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71. 发明授权

US4928482A Control of high compressor vanes and fuel for a gas turbine engine 失效
标题翻译：控制用于燃气轮机的高压缩机叶片和燃料
公开(公告)号：US4928482A
公开(公告)日：1990-05-29
申请号：US246728
申请日：1988-09-20
申请人： Robert R. Pollak , Juan A. Marcos
发明人： Robert R. Pollak , Juan A. Marcos
IPC分类号： F02C9/28 , F02C9/54 , F02K1/16 , F02K1/17
CPC分类号： F02C9/54 , F02C9/28 , F02K1/16 , F02K1/17 , F05D2270/051
摘要： The time responsiveness and engine stability for an acceleration and deceleration engine transient is enhanced by a control mechanism that synchronously adjusts fuel flow and high pressure compressor vane position as a function of corrected low pressure compressor speed in a twin spool axial flow turbine power plant. The acceleration and deceleration mode is targeted by power lever position and the target is attained by adjusting the vane position at a constant high pressure compressor speed and returned to a fuel efficient and engine stable steady state operating line by concomittantly adjusting fuel flow and vane position.
摘要翻译：加速和减速发动机瞬态的时间响应和发动机稳定性通过一个控制机构得到增强，该控制机构可同时调整燃油流量和高压压缩机叶片位置，作为双轴流轴式涡轮发电厂中校正的低压压缩机转速的函数。加速和减速模式由动力杆位置定位，目标通过以恒定的高压压缩机转速调节叶片位置，并通过调节燃油流量和叶片位置返回到燃油效率和发动机稳定的稳态操作线。

72. 发明授权

US4414807A Method and apparatus for controlling a gas turbine engine 失效
标题翻译：用于控制燃气涡轮发动机的方法和装置
公开(公告)号：US4414807A
公开(公告)日：1983-11-15
申请号：US214376
申请日：1980-12-08
申请人： Walter B. Kerr
发明人： Walter B. Kerr
IPC分类号： F02C9/28 , F02K1/17 , F02K1/18
CPC分类号： F02K1/17 , F02C9/28 , F05D2270/102
摘要： A gas turbine engine control for an engine which experiences airflow distortion at the engine inlet face plane uses a static pressure measurement upstream of the face plane along with a corrected rotor speed to generate a signal indicative of the average total pressure at the engine face plane. This signal is combined with a total pressure signal from elsewhere in the engine to generate a pressure ratio signal which is compared to the scheduled pressure ratio for the current operating conditions. Control logic then adjusts either the fuel flow rate to the burners or the area of the exhaust nozzle in response to the difference between these pressure ratios.
摘要翻译：用于在发动机入口面平面处经历气流变形的发动机的燃气涡轮发动机控制使用在面平面上游的静压测量以及修正的转子速度，以产生指示发动机平面的平均总压的信号。该信号与来自发动机其他地方的总压力信号组合以产生与当前操作条件的预定压力比进行比较的压力比信号。控制逻辑然后响应于这些压力比之间的差异来调节燃烧器的燃料流量或排气喷嘴的面积。

73. 发明授权

US4242864A Integrated control system for a gas turbine engine 失效
标题翻译：燃气轮机发动机综合控制系统
公开(公告)号：US4242864A
公开(公告)日：1981-01-06
申请号：US909608
申请日：1978-05-25
申请人： Jack E. Cornett , Andrew A. Saunders, Jr. , Ira E. Marvin , Richard S. Beitler
发明人： Jack E. Cornett , Andrew A. Saunders, Jr. , Ira E. Marvin , Richard S. Beitler
IPC分类号： F02C9/48 , F02K1/17 , F02K3/06
CPC分类号： F02C9/48 , F02K1/17
摘要： An integrated control system for a gas turbine engine of the turbofan type receives signals from a plurality of engine sensors and from the engine operator and generates control signals therefrom. A first control signal regulates the fan exhaust nozzle area in order to control inlet throat Mach number to maintain a low level of engine noise. Additional control signals regulate fuel flow to control engine thrust and fan pitch to control fan speed. A plurality of schedules are utilized to maintain a predetermined relationship between the controlled parameters and a number of fixed and calculated limits can override the control signals to prevent unsatisfactory engine performance.
摘要翻译：用于涡轮风扇式燃气涡轮发动机的集成控制系统从多个发动机传感器和发动机操作器接收信号并从其产生控制信号。第一个控制信号调节风扇排气喷嘴区域，以控制入口喉部马赫数，以保持低水平的发动机噪音。额外的控制信号调节燃油流量以控制发动机推力和风扇间距，以控制风扇转速。使用多个时间表来维持受控参数之间的预定关系，并且许多固定和计算的限制可以覆盖控制信号以防止不令人满意的发动机性能。

74. 发明授权

US4159625A Control for gas turbine engine 失效
标题翻译：燃气轮机发动机控制
公开(公告)号：US4159625A
公开(公告)日：1979-07-03
申请号：US764610
申请日：1977-02-01
申请人： Walter B. Kerr
发明人： Walter B. Kerr
IPC分类号： F02C9/48 , F02K1/16 , F02K1/17 , F02K3/02 , F02C9/08
CPC分类号： F02K1/17
摘要： Increased thrust during the transonic flight mode of an aircraft powered by a gas turbine engine is realized by a closed loop control that closes the loop on the pressure ratio across the fan by adjusting fuel flow and/or exhaust nozzle area in a turbofan, variable exhaust nozzle installation. Fan pressure ratio is scheduled as a function of corrected fan speed and actual pressure ratio provides an error signal to readjust engine operation to null out this error signal. A turbine inlet temperature limit signal is generated to prevent inadvertent overheating and it or this pressure ratio error signal is selected for providing the lower fuel flow value.
摘要翻译：由燃气涡轮发动机提供动力的飞机在跨音速飞行模式期间的推力增加是通过闭环控制实现的，该闭环控制通过调节涡轮风扇，可变排气中的燃料流量和/或排气喷嘴面积来关闭跨过风扇的压力比的环路喷嘴安装。风扇压力比作为校正风扇速度的函数进行调整，实际压力比提供误差信号以重新调整发动机运行，以消除该误差信号。产生涡轮进口温度限制信号以防止意外过热，或者选择该压力比误差信号以提供较低的燃料流量值。

75. 发明授权

US3854287A Self-trimming control for turbofan engines 失效
标题翻译：涡轮发动机的自调整控制
公开(公告)号：US3854287A
公开(公告)日：1974-12-17
申请号：US42775473
申请日：1973-12-26
申请人： UNITED AIRCRAFT CORP
发明人： REMBOLD J
IPC分类号： B64D31/14 , F02C9/48 , F02K1/16 , F02K1/17 , G05B11/00 , F02C3/06 , F02C9/04 , F02K3/06
CPC分类号： F02K1/17 , B64D31/14 , F02C9/48 , F02K1/16 , G05B11/00
摘要： A twin spool turbofan engine control is designed which maintains engine thrust and stall margin at nominal levels as the operating characteristics of the engine high spool deteriorates with operating hours, increased altitude or increased power extraction. An electronic supervisory control monitors the high rotor speed and the fan turbine inlet temperature relationships for all engine power settings from intermediate to maximum, and the electronic supervisory control schedules are adjusted based upon shifts in the relationships. In one embodiment the fuel flow to the engine is trimmed in response to a desired fan turbine inlet temperature schedule determined as a function of engine inlet temperature and main burner pressure, the schedule being modified in response to the difference between operating high rotor speed and a reference rotor speed which in turn is a function of engine inlet temperature. In another embodiment the engine fuel flow is trimmed in response to a high rotor speed schedule determined as a function of engine inlet temperature and biased by the difference between a sensed fan turbine inlet temperature and a reference fan turbine inlet temperature. In both embodiments the area of a variable geometry nozzle in the engine is trimmed to modify the fan airflow.
摘要翻译：双轴卷烟涡轮风扇发动机控制被设计成将发动机推力和失速余量保持在额定水平，因为发动机高阀芯的操作特性随着运行小时，高度增加或功率提升增加而下降。电子监控控制监测从中间到最大的所有发动机功率设置的高转子速度和风扇涡轮机入口温度关系，并且基于关系的变化调整电子监控控制计划。在一个实施例中，响应于作为发动机入口温度和主燃烧器压力的函数确定的期望的风扇涡轮入口温度调度来修整到发动机的燃料流，该调度响应于操作高转子速度和参考转子速度又是发动机入口温度的函数。在另一个实施例中，响应于作为发动机入口温度的函数确定的高转子速度调节并且通过所感测的风扇涡轮机入口温度和参考风扇涡轮机入口温度之间的差被偏置而调整发动机燃料流量。在两个实施例中，修整发动机中可变几何喷嘴的面积以修改风扇气流。

76. 发明授权

US3764785A Turbine power plant control system 失效
标题翻译：涡轮发电厂控制系统
公开(公告)号：US3764785A
公开(公告)日：1973-10-09
申请号：US3764785D
申请日：1970-10-29
申请人： UNITED AIRCRAFT CORP
发明人： HARNER K , SCHNEIDER R
IPC分类号： F02C9/32 , F02C9/44 , F02K1/17 , F02C9/04
CPC分类号： F02C9/44 , F02C9/32 , F02K1/17
摘要： Thrust of a turbine type of power plant is controlled by closing the loop on fuel flow as a function of the difference between the desired thrust and a precalculated inferred thrust signal in combination with an optimization system for obtaining optimum thrust specific fuel consumption.
摘要翻译：通过结合用于获得最佳推力特定燃料消耗的优化系统，结合用于获得最佳推力特定燃料消耗的优化系统，关闭作为期望推力和预先计算的推断推力信号之间的差的燃料流量循环来控制涡轮机类型的发电厂的推力。

77. 发明授权

US3360940A Fuel supply system for a jet propulsion engine including reheaters 失效
标题翻译：用于喷气推进发动机的燃料供应系统，包括再热器
公开(公告)号：US3360940A
公开(公告)日：1968-01-02
申请号：US55882366
申请日：1966-06-20
申请人： DOWTY FUEL SYST LTD
发明人： RONALD RIMMER
IPC分类号： F02C7/22 , F02K1/17 , F02K3/10
CPC分类号： F02K1/17 , F02C7/22 , F02K3/10

78. 发明授权

US3301309A Fuel control systems for gas turbine engines 失效
标题翻译：燃气轮机发动机燃油控制系统
公开(公告)号：US3301309A
公开(公告)日：1967-01-31
申请号：US42860265
申请日：1965-01-21
申请人： DOWTY FUEL SYST LTD
发明人： TYLER STANLEY R
IPC分类号： F02K1/17
CPC分类号： F02K1/17

79. 发明授权

US3298180A Single-control regulating system for afterburning by-pass turbojets 失效
标题翻译：用于后燃烧旁通涡轮喷气发动机的单控制调节系统
公开(公告)号：US3298180A
公开(公告)日：1967-01-17
申请号：US37131464
申请日：1964-06-01
申请人： SNECMA
发明人： ALFRED TRINKLER , ALBERT STIEGLITZ , FRANCOIS JUMELLE LOUIS
IPC分类号： F02K1/16 , F02K1/17 , F02K3/00 , F02K3/10
CPC分类号： F02K3/00 , F02K1/16 , F02K1/17 , F02K3/10

80. 发明授权

US3085395A Afterburner fuel control 失效
公开(公告)号：US3085395A
公开(公告)日：1963-04-16
申请号：US6509560
申请日：1960-10-26
申请人： GEN ELECTRIC
发明人： CHARLES O'NEILL WILLIAM
IPC分类号： F02C9/16 , F02C9/32 , F02K1/17 , F02K3/10
CPC分类号： F02K1/17 , F02C9/16 , F02C9/32 , F02K3/10

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