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1. 发明申请

US20090204306A1 METHODS AND SYSTEMS FOR MODULATING FUEL FLOW FOR GAS TURBINE ENGINES 有权
标题翻译：用于调节燃气涡轮发动机的燃油流量的方法和系统
公开(公告)号：US20090204306A1
公开(公告)日：2009-08-13
申请号：US12368472
申请日：2009-02-10
申请人： Jerry Lee Goeke , Brandon Philip Williams
发明人： Jerry Lee Goeke , Brandon Philip Williams
IPC分类号： F02C9/00
CPC分类号： F02C9/285 , F23R2900/00013
摘要： A method of combustion stability control for a gas turbine engine is provided, and includes the steps of receiving by a stability controller, information regarding environmental and operating conditions, and comparing the environmental and operating conditions to pre-programmed information to determine if a likelihood of combustion instability exists. The method further includes the steps of determining optimal fuel modulation frequency and amplitude for the environmental condition to reduce combustion instability, if a likelihood of combustion instability exists, and actuating at least one fuel modulation valve to, at the optimal fuel modulation frequency and amplitude, reduce combustion instability, if a likelihood of combustion instability exists. Systems for modulating fuel flow are also provided.
摘要翻译：提供了一种用于燃气涡轮发动机的燃烧稳定性控制的方法，并且包括以下步骤：由稳定性控制器接收关于环境和操作条件的信息，以及将环境和操作条件与预编程信息进行比较，以确定是否存在燃烧不稳定存在。该方法还包括以下步骤：如果存在燃烧不稳定的可能性，则确定用于环境条件的最佳燃料调制频率和幅度以减少燃烧不稳定性，并且以最佳燃料调制频率和振幅致动至少一个燃料调节阀，如果存在燃烧不稳定的可能性，则减少燃烧不稳定性。还提供用于调节燃料流量的系统。

2. 发明授权

US07010904B2 Method for control scheduling to achieve linear thrust response 失效
标题翻译：控制调度方法实现线性推力响应
公开(公告)号：US07010904B2
公开(公告)日：2006-03-14
申请号：US10729480
申请日：2003-12-05
申请人： Richard W. McBride
发明人： Richard W. McBride
IPC分类号： F02C9/00
CPC分类号： B64D31/14 , F02C9/00 , F02C9/285 , G05B13/021
摘要： A method for achieving linear engine thrust response comprising the steps of measuring a throttle position (FNRQ), measuring a plurality of engine parameters, inputting the plurality of engine parameters and the throttle position into a plurality of schedules to produce a plurality of outputs, combining the plurality of outputs to produce a part power scheduled airflow (W2RSCH), and using the W2RSCH to produce a near linear thrust response of the engine.
摘要翻译：一种用于实现线性发动机推力响应的方法，包括以下步骤：测量节气门位置（FNRQ），测量多个发动机参数，将多个发动机参数和节气门位置输入到多个调度表中以产生多个输出，组合多个输出以产生部分功率调度气流（W 2 RSCH），并且使用W 2 RSCH来产生发动机的近似线性推力响应。

3. 发明授权

US08239114B2 Methods and systems for modulating fuel flow for gas turbine engines 有权
标题翻译：用于调节燃气轮机发动机燃油流量的方法和系统
公开(公告)号：US08239114B2
公开(公告)日：2012-08-07
申请号：US12368472
申请日：2009-02-10
申请人： Jerry Lee Goeke , Brandon Philip Williams
发明人： Jerry Lee Goeke , Brandon Philip Williams
IPC分类号： G06F19/00
CPC分类号： F02C9/285 , F23R2900/00013
摘要： A method of combustion stability control for a gas turbine engine is provided, and includes the steps of receiving by a stability controller, information regarding environmental and operating conditions, and comparing the environmental and operating conditions to pre-programmed information to determine if a likelihood of combustion instability exists. The method further includes the steps of determining optimal fuel modulation frequency and amplitude for the environmental condition to reduce combustion instability, if a likelihood of combustion instability exists, and actuating at least one fuel modulation valve to, at the optimal fuel modulation frequency and amplitude, reduce combustion instability, if a likelihood of combustion instability exists. Systems for modulating fuel flow are also provided.
摘要翻译：提供了一种用于燃气涡轮发动机的燃烧稳定性控制的方法，并且包括以下步骤：由稳定性控制器接收关于环境和操作条件的信息，以及将环境和操作条件与预编程信息进行比较，以确定是否存在燃烧不稳定存在。该方法还包括以下步骤：如果存在燃烧不稳定的可能性，则确定用于环境条件的最佳燃料调制频率和幅度以减少燃烧不稳定性，并且以最佳燃料调制频率和振幅致动至少一个燃料调节阀，如果存在燃烧不稳定的可能性，则减少燃烧不稳定性。还提供用于调节燃料流量的系统。

4. 发明授权

US07262712B2 Helicopter tactile exceedance warning system 有权
标题翻译：直升机触觉超警预警系统
公开(公告)号：US07262712B2
公开(公告)日：2007-08-28
申请号：US10821974
申请日：2004-04-12
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： G08B23/00
CPC分类号： F02C9/285 , B64C13/10 , B64C27/04 , B64D43/00 , F05D2270/303 , F05D2270/3032 , F05D2270/44
摘要： A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.
摘要翻译：直升机触觉入门警告系统包括控制杆和附接到控制棒的触觉警告装置。还提供用于输入安全温度曲线的计算机或微处理器和键盘以及用于测量涡轮机输出温度的热电偶。计算机将实际温度与安全温度曲线进行比较，并在实际温度超出安全温度曲线的情况下产生信号以激活触觉报警装置，以警告飞行员中止启动。触发警告装置在飞行操作期间也会发生过应力状况，从而警告飞行员采取纠正措施。此外，触觉警告可以以第一频率作为早期警告激活，然后以第二频率激活，作为即将发生危险的指示。

5. 发明申请

US20160305346A1 CONTROL APPARATUS FOR A GAS-TURBINE AEROENGINE 审中-公开
标题翻译：一种气体涡轮机的控制装置
公开(公告)号：US20160305346A1
公开(公告)日：2016-10-20
申请号：US14689306
申请日：2015-04-17
申请人： HONDA MOTOR CO., LTD.
发明人： Keisuke Kawai
IPC分类号： F02C9/28 , F02D31/00 , F02C9/18
CPC分类号： F02C9/285 , F02C9/18 , F02D31/007
摘要： An apparatus for controlling a gas-turbine aeroengine is configured to calculate a fuel command to supply fuel based on a calculated desired rotational speed of a low-pressure turbine calculated from an operation angle of a thrust lever installed at an aircraft cockpit pilot's seat, determines whether it is a time point for outputting a command to open/close a bleed-off valve equipped at a high-pressure compressor connected to a high-pressure turbine and to supply the fuel command based on the time point when it is determined to be the time point for outputting the command to open/close the bleed-off valve.
摘要翻译：用于控制燃气涡轮机航空发动机的装置被配置为基于由安装在飞行器驾驶舱驾驶员座椅处的推力杆的操作角度计算出的计算出的低压涡轮机的所需旋转速度来计算燃料命令，确定是否输出命令来打开/关闭配备在连接到高压涡轮机的高压压缩机的排气阀的指令的时间点，并且基于确定为时间点的时间点来提供燃料命令输出打开/关闭泄放阀的命令的时间点。

6. 发明授权

US07856295B2 Device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system comprising same 有权
标题翻译：用于发出授权以对包括其的飞机发动机和发动机控制系统的操作条件起作用的装置
公开(公告)号：US07856295B2
公开(公告)日：2010-12-21
申请号：US11721035
申请日：2005-12-12
申请人： Patrick Zaccaria , Marie-Pierre Fuertes
发明人： Patrick Zaccaria , Marie-Pierre Fuertes
IPC分类号： G01C5/00
CPC分类号： F02C9/285 , F02C9/56 , F05D2260/80
摘要： A device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system includes a first unit for determining particular parameters concerning the aircraft, including the position of a power lever controlling the supply of fuel to the engine, and a second unit for determining, based on the particular parameters, whether the aircraft is in a state authorizing an action on the operating conditions of the engine and for issuing, as the case may be, a corresponding authorization signal.
摘要翻译：用于发出对飞机发动机和发动机控制系统的操作条件起作用的授权的装置包括用于确定与飞行器有关的特定参数的第一单元，包括控制向发动机供应燃料的动力杆的位置，以及第二单元单元，用于基于特定参数来确定飞机是否处于授权对发动机的操作条件采取行动的状态，并且根据情况发出相应的授权信号。

7. 发明授权

US07107757B2 Aircraft provided with thrust reversers 有权
标题翻译：飞机配有推力反向器
公开(公告)号：US07107757B2
公开(公告)日：2006-09-19
申请号：US10932342
申请日：2004-09-02
申请人： Joan Andre , Laurent Andrieu
发明人： Joan Andre , Laurent Andrieu
IPC分类号： F02K3/02
CPC分类号： F02C9/56 , B64D27/18 , B64D31/12 , F02C9/285 , F02K1/76 , Y02T50/671
摘要： Some but not all engines of an aircraft are provided with thrust reversers. A safety device disables, at least from the position corresponding to idling, the action of the throttles corresponding to the engines devoid of thrust reversers when the thrust reversers are controlled to deployment.
摘要翻译：一些但不是所有的飞机发动机都配有推力反向器。至少从与空转相对应的位置，当推力反向器被控制到展开时，对应于没有推力反向器的发动机的节流阀的作用不起作用。

8. 发明申请

US20050225456A1 Helicopter tactile exceedance warning system 有权
标题翻译：直升机触觉超警预警系统
公开(公告)号：US20050225456A1
公开(公告)日：2005-10-13
申请号：US10821974
申请日：2004-04-12
申请人： Randall Greene
发明人： Randall Greene
IPC分类号： B64C13/10 , B64C27/04 , B64C27/56 , B64D31/02 , B64D43/00 , B64D45/00 , F02C7/26 , F02C9/28 , G08B21/00
CPC分类号： F02C9/285 , B64C13/10 , B64C27/04 , B64D43/00 , F05D2270/303 , F05D2270/3032 , F05D2270/44
摘要： A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.
摘要翻译：直升机触觉入门警告系统包括控制杆和附接到控制棒的触觉警告装置。还提供用于输入安全温度曲线的计算机或微处理器和键盘以及用于测量涡轮机输出温度的热电偶。计算机将实际温度与安全温度曲线进行比较，并在实际温度超出安全温度曲线的情况下产生信号以激活触觉报警装置，以警告飞行员中止启动。触发警告装置在飞行操作期间也会发生过应力状况，从而警告飞行员采取纠正措施。此外，触觉警告可以以第一频率作为早期警告激活，然后以第二频率激活，作为即将发生危险的指示。

9. 发明授权

US10077720B2 Control apparatus for a gas-turbine aeroengine 有权
公开(公告)号：US10077720B2
公开(公告)日：2018-09-18
申请号：US14689306
申请日：2015-04-17
申请人： HONDA MOTOR CO., LTD.
发明人： Keisuke Kawai
IPC分类号： F02C9/28 , F02C9/18 , F02D31/00
CPC分类号： F02C9/285 , F02C9/18 , F02D31/007
摘要： An apparatus for controlling a gas-turbine aeroengine is configured to calculate a fuel command to supply fuel based on a calculated desired rotational speed of a low-pressure turbine calculated from an operation angle of a thrust lever installed at an aircraft cockpit pilot's seat, determines whether it is a time point for outputting a command to open/close a bleed-off valve equipped at a high-pressure compressor connected to a high-pressure turbine and to supply the fuel command based on the time point when it is determined to be the time point for outputting the command to open/close the bleed-off valve.

10. 发明授权

US09933336B2 Gas turbine having fuel monitoring 有权
公开(公告)号：US09933336B2
公开(公告)日：2018-04-03
申请号：US14488686
申请日：2014-09-17
申请人： ALSTOM Technology Ltd
发明人： Mengbin Zhang , Klaus-Dieter Liedtke , Wenceslao Granados Gomez
IPC分类号： F02C9/46 , G01M15/14 , F02C9/42 , F23N5/24 , F02C9/28 , F02C7/25 , F02C9/26 , F23N1/00 , F01D21/14 , F02C9/32 , F02C7/22 , F02C7/228
CPC分类号： G01M15/14 , F01D21/14 , F02C7/22 , F02C7/222 , F02C7/228 , F02C7/25 , F02C9/26 , F02C9/28 , F02C9/285 , F02C9/32 , F02C9/42 , F02C9/46 , F05B2260/80 , F05B2270/309 , F05B2270/335 , F05B2270/337 , F05D2260/80 , F05D2270/309 , F05D2270/335 , F23N1/00 , F23N5/24 , F23N5/242 , F23N5/245 , F23N5/247 , F23N2041/20
摘要： The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve and at least one burner of a gas turbine during the operation of the gas turbine. In order to detect a fuel leakage, the fuel consumption is approximated in accordance with the mechanical power of the gas turbine, the fuel amount fed to the fuel distribution system is determined, and the leakage flow is determined from the difference between the fed fuel amount and the fuel consumption. The invention further relates to a gas turbine for performing such a method.

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