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公开(公告)号：US4488236A
公开(公告)日：1984-12-11
申请号：US369302
申请日：1982-04-16
CPC分类号： F02C9/28 , G05D1/0005 , G05D1/0858 , F05D2220/329 , F05D2270/07 , Y02T50/671
摘要： A digital fuel control (53) for a helicopter engine (20) controls fuel flow (52) to the engine in response to a turbine reference speed (62) determined in a normal mode (FIG. 5) to be a rated speed, in a fade-in mode (FIG. 6) to be incremented (117, 120) to an estimated optimum minimum speed (114, 115, 125), in an optimizer mode (FIG. 7) to be incremented (138) in a direction (137) leading to least fuel consumption (135), and in a fade-out mode (FIG. 8) to be incremented (151, 153) back to rated speed (154). The invention provides an engine reference speed which results in minimum fuel consumption during cruise flight.
摘要翻译： 用于直升机发动机（20）的数字燃料控制（53）响应于以正常模式（图5）确定的涡轮参考速度（62）将发动机的燃料流量（52）控制为额定转速， 要在优化器模式（图7）中递增（138）的渐进模式（图6）被增加（117,120）到估计的最佳最小速度（114,115,125） （137）导致最小燃料消耗（135），并且在淡出模式（图8）中增加（151,153）返回到额定速度（154）。 本发明提供了在巡航飞行期间导致最小燃料消耗的发动机参考速度。
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公开(公告)号：US4291532A
公开(公告)日：1981-09-29
申请号：US45851
申请日：1979-06-05
申请人： Keith Robinson
发明人： Keith Robinson
IPC分类号： F02C9/08
摘要： This invention relates to a fuel supply system for an engine having a main fuel flow scheduling device, an auxiliary fuel flow scheduling device, a power demand adjuster operative to adjust both scheduling device, and a failure detector capable of detecting failure of the main scheduling device and of making the auxiliary scheduling device operative to control fuel flow to the engine following such failure. In the past, fuel systems of this kind have given an abrupt change of fuel flow on changeover to the auxiliary scheduling device giving the possibility of damage to the engine and danger to human life.In the present invention a metering valve 201 forms part of the auxiliary scheduling device 201, 246, 209, 221, 222, 231, 232, 233, 234 for continuous adjustment of the flow to the engine permitted by the main scheduling device 184. Whenever the auxiliary scheduling device begins to control fuel flow, the flow remains constant at the instant of changeover at the value determined by the main scheduling device just prior to the changeover.The auxiliary scheduling device may be arranged for slow self-variation after the changeover to alter the relation between fuel flow to the engine and the setting of the power demand adjuster.
摘要翻译： 本发明涉及一种用于发动机的燃料供应系统，该发动机具有主燃料流量调度装置，辅助燃料流量调度装置，可调节调度装置的功率需求调节器和能够检测主调度装置故障的故障检测器 并且使得辅助调度装置可操作以在发生故障之后控制到发动机的燃料流。 过去，这种燃油系统在辅助调度装置的转换时，燃油流量急剧变化，给予发动机损坏的可能性和人身伤害。 在本发明中，计量阀201形成辅助调度装置201,246,209,221,222,231,232,233,234的一部分，用于连续调节由主调度装置184允许的发动机的流量。每当 辅助调度装置开始控制燃料流量，流量在切换之前由主调度装置确定的值保持恒定。 辅助调度装置可以被设置为在切换之后缓慢的自变量以改变到发动机的燃料流量与功率需求调节器的设定之间的关系。
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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
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。
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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
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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5.发明授权Regulating device for a prime mover, more particularly for a single-spool gas turbine 失效用于原动机的调节装置，更特别地用于单线轴燃气轮机
公开(公告)号：US4018045A
公开(公告)日：1977-04-19
申请号：US523801
申请日：1974-11-14
摘要： A regulating system for a prime mover, especially a single-spool gas turbine for use in propelling a motor vehicle or aircraft, in which system there is provided a first speed governor for controlling the fuel flow or input power and a second speed governor for controlling the power output. The two speed governors act concurrently in response to the speed of the prime mover and regulate the power input and power output independently of one another.
摘要翻译： 用于原动机的调节系统，特别是用于推进机动车辆或飞行器的单线轴燃气轮机，其中提供了用于控制燃料流量或输入功率的第一调速器和用于控制的第二调速器 功率输出。 两个调速器响应于原动机的速度同时起作用，并且彼此独立地调节功率输入和功率输出。
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公开(公告)号：US4010606A
公开(公告)日：1977-03-08
申请号：US654668
申请日：1976-02-02
申请人： Kenneth Peter Hansen
发明人： Kenneth Peter Hansen
CPC分类号： F02C9/28
摘要： An improved automatic fuel shutoff system is provided for a turbine type power plant which incorporates (1) sensing means responsive to a preselected abnormal engine operating condition for initially cutting off fuel flow to the engine and (2) latching means for maintaining the cutoff until engine conditions favorable for a normal restart are obtained.
摘要翻译： 提供了一种用于涡轮机型发电厂的改进的自动燃料切断系统，其包括（1）响应于预先选择的异常发动机操作条件的感测装置，用于初始切断到发动机的燃料流量;以及（2）用于将截止直到发动机 获得有利于正常重启的条件。
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公开(公告)号：US3981141A
公开(公告)日：1976-09-21
申请号：US648018
申请日：1976-01-12
申请人： Trevor Stanley Smith
发明人： Trevor Stanley Smith
摘要： A fuel control system for a gas turbine engine includes a metering device and a servo-operated control valve through which fuel flows from the metering device to the engine. A pilot valve for the servo-operated control valve is responsive to engine speed and is also operable, when a metering device control member moves past a predetermined position, to cause the servo-operated control valve to reduce fuel flow.
摘要翻译： 用于燃气涡轮发动机的燃料控制系统包括计量装置和伺服操作的控制阀，燃料通过该控制阀从计量装置流向发动机。 用于伺服操作的控制阀的先导阀响应于发动机转速，并且当计量装置控制构件移动超过预定位置时，也可操作，以使伺服操作的控制阀减少燃料流量。
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公开(公告)号：US3977182A
公开(公告)日：1976-08-31
申请号：US588696
申请日：1975-06-20
申请人： Dennis E. Schroff
发明人： Dennis E. Schroff
CPC分类号： F02C9/52
摘要： A fuel and burner variable geometry (BVG) control for a gas turbine engine. Fuel is controlled in response to the product of desired overall fuel-air ratio and a value of air flow derived from gas generator turbine speed. The desired fuel-air ratio is controlled by a speed governor, and by acceleration and deceleration limits varied as a function of measured burner inlet temperature. A compensated turbine inlet temperature (TIT) signal is derived from measurement of actual turbine inlet temperature and acceleration or deceleration compensation based upon rate of change of the desired fuel-air ratio. The difference between the compensated TIT and the burner inlet temperature (BIT) is the burner temperature rise.The setting of air flow control devices in the combustion apparatus (BVG) determines the ratio of primary to total air. The desired ratio to control BVG is computed by dividing burner temperature rise by flame temperature rise. Flame temperature rise is the difference between the desired flame temperature and the measured BIT. The desired flame temperature is scheduled as a function of BIT and BVG. The ratio of primary to total air may be limited temporarily during starting of the engine.
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9.发明授权Method of and apparatus for preventing compressor stall in a gas turbine engine 失效用于防止燃气涡轮发动机中的压缩机失速的方法和装置
公开(公告)号：US3938319A
公开(公告)日：1976-02-17
申请号：US497017
申请日：1974-08-13
申请人： Faulkner C. Thomson
发明人： Faulkner C. Thomson
摘要： A method of and apparatus for detecting air distortion at the inlet of a turbine engine and adjusting fuel flow to anticipate and prevent compressor stall. A plurality of pressure taps are arranged in a spaced relation around the periphery of the engine inlet. A distortion detector senses the differential pressure between the instantaneous pressure at each pressure tap and the ambient pressure of a reference pressure chamber which communicates with the plurality of pressure taps. At a predetermined pressure differential the distortion detector activates a solenoid-operated fuel bypass valve which reduces fuel flow to the fuel nozzles of the gas turbine engine.
摘要翻译： 一种用于检测燃气涡轮发动机入口处的空气变形并调节燃料流量以预测和防止压缩机失速的方法和装置。 多个压力抽头以发动机入口周边的间隔布置。 变形检测器检测每个压力抽头的瞬时压力与与多个压力抽头连通的参考压力室的环境压力之间的压差。 在预定的压力差下，失真检测器激活电磁操作燃料旁通阀，其减少燃料涡轮发动机的燃料喷嘴的燃料流量。
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10.发明授权Method of and apparatus for control of helicopter gas turbine engine during auto rotation 失效自动旋转期间直升机燃气轮机的控制方法及装置
公开(公告)号：US3893293A
公开(公告)日：1975-07-08
申请号：US38297473
申请日：1973-07-26
申请人： BENDIX CORP
发明人： MOORE JR ROBERT G
CPC分类号： B64C27/32
摘要： Engine governor control apparatus for controlling the power output of a helicopter gas turbine engine having independently rotating gas generator and power turbines. During normal operation gas generator turgine speed is sensed and controlled by a first governor and power turbine speed is sensed and controlled by a second operatively connected to the first governor for resetting the speed setting of the first governor. During helicopter practice auto-rotation, the second governor is rendered inoperative to reset the first governor at a predetermined position of a manually actuated engine power request lever to thereby eliminate transient undershoot of gas generator turbine speed during a power turbine load reduction prior to auto-rotation as well as eliminate a tendency for gas generator speed instability while operating in the practice autorotation mode.
摘要翻译： 用于控制具有独立旋转的气体发生器和动力涡轮机的直升机燃气轮机的功率输出的发动机调速器控制装置。 在正常操作期间，气体发生器的翻转速度由第一调速器感测和控制，并且功率涡轮机速度由操作地连接到第一调速器的第二调速器的第二传感器检测和控制，以复位第一调速器的速度设置。 在直升机实践自动旋转期间，第二调速器不起作用以将第一调速器复位在手动致动的发动机功率请求杆的预定位置，从而消除在动力涡轮机负载减小之前的气体发生器涡轮机转速的瞬时下冲， 并且在实践自动旋转模式下操作时消除了气体发生器速度不稳定的趋势。
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