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1.发明授权公开(公告)号：US09677504B2
公开(公告)日：2017-06-13
申请号：US12777508
申请日：2010-05-11
Applicant: Sean S. Stroud , Michael J. Piovoso
Inventor： Sean S. Stroud , Michael J. Piovoso
CPC classification number: F02K9/80 , F02K9/08 , F02K9/58 , F05D2200/23 , F05D2200/24 , F05D2270/12 , F05D2270/13 , F05D2270/701
Abstract: Rockets, rocket motors, methods of controlling a rocket and methods of evaluating a rocket design are disclosed. In some embodiments, a method of controlling a rocket may include measuring a combustion chamber pressure, calculating a logarithm of the measured combustion chamber pressure, and computing the difference between the logarithm of the measured combustion chamber pressure and the logarithm of a reference combustion chamber pressure value to generate an error signal. The method may further include filtering the error signal to generate a compensated signal in the logarithm domain, and exponentiating of the compensated signal in the logarithm domain to provide a compensated signal in the physical domain.
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公开(公告)号：US20180156127A1
公开(公告)日：2018-06-07
申请号：US15576962
申请日：2016-04-20
Applicant: Siemens Aktiengesellschaft
Inventor： Kai Hausmann , Carsten Seiler , Dirk Wall
CPC classification number: F02C7/228 , F02C9/26 , F02C9/28 , F05D2270/053 , F05D2270/10 , F05D2270/14 , F05D2270/303 , F05D2270/309 , F05D2270/335 , F05D2270/701 , F05D2270/708 , F23N2025/08 , F23N2041/20
Abstract: An operating method for a gas turbine by partial-load operation, includes setting of a power setpoint value for a predefined temperature value; determining the two operating curves as a function of temperature according to the power of the gas turbine, wherein the power setpoint value is located between said operating curves; determining the difference in power of said two operating curves at the substantially constant predetermined temperature value; determining a power deviation from the predetermined power setpoint value of one of the two operating curves at the substantially constant predetermined temperature value; calculating an interpolated operating curve deviation on the basis of the difference in power and the power deviation, wherein the temperature is a turbine outlet temperature or a computationally determined turbine inlet temperature.
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3.发明申请公开(公告)号：US20090277185A1
公开(公告)日：2009-11-12
申请号：US12116928
申请日：2008-05-07
Applicant: Jerry L. Goeke , Brandon P. Williams
Inventor： Jerry L. Goeke , Brandon P. Williams
IPC: F02C9/26
CPC classification number: F02C9/263 , F05D2270/701
Abstract: Valve systems for controlling a flow of fuel in a gas turbine engine and related methods are provided. In one embodiment, the valve system includes a supply conduit, a proportional valve portion, and a pulsating valve portion. The supply conduit is adapted and configured for receiving and carrying a flow of fuel. The proportional valve portion is in fluid connection with the supply conduit adapted and configured to gradually adjust a pressure drop thereacross and thus a flow rate of fuel flowing therethrough. The pulsating valve portion is in fluid connection with the supply conduit, in parallel with the proportional valve portion, and is adapted and configured to rapidly adjust a pressure drop thereacross and thus a flow rate of fuel flowing therethrough.
Abstract translation: 提供了用于控制燃气涡轮发动机中的燃料流的阀门系统和相关方法。 在一个实施例中，阀系统包括供应管道，比例阀部分和脉动阀部分。 供应管道适于和构造成用于接收和携带燃料流。 比例阀部分与供应管道流体连接，该供应管道适于并构造成逐渐调节其上的压降，从而流过其中的燃料流量。 脉动阀部分与供应管道流体连接，与比例阀部分平行，并且适于和构造成快速地调节其上的压降，从而使燃料流过其中的流量。
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Patent Agency Ranking
公开(公告)号：US20180171824A1
公开(公告)日：2018-06-21
申请号：US15738589
申请日：2016-06-08
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： MARC BOROWSKI , OLIVER STAWARSKI
CPC classification number: F01D25/12 , F01D21/003 , F01K13/02 , F01K13/025 , F01P7/02 , F05D2220/31 , F05D2260/20 , F05D2270/701 , F05D2270/705 , F05D2270/706 , G06F1/206
Abstract: Provided is a method for rapidly cooling a steam turbine, wherein ambient air is introduced into the steam turbine through a valve via an evacuation unit, resulting in cooling of the steam turbine, the rate of cooling being adjusted by an automation system including a controller.
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公开(公告)号：US20170292457A1
公开(公告)日：2017-10-12
申请号：US15092928
申请日：2016-04-07
Applicant: United Technologies Corporation
Inventor： Tyler J. Selstad
CPC classification number: F02C9/263 , F01D21/003 , F02C7/232 , F02C9/44 , F05D2220/323 , F05D2260/82 , F05D2270/306 , F05D2270/54 , F05D2270/701 , F05D2270/71 , F05D2270/80
Abstract: According to an aspect, a correction factor for a fuel flow of a fuel system of an engine is determined. A nominal fuel flow is determined based on a metering valve stroke. The correction factor is applied to the nominal fuel flow to produce an estimated fuel flow to control combustion in the engine.
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公开(公告)号：US09932850B2
公开(公告)日：2018-04-03
申请号：US14612491
申请日：2015-02-03
Applicant: General Electric Company
Inventor： Yuhui Chen , Bryan Edward Sweet , Scott William Szepek
CPC classification number: F01D17/04 , F01D15/10 , F01D21/003 , F02C9/28 , F02C9/32 , F05D2220/764 , F05D2270/024 , F05D2270/061 , F05D2270/701
Abstract: A method, including receiving a turbine system operating parameter. The turbine system operating parameter includes an indication of a frequency variation of an electric power system associated with the turbine system. The method includes determining a correction factor to vary the output of the turbine system according to the frequency variation, wherein the correction factor is based on a droop power response and a nominal droop power ratio. The droop power response is calculated based on a gas turbine power output and a speed-load error. The method further includes varying the output of the turbine system based at least in part on the correction factor.
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7.发明申请公开(公告)号：US20160222816A1
公开(公告)日：2016-08-04
申请号：US14612491
申请日：2015-02-03
Applicant: General Electric Company
Inventor： Yuhui Chen , Bryan Edward Sweet , Scott William Szepek
CPC classification number: F01D17/04 , F01D15/10 , F01D21/003 , F02C9/28 , F02C9/32 , F05D2220/764 , F05D2270/024 , F05D2270/061 , F05D2270/701
Abstract: A method, including receiving a turbine system operating parameter. The turbine system operating parameter includes an indication of a frequency variation of an electric power system associated with the turbine system. The method includes determining a correction factor to vary the output of the turbine system according to the frequency variation, wherein the correction factor is based on a droop power response and a nominal droop power ratio. The droop power response is calculated based on a gas turbine power output and a speed-load error. The method further includes varying the output of the turbine system based at least in part on the correction factor.
Abstract translation: 一种方法，包括接收涡轮机系统操作参数。 涡轮机系统操作参数包括与涡轮机系统相关联的电力系统的频率变化的指示。 该方法包括根据频率变化确定校正因子以改变涡轮机系统的输出，其中校正因子基于下垂功率响应和标称下垂功率比。 下降功率响应是基于燃气轮机功率输出和速度 - 负载误差来计算的。 该方法还包括至少部分地基于校正因子来改变涡轮机系统的输出。
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8.发明申请公开(公告)号：US20110277446A1
公开(公告)日：2011-11-17
申请号：US12777508
申请日：2010-05-11
Applicant: Sean S. Stroud , Michael J. Piovoso
Inventor： Sean S. Stroud , Michael J. Piovoso
CPC classification number: F02K9/80 , F02K9/08 , F02K9/58 , F05D2200/23 , F05D2200/24 , F05D2270/12 , F05D2270/13 , F05D2270/701
Abstract: Rockets, rocket motors, methods of controlling a rocket and methods of evaluating a rocket design are disclosed. In some embodiments, a method of controlling a rocket may include measuring a combustion chamber pressure, calculating a logarithm of the measured combustion chamber pressure, and computing the difference between the logarithm of the measured combustion chamber pressure and the logarithm of a reference combustion chamber pressure value to generate an error signal. The method may further include filtering the error signal to generate a compensated signal in the logarithm domain, and exponentiating of the compensated signal in the logarithm domain to provide a compensated signal in the physical domain.
Abstract translation: 公开了火箭，火箭发动机，控制火箭的方法和评估火箭设计的方法。 在一些实施例中，控制火箭的方法可以包括测量燃烧室压力，计算所测量的燃烧室压力的对数，以及计算所测量的燃烧室压力的对数与参考燃烧室压力的对数之间的差 值产生错误信号。 该方法还可以包括对误差信号进行滤波以产生对数域中的经补偿的信号，以及对数域中的补偿信号的指数，以在物理域中提供经补偿的信号。
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