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101. 发明授权

US5197280A Control system and method for controlling a gas turbine engine 失效
标题翻译：用于控制燃气轮机的控制系统和方法
公开(公告)号：US5197280A
公开(公告)日：1993-03-30
申请号：US607786
申请日：1990-10-29
申请人： R. Sheldon Carpenter , William L. Gazzola
发明人： R. Sheldon Carpenter , William L. Gazzola
IPC分类号： F02C9/28 , F02K1/17
CPC分类号： F02K1/17 , F02C9/28 , F05D2270/051
摘要： A control system for a gas turbine engine receives a signal representative of a first target engine operating condition and also receives a signal representative of an actual engine condition. The system produces an error signal representative of the difference between the target signal and the actual engine condition signal. A gain means adjusts the gain of the error signal to be equal to the desired change in the controlled engine parameter. The output of the gain means is then coupled to an activator of the engine which controls the parameter.
摘要翻译：用于燃气涡轮发动机的控制系统接收表示第一目标发动机运行状态的信号，并且还接收表示实际发动机状态的信号。该系统产生代表目标信号与实际发动机状况信号之差的误差信号。增益装置将误差信号的增益调整为等于受控发动机参数中所需的变化。增益装置的输出然后被耦合到控制参数的发动机的启动器。

102. 发明授权

US4809500A Transient control system for gas turbine engine 失效
标题翻译：燃气轮机发动机瞬态控制系统
公开(公告)号：US4809500A
公开(公告)日：1989-03-07
申请号：US10045
申请日：1987-02-03
申请人： William C. Roberts, Jr.
发明人： William C. Roberts, Jr.
IPC分类号： F02C9/28 , F02K1/17
CPC分类号： F02K1/17 , F02C9/28 , F05D2270/04
摘要： A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transient engine operation primarily in the combat box of between approximately 0.4 to 1.2 Mach number at an altitude between 10,000 to 30,000 feet of the flight envelope and does maintain higher compressor rpm, turbine inlet temperature, and engine air flow at the idle or part power thrust settings by concomitantly adjusting fuel flow and engine exhaust nozzle area thereby enhancing thrust response, low cycle fatigue life, and engine stability.

103. 发明授权

US3908363A Aero gas turbine afterburner control 失效
标题翻译： AERO GAS TURBINE AFTERBURNER CONTROL
公开(公告)号：US3908363A
公开(公告)日：1975-09-30
申请号：US37590373
申请日：1973-07-02
申请人： MTU MUENCHEN GMBH
发明人： BAUERFEIND KLAUS
IPC分类号： F02K1/16 , F02K1/17 , F02K1/18
CPC分类号： F02K1/16 , F02K1/17
摘要： Aero gas turbine engine equipped with an afterburner and a final nozzle having a variable discharge area in which a direct mechanical or electrical connection exists between the nozzle actuating mechanism and the afterburner fuel control unit for controlling the degree of after-burning as a function of the actual nozzle discharge area during transient engine operating conditions with the engine throttle moving in the after-burning range above a predetermined speed. A working line trim unit of limited authority is provided for making minor adjustments to the nozzle discharge area during steady state operation, while the degree of afterburning signal from the nozzle to the fuel control unit is held constant. This working line trim unit is locked out of the control cycle during transient operating conditions so as to assure the direct control of the degree of afterburning as a function of the actual discharge area during these transient conditions.

104. 发明授权

US3656301A Compensated feedback gas turbine augmentation control system 失效
标题翻译：补偿反馈气体涡轮增压控制系统
公开(公告)号：US3656301A
公开(公告)日：1972-04-18
申请号：US3656301D
申请日：1969-11-25
申请人： GEN ELECTRIC
发明人： KATZ HERBERT
IPC分类号： F02C20060101 , F02C9/00 , F02K1/00 , F02K1/16 , F02K3/00 , F02K3/08
CPC分类号： F02K1/17
摘要： A control system for a gas turbine engine having an augmenter combustion system and a variable area exhaust nozzle. The control system is applicable to both turbofan and to straight turbojet engines. In the turbofan application, a signal generator schedules the exhaust nozzle area as a function of throttle position and augmenter fuel flow as a function of exhaust nozzle area. An error signal generated between desired fan duct mach number and actual fan duct mach number is integrated and applied to both the augmenter fuel rate generator and the exhaust nozzle area generator. In this manner, during steady state operations, the exhaust nozzle position maintains a desired mach number and the throttle lever position maintains augmenter fuel flow rates. During transients, the exhaust nozzle area position controls the augmenter fuel flow. In the turbojet application the fan duct mach number error signal is replaced by a turbine temperature error signal and the system operates essentially as described above.
摘要翻译：一种用于具有增压器燃烧系统和可变面积排气喷嘴的燃气涡轮发动机的控制系统。控制系统适用于涡轮风扇和直喷涡轮喷气发动机。在涡轮风扇应用中，信号发生器作为排气喷嘴区域的函数调节作为节气门位置和增压器燃料流量的函数的排气喷嘴区域。在所需的风扇管道马赫数和实际的风扇管道马赫数之间产生的误差信号被集成并应用于增压器燃料发生器和排气喷嘴区域发生器。以这种方式，在稳态操作期间，排气喷嘴位置保持期望的马赫数，并且节流杆位置保持增加的燃料流量。在瞬变期间，排气喷嘴区域位置控制增压器燃料流量。在涡轮喷射应用中，风扇管道马赫数误差信号由涡轮机温度误差信号代替，并且系统基本上如上所述地操作。

105. 发明授权

US3331204A Standby afterburner operation system 失效
标题翻译：待机加力器操作系统
公开(公告)号：US3331204A
公开(公告)日：1967-07-18
申请号：US52563966
申请日：1966-02-07
申请人： GEN ELECTRIC
发明人： LOVE PENDER L
IPC分类号： F02K1/16 , F02K1/17 , F02K3/10
CPC分类号： F02K1/17 , F02K1/16 , F02K3/10

106. 发明授权

US3300979A Apparatus for controlling the afterburner load of a jet engine according to the jet pipe aperture 失效
公开(公告)号：US3300979A
公开(公告)日：1967-01-31
申请号：US3300979D
CPC分类号： F02K1/17

107. 发明授权

US3289411A Coordinated afterburner fuel control and exhaust nozzle area control for gas turbine engine 失效
标题翻译：用于燃气轮机的辅助加燃料燃料控制和排气喷嘴面积控制
公开(公告)号：US3289411A
公开(公告)日：1966-12-06
申请号：US50144365
申请日：1965-10-22
申请人： BENDIX CORP
发明人： ROGERS FRANCIS R , MCCOMBS JR HOWARD L , MIKE SNIDER
IPC分类号： F02C9/16 , F02K1/16 , F02K1/17 , F02K3/10
CPC分类号： F02K1/17 , F02C9/16 , F02K1/16 , F02K3/10

108. 发明授权

US3283500A Fuel feed and power control apparatus for combustion engines 失效
公开(公告)号：US3283500A
公开(公告)日：1966-11-08
申请号：US50194165
申请日：1965-10-22
申请人： BENDIX CORP
发明人： ROGERS FRANCIS R , MCCOMBS JR HOWARD L , MIKE SNIDER
IPC分类号： F02C9/16 , F02K1/16 , F02K1/17 , F02K3/10
CPC分类号： F02K1/17 , F02C9/16 , F02K1/16 , F02K3/10

109. 发明授权

US3082599A Coordinated control of afterburner fuel and exhaust nozzle area 失效
标题翻译：辅助燃料和排气喷嘴区域的协调控制
公开(公告)号：US3082599A
公开(公告)日：1963-03-26
申请号：US72302058
申请日：1958-03-21
申请人： UNITED AIRCRAFT CORP
发明人： WHITE JAMES N , TORELL BRUCE N
IPC分类号： F02C9/16 , F02K1/17
CPC分类号： F02C9/16 , F02K1/17

110. 发明授权

US3080709A Afterburner fuel and nozzle area control 失效
标题翻译：加力燃料和喷嘴区域控制
公开(公告)号：US3080709A
公开(公告)日：1963-03-12
申请号：US6509360
申请日：1960-10-26
申请人： GEN ELECTRIC
发明人： ALBERT RAND
IPC分类号： F02K1/16 , F02K1/17
CPC分类号： F02K1/16 , F02K1/17

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