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61.发明申请METHOD AND A DEVICE FOR ADJUSTING A SETPOINT VALUE OF A PARAMETER THAT INFLUENCES THRUST FROM A GAS TURBINE ENGINE 有权用于调节来自气体涡轮发动机的参数的设定值的方法和装置公开(公告)号：US20150285159A1
公开(公告)日：2015-10-08
申请号：US14409663
申请日：2013-06-11
Applicant: SNECMA
Inventor： Hichem Belghagi , Sylvain Clermonte , Laurence Garin
CPC classification number: F02C9/44 , F02C9/28 , F05D2270/051 , F05D2270/3011 , F05D2270/303 , F05D2270/304 , F05D2270/312 , F05D2270/313 , F05D2270/708
Abstract: A method of adjusting a setpoint value of at least one parameter that has an influence on thrust of a gas turbine engine propelling an aircraft during a stage of flight of the aircraft, the method including: obtaining a current value of at least one operating variable of the engine; extracting from a pre-established table a decrement value for the at least one parameter associated with the current value of the at least one operating variable of the engine; and adjusting the setpoint value of the at least one parameter by applying thereto the decrement value extracted from the table.
Abstract translation: 一种调节至少一个参数的设定值的方法，所述至少一个参数对在飞机的飞行阶段期间推进飞机的燃气涡轮发动机的推力具有影响，所述方法包括：获得至少一个操作变量的当前值 引擎; 从预先建立的表中提取与所述发动机的至少一个操作变量的当前值相关联的所述至少一个参数的递减值; 以及通过向其应用从表中提取的递减值来调整至少一个参数的设定值。
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公开(公告)号：US4783957A
公开(公告)日：1988-11-15
申请号：US946455
申请日：1986-12-23
Applicant: James J. Harris
Inventor： James J. Harris
CPC classification number: F02C9/44 , F02C9/28 , F05D2270/02 , F05D2270/092
Abstract: In a fuel control system for turbine engines, it is beneficial to provide a minimum fuel signal which prevents the fuel demand of the turbine engine from being decreased below a lower limit which can cause flameout or extinction. The fuel control system of the present invention provides an electronic circuit that includes a portion which dynamically determines the minimum fuel demand of the turbine engine during operation. A circuit is provided to compare the power output of the turbine engine to a predetermined threshold magnitude. The no-load or low-load minimum fuel demand level is continually monitored until the power output of the turbine engine exceeds the predetermined threshold magnitude at which time the stored value of fuel demand is inhibited from being subsequently changed. During later operation of the turbine engine, the stored value of minimum fuel demand is provided to a most fuel bus to operate as a minimum limit of fuel demand for the turbine engine. A temperature compensation device adjusts the minimum fuel demand in response to temperature changes that can occur after the minimum fuel demand is stored.
Abstract translation: 在用于涡轮发动机的燃料控制系统中，有利的是提供一种最小的燃料信号，其防止涡轮发动机的燃料需求降低到可能导致熄火或熄灭的下限以下。 本发明的燃料控制系统提供一种电子电路，其包括在运行期间动态地确定涡轮发动机的最小燃料需求的部分。 提供电路以将涡轮发动机的功率输出与预定阈值幅度进行比较。 持续监控无负载或低负荷的最小燃料需求量，直到涡轮发动机的功率输出超过预定阈值幅值，此时禁止燃料需求的储存值随后改变。 在涡轮发动机的后续操作期间，将最低燃料需求的存储值提供给大多数燃料总线以作为涡轮发动机的燃料需求的最小限度。 温度补偿装置根据存储最低燃料需求之后可能发生的温度变化来调整最小燃料需求。
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公开(公告)号：US4551972A
公开(公告)日：1985-11-12
申请号：US664949
申请日：1984-10-26
Applicant: Leon D. Lewis
Inventor： Leon D. Lewis
IPC: F02C9/32 , F02C9/00 , F02C9/44 , F02D20060101 , F02C9/28
CPC classification number: F02C9/00 , Y02T50/671
Abstract: A limited authority system for controlling engine performance in accordance with energy or thrust requirements in response to engine parameters which is capable of operating in a number of control modes.
Abstract translation: PCT No.PCT / US80 / 01065 Sec。 371日期1982年3月4日 102（e）1982年3月4日PCT PCT 1980年8月21日PCT公布。 公开号WO82 / 00687 日期1982年3月4日。一种用于根据能够以多种控制模式操作的发动机参数来响应能量或推力要求来控制发动机性能的有限权限系统。
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公开(公告)号：US4468924A
公开(公告)日：1984-09-04
申请号：US422863
申请日：1982-09-24
Applicant: M. Samuel Moore
Inventor： M. Samuel Moore
CPC classification number: F02C9/44 , F02C9/28 , F05D2270/02
Abstract: Pushbutton controls are provided for the power management of a turbine powered aircraft; and these pushbuttons may be mounted on the aircraft pilot's control handwheel. The turbine engine has a maximum rated permissible rotational speed which initially increases with increasing air temperature and with increasing altitude or reduced pressure; and has an absolute maximum limitation, with this maximum permissible rotational speed decreasing at increasing temperatures starting at about 10 or 15 degrees below zero, centigrade; and these limitations are reduced when supplemental equipment such as de-icing equipment is turned on. In accordance with the present invention, a series of "maps", or rotational speed control characteristics reflecting the factors mentioned above, are provided, and the pushbutton controls select among these characteristics, with the "take-off" power button permitting the highest maximum speeds, etc. In addition, automatic timing to reduce the maximum power levels, such as "Take-Off" power or "Performance Climb" power, is provided, to avoid over-stressing the turbine engines. The system may include additional arrangements for limiting the maximum allowable rotational speed of the turbine engine to a speed below that indicated by any of the "maps", when certain pushbuttons such as the "Approach" pushbutton is actuated.
Abstract translation: 提供按钮控制，用于涡轮动力飞机的电源管理; 并且这些按钮可以安装在飞行员飞行员的控制手轮上。 涡轮发动机具有最大额定允许转速，其最初随着空气温度升高并且随着高度或降低的压力而增加; 并且具有绝对的最大限制，在最高允许转速下降时，起升温度在零下10度或15度以下; 并且当诸如除冰设备的补充设备被打开时，这些限制被减少。 根据本发明，提供了一系列反映上述因素的“地图”或转速控制特性，并且按钮控制在这些特性之中选择允许最大最大值的“起飞”电源按钮 速度等。此外，提供了降低最大功率水平的自动定时，例如“起飞”功率或“性能爬升”功率，以避免涡轮发动机的过度应力。 当诸如“接近”按钮的某些按钮被致动时，该系统可以包括用于将涡轮发动机的最大允许转速限制到低于任何“地图”所指示的速度的附加装置。
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公开(公告)号：US4397148A
公开(公告)日：1983-08-09
申请号：US165159
申请日：1980-07-02
Applicant: William W. Stockton , Walter D. Hutto, Jr.
Inventor： William W. Stockton , Walter D. Hutto, Jr.
Abstract: The engine includes a main engine fuel flow, an augmentation fuel flow, and a variable area exhaust nozzle. Primary speed control means is powered by first electrical power supply means. Fan speed is controlled by modulation of main engine fuel flow. Loss of electrical power to the primary speed control means during augmented operation results in a reversion from fan speed control to core engine speed control while simultaneously reducing the augmentation fuel flow toward a minimum level and closing the variable area exhaust nozzle. Backup speed control means is coupled to the primary speed control means for limiting fan overspeed in augmented operation during loss of electrical power to the primary speed control means. The backup speed control means is powered by second electrical power supply means which is independent of the first power supply means. For example, in one embodiment involving aircraft application, the first electrical power supply means comprises an engine-driven alternator and the second electrical power supply means comprises an aircraft positioned power supply. The primary and backup speed control means may be coupled to separate windings of a single torque motor.
Abstract translation: 发动机包括主发动机燃料流，增压燃料流和可变区排气喷嘴。 主速度控制装置由第一电力供应装置供电。 风扇转速由主机燃油流量调节控制。 在增加操作期间，对主速度控制装置的电力的损失导致从风扇速度控制向核心发动机转速控制的逆转，同时将增加的燃料流量降低到最小水平并且关闭可变区域排气喷嘴。 备用速度控制装置耦合到主速度控制装置，用于在对主速度控制装置的电力损失期间限制增大操作中的风扇超速。 备用速度控制装置由独立于第一电源装置的第二电源装置供电。 例如，在涉及飞机应用的一个实施例中，第一电力供应装置包括发动机驱动的交流发电机，第二电力供给装置包括飞机定位的电源。 主和后备速度控制装置可以耦合到单个扭矩电动机的分离绕组。
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Patent Agency Ranking
公开(公告)号：US4212161A
公开(公告)日：1980-07-15
申请号：US901899
申请日：1978-05-01
Applicant: David M. Newirth , Eugene W. Koenig
Inventor： David M. Newirth , Eugene W. Koenig
CPC classification number: F02C9/46 , F05D2200/13
Abstract: For a failure of a sensor utilized in the controls for a gas turbine engine, calculations from other parameters based on the thermodynamics of the cycle serve to simulate the value otherwise manifested by the failed sensor. In this instance, the ratio of burner pressure to engine inlet total pressure generated as a function of corrected rotor speed multiplied by a calculated engine total pressure from aircraft altitude and Mach No. simulates burner pressure utilized in the main fuel control for continuing automatic engine operation.
Abstract translation: 对于在燃气轮机发动机的控制中使用的传感器的故障，基于循环的热力学的其他参数的计算用于模拟由故障传感器表现的值。 在这种情况下，燃烧器压力与发动机入口总压力的比值作为校正的转子速度乘以来自飞机高度和马赫数的计算的发动机总压力产生的函数，模拟用于继续自动发动机运行的主燃料控制中使用的燃烧器压力 。
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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
Applicant: Peter D. Toot
Inventor： Peter D. Toot
CPC classification number: F02K1/48
Abstract: 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.
Abstract translation: 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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公开(公告)号：US3932058A
公开(公告)日：1976-01-13
申请号：US477532
申请日：1974-06-07
Applicant: Kermit I. Harner , Roy W. Schneider
Inventor： Kermit I. Harner , Roy W. Schneider
IPC: F02C9/28 , B64D31/06 , F02C9/44 , F02C9/54 , F02C9/58 , F02K1/66 , F02K3/06 , B63H3/10 , B64C11/44 , F02C9/02
Abstract: A control for a variable pitch fan propulsor driven by a turbine type of power plant which fan is mounted in an engine bypass duct having a variable exit nozzle. The control serves to coordinate the control of fuel flow to the engine, the area of the fan exit nozzle, and the pitch of the fan blades by biasing the power lever position signal with Flight Mach No. An additional feature is the inclusion of fan surge control derived from signals of flight Mach No. and corrected free turbine speed.
Abstract translation: 用于由涡轮机类型的发电厂驱动的可变桨距风扇推进器的控制器，风扇安装在具有可变出口喷嘴的发动机旁路管道中。 该控制用于通过用飞行马赫数偏置动力杆位置信号来协调对发动机的燃料流量，风扇出口喷嘴的面积和风扇叶片的间距的控制。另外的特征是包括风扇浪涌 控制来自飞行马赫数的信号和校正的免费涡轮转速。
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公开(公告)号：US3874170A
公开(公告)日：1975-04-01
申请号：US34863373
申请日：1973-04-06
Applicant: LUCAS AEROSPACE LTD
Inventor： LEWIS GEOFFREY ARTHUR
CPC classification number: F02C7/232
Abstract: A fuel control apparatus for a gas turbine engine reheat system has a variable metering arrangement responsive to engine operating parameters to control fuel flow to the reheat burners, and a distributor valve arrangement between the metering arrangement and the burners. The distributor arrangement is operable in one mode to connect the metering arrangement to the burners, and in another mode to shut off fuel from the metering arrangement and to connect the burners to a low pressure drain.
Abstract translation: 用于燃气涡轮发动机再热系统的燃料控制装置具有响应于发动机操作参数的可变计量装置，以控制到再热燃烧器的燃料流量，以及计量装置和燃烧器之间的分配器阀装置。 分配器装置可以在一种模式中操作以将计量装置连接到燃烧器，并且在另一模式中可以切断来自计量装置的燃料并将燃烧器连接到低压排放管。
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公开(公告)号：US3764785A
公开(公告)日：1973-10-09
申请号：US3764785D
申请日：1970-10-29
Applicant: UNITED AIRCRAFT CORP
Inventor： HARNER K , SCHNEIDER R
Abstract: 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.
Abstract translation: 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。
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