , Tom Compton
IPC分类号： F02C1/06
CPC分类号： H02K7/1823 , F01D15/10 , F02C7/32 , F02K3/06 , H02K1/02 , H02K19/20 , Y02T50/672
摘要： An inside out generator disposed aft of the low-pressure turbine spool to generate power for the electrical demands of an aircraft system. The low-pressure turbine discharge flow is used to drive the power turbine, which is coupled to the generator. The generator is able to extract power at idle conditions of the aircraft engine from ducting the discharge through the inside out generator. The system eliminates the placement of a generator in the hot gas path of the discharge, and enables the injection of power directly to the accessory gear box of the engine.
摘要翻译：设置在低压涡轮阀芯的后方的内出发电机，以产生用于飞机系统的电气需求的动力。低压涡轮机排放流被用于驱动耦合到发电机的动力涡轮机。发电机能够在飞机发动机的怠速状态下提取动力，从而将排放管道通过内向外发生器。该系统消除了发生器在放电的热气路径中的放置，并且能够将动力直接喷射到发动机的附件齿轮箱。

3. 发明授权

US07791235B2 Variable magnetic coupling of rotating machinery 有权
标题翻译：旋转机械可变磁耦合
公开(公告)号：US07791235B2
公开(公告)日：2010-09-07
申请号：US11615627
申请日：2006-12-22
申请人： John M. Kern , Juan M. De Bedout , Kiyoung Chung , Michal-Wolfgang Waszak , Manoj Ramprasad Shah , Peter D. Toot , Ronghai Qu , Wei Wu
发明人： John M. Kern , Juan M. De Bedout , Kiyoung Chung , Michal-Wolfgang Waszak , Manoj Ramprasad Shah , Peter D. Toot , Ronghai Qu , Wei Wu
IPC分类号： H02K7/10
CPC分类号： H02K49/102 , F01D15/10 , F02C3/113 , F02C7/32 , F02C7/36 , F05D2220/327 , F05D2220/76 , F05D2220/768 , F05D2260/40311 , F05D2260/404
摘要： A system for transferring torque between a pair of independently, concurrently rotating shafts of a turbofan engine includes a magnetic gearbox. The magnetic gearbox has a first ring structure, a second ring structure and an intermediate ring structure. Each ring structure has an annular aperture therethrough and a plurality of permanent magnets embedded therein. The intermediate ring structure is disposed between the first and the second ring structures. Each ring structure is coaxially concentric with, and independently rotatable with respect to the remaining ring structures. The first and second ring structures are each coupled to separate ones of the rotating engine shafts, and the intermediate ring is operable to transfer torque between the pair of shafts. Preferably, the intermediate ring structure is coupled to a rotating machine. The rotating machine has a controller, and is operable for adjusting a ratio of torque transferred between the pair of shafts.
摘要翻译：用于在涡轮风扇发动机的一对独立且同时旋转的轴之间传递扭矩的系统包括磁性齿轮箱。磁齿轮箱具有第一环结构，第二环结构和中间环结构。每个环形结构具有穿过其中的环形孔和嵌入其中的多个永磁体。中间环结构设置在第一和第二环形结构之间。每个环结构与其余的环结构同心并且可独立地旋转。第一和第二环结构各自联接到分离的旋转发动机轴中，并且中间环可操作以在一对轴之间传递扭矩。优选地，中间环结构联接到旋转机器。旋转机具有控制器，并且可操作用于调节在一对轴之间传递的扭矩的比率。

4. 发明申请

US20080149445A1 Variable Magnetic Coupling of Rotating Machinery 有权
标题翻译：旋转机械的可变磁耦合
公开(公告)号：US20080149445A1
公开(公告)日：2008-06-26
申请号：US11615627
申请日：2006-12-22
申请人： John M. Kern , Juan M. De Bedout , Kiyoung Chung , Michal-Wolfgang Waszak , Manoj R. Shah , Peter D. Toot , Ronhai Qu , Wei Wu
发明人： John M. Kern , Juan M. De Bedout , Kiyoung Chung , Michal-Wolfgang Waszak , Manoj R. Shah , Peter D. Toot , Ronhai Qu , Wei Wu
IPC分类号： H02K49/06 , B60W10/02 , F16D67/06
CPC分类号： H02K49/102 , F01D15/10 , F02C3/113 , F02C7/32 , F02C7/36 , F05D2220/327 , F05D2220/76 , F05D2220/768 , F05D2260/40311 , F05D2260/404
摘要： A system for transferring torque between a pair of independently, concurrently rotating shafts of a turbofan engine includes a magnetic gearbox. The magnetic gearbox has a first ring structure, a second ring structure and an intermediate ring structure. Each ring structure has an annular aperture therethrough and a plurality of permanent magnets embedded therein. The intermediate ring structure is disposed between the first and the second ring structures. Each ring structure is coaxially concentric with, and independently rotatable with respect to the remaining ring structures. The first and second ring structures are each coupled to separate ones of the rotating engine shafts, and the intermediate ring is operable to transfer torque between the pair of shafts. Preferably, the intermediate ring structure is coupled to a rotating machine. The rotating machine has a controller, and is operable for adjusting a ratio of torque transferred between the pair of shafts.
摘要翻译：用于在涡轮风扇发动机的一对独立且同时旋转的轴之间传递扭矩的系统包括磁性齿轮箱。磁齿轮箱具有第一环结构，第二环结构和中间环结构。每个环形结构具有穿过其中的环形孔和嵌入其中的多个永磁体。中间环结构设置在第一和第二环形结构之间。每个环结构与其余的环结构同心并且可独立地旋转。第一和第二环结构各自联接到分离的旋转发动机轴中，并且中间环可操作以在一对轴之间传递扭矩。优选地，中间环结构联接到旋转机器。旋转机具有控制器，并且可操作用于调节在一对轴之间传递的扭矩的比率。

5. 发明授权

US4227443A Fail-fixed servovalve 失效
标题翻译：故障固定伺服阀
公开(公告)号：US4227443A
公开(公告)日：1980-10-14
申请号：US945165
申请日：1978-09-25
申请人： Peter D. Toot
发明人： Peter D. Toot
IPC分类号： F15B13/043
CPC分类号： F15B13/0436 , Y10T137/8659 , Y10T137/86598 , Y10T137/86614 , Y10T137/8671
摘要： A fail-fixed servovalve is provided for use in a digital control system. The servovalve is comprised of a deflecting means which deflects a jet pipe in response to an electrical input signal. Fluid flowing through the jet pipe causes a spool to translate within a sleeve, thereby allowing pressurized fluid to flow through selected ports within the sleeve to control the movement of an output piston. The output of the servovalve is essentially linear over the primary range of digital input currents with the output being zero when the input current is either zero or in excess of the maximum rated current for the servovalve.
摘要翻译：提供了一种用于数字控制系统的故障固定伺服阀。伺服阀包括偏转装置，该偏转装置响应于电输入信号使喷射管偏转。流经喷射管的流体使套筒在套筒内平移，从而允许加压流体流过套筒内的选定端口，以控制输出活塞的移动。伺服阀的输出在数字输入电流的主要范围内基本上是线性的，当输入电流为零或超过伺服阀的最大额定电流时，输出为零。

6. 发明授权

US4128995A Method and apparatus for stabilizing an augmenter system 失效
标题翻译：用于稳定增强系统的方法和装置
公开(公告)号：US4128995A
公开(公告)日：1978-12-12
申请号：US733093
申请日：1976-10-18
申请人： Peter D. Toot
发明人： Peter D. Toot
IPC分类号： F02C9/28 , F02C9/16 , F02C9/44 , F02K3/06 , F02K3/08 , F02K3/10 , F02K99/00 , F02C9/08
CPC分类号： F02K1/48
摘要： A turbine is stabilized in high speed, high altitude flight conditions by reducing the maximum augmenter fuel/air ratio in response to certain pressure and temperature conditions. Temperatures and pressures indicative of those at the combustor are sensed and the augmenter fuel schedule is accordingly modified to a level which provides reduced fuel/air ratios and stable burning conditions.
摘要翻译：涡轮机在高速，高空飞行条件下通过响应于某些压力和温度条件降低最大增压器燃料/空气比来稳定。感测到燃烧器处的那些温度和压力，并且将增压器燃料调度相应地修改到提供降低的燃料/空气比和稳定的燃烧条件的水平。

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