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1. 发明授权

US4435647A Predicted motion wind turbine tower damping 失效
标题翻译：预测运动风力涡轮机塔架阻尼
公开(公告)号：US4435647A
公开(公告)日：1984-03-06
申请号：US364707
申请日：1982-04-02
申请人： Kermit I. Harner , John P. Patrick , Joseph M. Kos
发明人： Kermit I. Harner , John P. Patrick , Joseph M. Kos
IPC分类号： F03D7/04 , F03D7/02 , F03D13/20 , F03D9/00
CPC分类号： F03D7/043 , F03D7/0224 , F03D7/0292 , F03D80/00 , F05B2240/912 , F05B2260/821 , F05B2260/96 , F05B2270/1033 , F05B2270/322 , F05B2270/335 , Y02E10/723 , Y02E10/728
摘要： Damping of the primary bending mode of a tower (12) mounting a wind turbine having a control (36) for providing a pitch blade angle reference signal (40) to modulate the pitch of the turbine blades (1) through a pitch change mechanism (38) for constant power is provided by generating the pitch blade angle reference signal as the integral (104) of the summation (266) of a torque/power controlling blade pitch angle reference rate signal (98) with an estimated acceleration signal (255) generated by filtering (250, 252, 254) the blade pitch angle reference signal (40) with the following transfer function ##EQU1##
摘要翻译：具有安装风力涡轮机的塔架（12）的主要弯曲模式的阻尼，所述风力涡轮机具有用于提供俯仰叶片角度参考信号（40）的控制器（36），以通过桨距变化机构（...）调节涡轮叶片（1）的桨距通过产生作为扭矩/功率控制叶片俯仰角参考速率信号（98）的求和（266）的积分（104）的俯仰叶片角度参考信号与估计的加速度信号（255）来提供恒定功率，通过以下传递函数过滤（250,252,254）叶片俯仰角参考信号（40）而产生

2. 发明授权

US4420692A Motion responsive wind turbine tower damping 失效
标题翻译：运动响应风力涡轮机塔架阻尼
公开(公告)号：US4420692A
公开(公告)日：1983-12-13
申请号：US364706
申请日：1982-04-02
申请人： Joseph M. Kos , John P. Patrick , Kermit I. Harner
发明人： Joseph M. Kos , John P. Patrick , Kermit I. Harner
IPC分类号： F03D7/04 , F03D7/02 , F03D13/20 , F03D9/00
CPC分类号： F03D7/043 , F03D7/0224 , F03D7/0292 , F03D80/00 , F05B2240/912 , F05B2260/96 , F05B2270/1033 , F05B2270/322 , F05B2270/334 , Y02E10/723 , Y02E10/728
摘要： An accelerometer (1) disposed on the support tower (12) of a wind turbine electric generating system in the vicinity of the rotor (10, 16) thereof provides a signal (1) indicative of acceleration of the tower in the direction of the rotor rotational axis. The signal (2) is passed through a band-pass filter (4) for summation (9) with a torque/power controlled (100) blade pitch angle reference rate signal (98), the integral (104) of which provides a blade pitch angle reference signal (40) to control the pitch angle of the rotor blades (10) through a pitch change mechanism (38), thereby to provide additional, positive aerodynamic damping to the tower while modulating blade angle for constant torque/power in response to wind turbulence.
摘要翻译：设置在风力涡轮机发电系统的支撑塔（12）上的加速度计（1）在其转子（10,16）附近提供一个信号（1），其指示塔架在转子方向上的加速度旋转轴。信号（2）通过扭矩/功率控制（100）叶片桨距角参考速率信号（98）通过用于求和（9）的带通滤波器（4），其整体（104）提供叶片俯仰角参考信号（40），以通过间距改变机构（38）来控制转子叶片（10）的俯仰角，从而为塔架提供额外的正空气动力学阻尼，同时响应于恒定扭矩/功率调节叶片角度风湍流。

3. 发明授权

US4339666A Blade pitch angle control for a wind turbine generator 失效
标题翻译：用于风力发电机的桨叶角度控制
公开(公告)号：US4339666A
公开(公告)日：1982-07-13
申请号：US219611
申请日：1980-12-24
申请人： John P. Patrick , Joseph M. Kos , Kermit I. Harner
发明人： John P. Patrick , Joseph M. Kos , Kermit I. Harner
IPC分类号： F03D7/04 , F03D7/02 , F03D9/00
CPC分类号： F03D7/0224 , F05B2270/1032 , F05B2270/1033 , F05B2270/32 , Y02E10/723
摘要： A blade pitch angle control for a wind turbine-generator establishing an optimum power or torque reference signal which, when operating conditions so warrant, is not limited by the nominal torque or power ratings of various turbine generator components. The reference signal is indicative of a maximum blade angle setting for safe operation of the wind turbine. An integral or lag compensation circuit for enhanced transient and steady-state operation may be employed.
摘要翻译：风力涡轮发电机的叶片俯仰角控制器建立最佳功率或扭矩参考信号，当操作条件如此保证时，其不受各种涡轮发电机部件的额定转矩或额定功率的限制。参考信号表示用于风力涡轮机的安全操作的最大叶片角度设置。可以使用用于增强的瞬态和稳态操作的积分或滞后补偿电路。

4. 发明授权

US4160170A Wind turbine generator pitch control system 失效
标题翻译：风力发电机调速控制系统
公开(公告)号：US4160170A
公开(公告)日：1979-07-03
申请号：US916321
申请日：1978-06-15
申请人： Kermit I. Harner , Joseph M. Kos , John P. Patrick
发明人： Kermit I. Harner , Joseph M. Kos , John P. Patrick
IPC分类号： F03D7/02 , F03D7/04 , F03D9/00
CPC分类号： F03D7/044 , F03D7/0224 , F03D7/046 , F05B2220/706 , F05B2270/101 , F05B2270/102 , F05B2270/1033 , F05B2270/1095 , F05B2270/32 , F05B2270/327 , F05B2270/328 , F05B2270/706 , Y02E10/723 , Y02E10/725 , Y10S416/04
摘要： Wind energy is used to drive a wind turbine, which is in turn connected to an electrical generator to produce electrical power. The pitch angle of the wind turbine blades is controlled in a closed loop manner to maintain either a constant generator speed for isolated power generating stations or when the generator is synchronized to the load, or constant generator output power or shaft torque when the generator is connected to an electrical grid. Open loop acceleration and deceleration schedules are provided to minimize blade stress and shaft torque variations during start up and shutdown transients, limiting blade angle excursions as a function of wind velocity and speed. The schedules may be implemented either electronically or by a suitably programmed digital computer. The gains in the speed, torque and power loop controls are scheduled as a function of average wind velocity to optimize stability and response. An anticipatory blade angle schedule responsive to instantaneous wind velocity is added to the desired blade angle reference from the closed loop controls to minimize transient excursions in output power or generator speed resulting from wind gusts.

5. 发明授权

US4318509A Fluid temperature control system 失效
标题翻译：流体温度控制系统
公开(公告)号：US4318509A
公开(公告)日：1982-03-09
申请号：US254234
申请日：1981-04-15
申请人： John P. Patrick , Robert B. Goodman
发明人： John P. Patrick , Robert B. Goodman
IPC分类号： G05D23/13 , G05D23/185 , G05D23/08
CPC分类号： G05D23/138 , G05D23/185 , Y10T137/2409
摘要： Fluid temperature control system for providing a supply fluid at a select temperature by warming or cooling a first fluid with a controlled flow of a second fluid. The control of the second fluid flow is achieved by a modulation valve adjustable in response to the pressure of a supply of servo fluid which is itself adjusted in response to the temperature of the supply fluid. The adjustment of the servo fluid pressure by the control system is such that the change in servo fluid pressure from a steady state condition is initially great, diminishing with time to a lesser, steady state value, thereby enhancing the transient response of the control system.
摘要翻译：流体温度控制系统，用于通过用受控流动的第二流体加热或冷却第一流体，在选定温度下提供供应流体。第二流体流量的控制通过响应于伺服流体供应的压力可调节的调节阀来实现，伺服流体本身被自身根据供给流体的温度进行调节。控制系统对伺服流体压力的调节使得伺服液压力从稳态状态的变化开始很大，随时间逐渐减小到较小的稳态值，从而增强了控制系统的瞬态响应。

6. 发明授权

US4277940A Integral rocket-ramjet closed loop fuel control system 失效
标题翻译：一体式火箭冲压喷气闭环燃油控制系统
公开(公告)号：US4277940A
公开(公告)日：1981-07-14
申请号：US60444
申请日：1979-07-25
申请人： Kermit I. Harner , John P. Patrick
发明人： Kermit I. Harner , John P. Patrick
IPC分类号： F02C9/44 , F02K7/18 , F02K9/06
CPC分类号： F02C9/44 , F02K7/18 , Y02T50/671
摘要： In an integral rocket-ramjet having a combustor which initially serves as a rocket combustion chamber for booster propellant, and after the booster propellant is expended serves as a ramjet combustor where fuel and air are burned, a fuel control system is described for the ramjet stage by which ram burner light-off is automatically initiated upon transition from rocket to ramjet propulsion. The fuel control regulates fuel flow to the combustor over the entire flight regime and responds to operating conditions to provide a light-off schedule, to stabilize the shock wave at the air inlet, to provide a maximum fuel-to-air ratio limit, to limit the maximum vehicle Mach number, and to prevent lean burner blowout by providing a minimum fuel-to-air ratio limit. Mach number limiting and air inlet margin limiting are performed in closed loop fashion, while the other functions are scheduled or open loop controls. The closed loop functions are performed by scheduling a ratio of combustion chamber pressure to a reference pressure, and comparing this ratio to the ratio of the pressures as measured, any error therebetween being used to produce a desired fuel flow to combustion chamber pressure ratio. By measuring the actual combustion chamber pressure, the desired fuel flow is obtained.
摘要翻译：在具有最初用作助燃推进剂的火箭燃烧室的燃烧器的整体式火箭冲压喷气发动机中，并且在助燃剂推进剂消耗之后用作燃料和空气燃烧的冲压喷气燃烧器时，描述了用于冲压喷气级的燃料控制系统在从火箭转向冲压喷气推进时，自动启动柱塞燃烧器点火。燃料控制调节在整个飞行状态下到燃烧器的燃料流量，并响应操作条件以提供熄灯计划，以稳定进气口处的冲击波，以提供最大的燃油比空气比限制限制最大车辆马赫数，并通过提供最小燃料空气比限制来防止燃油喷嘴泄漏。马赫数限制和进气口边界限制以闭环方式执行，而其他功能是调度或开环控制。通过调节燃烧室压力与参考压力的比率来执行闭环功能，并且将该比率与测量的压力比进行比较，其间的任何误差被用于产生期望的燃料流量与燃烧室压力比。通过测量实际的燃烧室压力，获得所需的燃料流量。

7. 发明授权

US4193005A Multi-mode control system for wind turbines 失效
标题翻译：风力发电机多模式控制系统
公开(公告)号：US4193005A
公开(公告)日：1980-03-11
申请号：US934658
申请日：1978-08-17
申请人： Joseph M. Kos , John P. Patrick , Kermit I. Harner
发明人： Joseph M. Kos , John P. Patrick , Kermit I. Harner
IPC分类号： F03D9/00 , F03D7/02 , F03D7/04 , H02P9/04
CPC分类号： F03D7/0224 , F03D7/026 , F03D7/0264 , F03D7/043 , H02P9/04 , F05B2220/70642 , F05B2270/101 , F05B2270/1016 , F05B2270/102 , F05B2270/1032 , F05B2270/309 , F05B2270/32 , F05B2270/327 , F05B2270/328 , F05B2270/706 , H02P2101/15 , Y02E10/723 , Y02E10/725
摘要： A multi-mode electronic wind turbine control system establishes a reference blade angle for a two-bladed, horizontal axis, variable pitch wind turbine rotor, the blade angle being regulated by a hydraulic pitch change mechanism. The rotor, via appropriate shafts and a gearbox, is coupled to a synchronous generator to produce electrical energy which is fed to a power utility grid. The control system provides closed loop pitch control for rotor acceleration rate during start-up, for rotor deceleration rate during shutdown, for speed control when the synchronous generator is off-line, and for power control when the synchronous generator is on-line. A single control integrator is used for all closed loop operating modes, with a rate limiter circuit in front of the control integrator to prevent integrator overtravel. The integrator has maximum and minimum blade angle stops, the minimum stop being variable as a function of rotor speed and wind speed. When on-line, power control is provided by a unique shaft torque control using proportional plus integral plus derivative controls in combination.
摘要翻译：多模式电子风力发电机控制系统为双叶片横轴，变桨距风力涡轮机转子建立参考叶片角度，叶片角度由液压桨距变化机构调节。转子通过适当的轴和齿轮箱耦合到同步发电机以产生馈送到电力公用电网的电能。控制系统为启动时的转子加速率，停机时的转子减速率，同步发电机脱机时的速度控制以及同步发电机在线时的功率控制提供闭环调节。单个控制积分器用于所有闭环操作模式，在控制积分器前面设有速率限制器电路，以防止积分器超程。积分器具有最大和最小叶片角度停止，最小停止可以根据转子速度和风速变化。在线时，通过独特的轴转矩控制提供功率控制，使用比例加积分加微分控制组合。

8. 发明授权

US4462753A Blade feathering system for wind turbines 失效
标题翻译：风力发电机叶片羽化系统
公开(公告)号：US4462753A
公开(公告)日：1984-07-31
申请号：US391016
申请日：1982-06-22
申请人： Kermit I. Harner , John P. Patrick , Kenneth F. Vosseller
发明人： Kermit I. Harner , John P. Patrick , Kenneth F. Vosseller
IPC分类号： F03D7/04 , F03D7/02
CPC分类号： F03D7/0224 , F05B2260/74 , Y02E10/723
摘要： A blade feathering system for wind turbines includes a feather actuator (299), control means (330 and 335) operatively connected thereto and an adjustment means (340) operatively connected to the control means for selectively varying the rate of operation of the feather actuator for feathering the wind turbine blades (10 and 15) at a variable rate.
摘要翻译：用于风力涡轮机的叶片羽化系统包括羽毛致动器（299），可操作地连接到其上的控制装置（330和335）和可操作地连接到控制装置的调节装置（340），用于选择性地改变羽毛致动器的操作速率以可变速率对风力涡轮机叶片（10和15）进行羽化。

9. 发明授权

US4263781A Integral rocket-ramjet open loop fuel control system 失效
标题翻译：一体式火箭冲击式开环燃油控制系统
公开(公告)号：US4263781A
公开(公告)日：1981-04-28
申请号：US60443
申请日：1979-07-25
申请人： Kermit I. Harner , John P. Patrick
发明人： Kermit I. Harner , John P. Patrick
IPC分类号： F02C9/28 , F02K9/06
CPC分类号： F02C9/28 , F05D2270/122
摘要： In an integral rocket-ramjet having a combustor which initially serves as a rocket combustion chamber for booster propellant, and after the booster propellant is expended, serves as a ramjet combustor where fuel and air are burned, a fuel control system is described for the ramjet stage by which ram burner light-off is automatically initiated upon transition from rocket to ramjet propulsion. The fuel control regulates fuel flow to the combustor over the entire flight regime and responds to operating conditions to provide a light-off schedule, to stabilize the shock wave in the air inlet, to provide a maximum fuel-to-air ratio limit, to limit the maximum vehicle Mach number, and to prevent lean burner blowout by providing a minimum fuel-to-air ratio limit. Mach number limiting is performed in closed loop fashion, while the other functions are scheduled or open loop controls. Fuel flow to combustion chamber pressure ratio is used to provide fuel-to-air ratio limits, actual combustion chamber pressure being measured to provide the desired fuel flow signal.
摘要翻译：在具有最初用作助燃推进剂的火箭燃烧室的燃烧器的整体式火箭 - 冲压式喷气式发动机中，并且在助燃剂推进剂消耗之后，用作燃料和空气燃烧的冲压式喷射燃烧器，描述了用于冲压式喷气发动机的燃料控制系统在从火箭到冲压喷气推进过渡时，自动启动柱塞燃烧器点火的阶段。燃料控制调节在整个飞行状态下到燃烧器的燃料流量，并且响应于操作条件以提供点火时间表，以稳定进气口中的冲击波，以提供最大的燃油比空气比限制限制最大车辆马赫数，并通过提供最小燃料空气比限制来防止燃油喷嘴泄漏。马赫数限制以闭环方式执行，而其他功能则是调度或开环控制。使用燃料流到燃烧室压力比来提供燃料 - 空气比限度，测量实际燃烧室压力以提供期望的燃料流量信号。

10. 发明授权

US4161658A Wind turbine generator having integrator tracking 失效
标题翻译：具有积分器跟踪的风力发电机组
公开(公告)号：US4161658A
公开(公告)日：1979-07-17
申请号：US916320
申请日：1978-06-15
申请人： John P. Patrick
发明人： John P. Patrick
IPC分类号： F03D7/02 , F03D7/04 , H02P9/04 , F03D9/00
CPC分类号： F03D7/044 , F03D7/0224 , F03D7/046 , H02P9/04 , F05B2220/706 , F05B2270/1016 , F05B2270/102 , F05B2270/1095 , F05B2270/309 , F05B2270/32 , F05B2270/327 , F05B2270/328 , F05B2270/706 , H02P2101/15 , H02P2101/30 , Y02E10/723 , Y02E10/725 , Y10S416/04
摘要： A power generating system includes a wind turbine driven generator, the wind turbine having a wind driven rotor with a plurality of variable pitch angle blades. The blade angle is scheduled during acceleration and deceleration of the wind turbine by open loop controls to minimize stresses, and is scheduled during powered operation by closed loop controls to maintain desired torque or speed. The closed loop controls contain an integrator which produces an integral blade angle control signal. The scheduled blade angle is fed back to the integrators through an integrator tracking network to maintain the integral blade angle control signal at all times within a preselected range relative to the scheduled blade angle.
摘要翻译：发电系统包括风力涡轮机驱动发电机，风力涡轮机具有带有多个可变桨距角叶片的风力转子。通过开环控制在风力涡轮机的加速和减速期间安排叶片角度以最小化应力，并且在通过闭环控制的动力操作期间调度以保持期望的扭矩或速度。闭环控制包含产生一体化叶片角度控制信号的积分器。预定的叶片角度通过积分器跟踪网络反馈给积分器，以将整个叶片角度控制信号始终保持在相对于预定叶片角度的预选范围内。

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