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41. 发明授权

US2705864A Electronic control for gas turbine engines 失效
标题翻译：燃气轮机发动机的电子控制
公开(公告)号：US2705864A
公开(公告)日：1955-04-12
申请号：US23009751
申请日：1951-06-06
申请人： BENDIX AVIAT CORP
发明人： PETERS NORMAN K
IPC分类号： F02K1/17
CPC分类号： F02K1/17

42. 发明申请

US20190055901A1 METHOD AND SYSTEM FOR LIMITING POWER OF AN ENGINE 审中-公开
公开(公告)号：US20190055901A1
公开(公告)日：2019-02-21
申请号：US15681531
申请日：2017-08-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sylvain LAMARRE , Simon LOPEZ , Nicolas DES ROCHES-DIONNE , Michael CONCIATORI
IPC分类号： F02K1/76 , F02K1/17 , F02C9/44 , F02K1/66
CPC分类号： F02K1/76 , B64C11/305 , F02C9/44 , F02C9/58 , F02K1/17 , F02K1/66 , F05D2270/053
摘要： Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.

43. 发明申请

US20160138523A1 Optimal Thrust Control of an Aircraft Engine 审中-公开
标题翻译：飞机发动机的最佳推力控制
公开(公告)号：US20160138523A1
公开(公告)日：2016-05-19
申请号：US14921019
申请日：2015-10-23
申请人： United Technologies Corporation
发明人： Chaohong Cai , Timothy J. Crowley , Mark E. Lacour , David L. Ma
IPC分类号： F02K1/17 , F02C9/50
CPC分类号： F02K1/17 , F02C9/00 , F02C9/50 , F02C9/54 , F05D2270/20 , F05D2270/44 , F05D2270/71
摘要： A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions. The control system may further include a control module for determining a control command for the gas turbine engine. The control command may include, at least, a fuel flow command and an exhaust nozzle position command and the control command may be based on, at least, the exhaust nozzle position goal and an estimated thrust value. The control system may further include an actuator for controlling the gas turbine engine based on the control command.
摘要翻译：公开了一种燃气轮机的控制系统，燃气轮机的控制方法和燃气轮机。控制系统可以包括用于基于与飞行条件相关的排气喷嘴位置的喷嘴计划来确定排气喷嘴位置目标的喷嘴调度器。控制系统还可以包括用于确定燃气涡轮发动机的控制命令的控制模块。控制命令至少可以包括燃料流量指令和排气喷嘴位置指令，并且控制命令可以至少基于排气喷嘴位置目标和估计推力值。控制系统还可以包括用于基于控制命令控制燃气涡轮发动机的致动器。

44. 发明授权

US09222418B2 Fuel feed circuit with hydraulic actuator and fuel metering unit for an aeroengine 有权
标题翻译：具有用于航空发动机的液压致动器和燃料计量单元的燃料供给回路
公开(公告)号：US09222418B2
公开(公告)日：2015-12-29
申请号：US13500756
申请日：2010-09-30
申请人： Nicolas Alain Bader , Frederic Brettes , Bastien Dore , Laurent Gilbert Yves Hodinot
发明人： Nicolas Alain Bader , Frederic Brettes , Bastien Dore , Laurent Gilbert Yves Hodinot
IPC分类号： F02C9/48 , F02C7/236 , F02C9/26 , F02K1/17
CPC分类号： F02C9/48 , F02C7/236 , F02C9/263 , F02K1/17
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.
摘要翻译：一种用于航空发动机的燃料供给电路，该电路包括包括第一和第二容积式泵的高压泵送系统，液压致动器和燃料计量单元。作为致动器的滑动位置的函数，致动器的进料孔可以连接到连接到第二泵的出口的高压输送孔，或连接到低压输送孔压力进料管线。燃料计量单元包括贯穿部分，这些通过部分中的一个连接到高压泵送系统的出口，另一个通过部分连接到高压泵送系统的出口，并通向高压引燃器液压执行器的腔室。

45. 发明授权

US09206746B2 Method of controlling speed transients in a turbine engine 有权
标题翻译：控制涡轮发动机速度瞬变的方法
公开(公告)号：US09206746B2
公开(公告)日：2015-12-08
申请号：US13540144
申请日：2012-07-02
申请人： Cedrik Djelassi
发明人： Cedrik Djelassi
IPC分类号： F02C9/28 , F02C9/32 , F02K1/17 , F02C9/26
CPC分类号： F02C9/28 , F02C9/26 , F02C9/32 , F02K1/17 , F05D2270/04 , F05D2270/042 , F05D2270/101 , F05D2270/304
摘要： A method of controlling an engine in which a fuel flow setpoint is determined is provided. The method includes implementing a steady speed regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a setpoint parameter that depends on the position of a control lever and an operating parameter of the engine; detecting an intended speed transient; and implementing a speed transient regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a speed of the engine and a speed setpoint varying over time with the speed trajectory as generated in predetermined manner, if a speed transient is detected.
摘要翻译：提供一种控制其中确定燃料流量设定点的发动机的方法。该方法包括实现稳定的速度调节回路，其中燃料流量设定点被确定为取决于控制杆的位置和发动机的操作参数的设定点参数之间的差的函数; 检测预期的速度瞬变; 并且实施速度瞬态调节回路，其中燃料流量设定点被确定为发动机的速度与随时间变化的速度设定点之间的差异与以预定方式产生的速度轨迹的差的函数，如果速度检测到瞬态。

46. 发明申请

US20120174559A1 SYSTEM AND METHOD FOR CONTROLLING A GAS TURBINE ENGINE AFTERBURNER 审中-公开
标题翻译：用于控制燃气轮机后的发动机的系统和方法
公开(公告)号：US20120174559A1
公开(公告)日：2012-07-12
申请号：US12986493
申请日：2011-01-07
申请人： Richard Ling , Karl Keppler , Kevin Shepherd , Mark Lee Denton
发明人： Richard Ling , Karl Keppler , Kevin Shepherd , Mark Lee Denton
IPC分类号： F02K3/10
CPC分类号： F02K3/10 , F02C9/16 , F02C9/26 , F02C9/48 , F02K1/16 , F02K1/17
摘要： Methods and apparatus are provided for operating a gas turbine engine. In a first operational mode, the gas turbine engine generates thrust using the propulsion turbine and not the afterburner when it is commanded to generate a thrust between at least a first thrust magnitude and a second thrust magnitude, and generates thrust using the propulsion turbine and the afterburner when it is commanded to generate thrust greater than the second thrust magnitude. In a second operational mode, the gas turbine engine generates thrust using the propulsion turbine and the afterburner when it is commanded to generate a thrust greater than the first thrust magnitude. The steady state thrust-versus-throttle position response has a substantially constant linear slope that is set to be two times the similar slope of the first operational mode. Thrust transients of the propulsion turbine and the afterburner are substantially synchronizing when the gas turbine engine is operating in the second mode and generating thrust greater than first thrust magnitude.
摘要翻译：提供了用于操作燃气涡轮发动机的方法和装置。在第一操作模式中，当被命令在至少第一推力大小和第二推力大小之间产生推力时，燃气涡轮发动机使用推进涡轮而不是后燃器产生推力，并使用推进涡轮和当燃烧器被命令产生大于第二推力大小的推力时。在第二操作模式中，当被命令产生大于第一推力大小的推力时，燃气涡轮发动机使用推进涡轮和加力燃烧器产生推力。稳态推力对节气门位置响应具有基本恒定的线性斜率，其被设置为第一操作模式的相似斜率的两倍。当燃气涡轮发动机在第二模式下操作并且产生大于第一推力幅度的推力时，推进涡轮机和加力燃烧器的推力瞬变基本上同步。

47. 发明申请

US20020050140A1 Device and process for economizing fuel supply in a fuel supply circuit 有权
标题翻译：节省燃料供应回路燃料供应的装置和方法
公开(公告)号：US20020050140A1
公开(公告)日：2002-05-02
申请号：US09983623
申请日：2001-10-25
申请人： SNECMA MOTEURS
发明人： Marie-Trinite Rose Blot-Carretero , Philippe Galozio , Jean-Marie Brocard , Claude Marcel Maillard
IPC分类号： F02C007/22
CPC分类号： F02C9/32 , F02C7/236 , F02C7/262 , F02K1/17 , F05D2270/092 , Y02T50/671
摘要： An aircraft engine fuel supply circuit includes a high pressure pump for supplying the engine fuel injectors and supplying a plurality of servovalves for operating various auxiliary mechanisms. In an in-flight re-ignition configuration, with the rotational speed of the engine drops below a threshold value, a fuel economizer valve receives a command to close, thereby shutting off the supply of high pressure fuel to the servovalves. Consequently, the dimensions of the high pressure pump and other associated components in the circuit, especially heat exchangers, may be reduced.
摘要翻译：飞机发动机燃料供给回路包括用于供给发动机燃料喷射器的高压泵，并且供给用于操作各种辅助机构的多个伺服阀。在飞行中重启配置中，随着发动机的转速下降到阈值以下，燃油节能器阀接收关闭的命令，从而切断向伺服阀供应高压燃料。因此，可以减小电路中的高压泵和其它相关部件的尺寸，特别是热交换器。

48. 发明授权

US5133182A Control of low compressor vanes and fuel for a gas turbine engine 失效
标题翻译：控制低压缩机叶片和用于燃气涡轮发动机的燃料
公开(公告)号：US5133182A
公开(公告)日：1992-07-28
申请号：US448391
申请日：1989-12-11
申请人： Juan A. Marcos
发明人： Juan A. Marcos
IPC分类号： F02C9/28 , F02C9/54 , F02K1/16 , F02K1/17
CPC分类号： F02C9/28 , F02C9/54 , F02K1/16 , F02K1/17 , F05D2270/051 , F05D2270/71
摘要： Time responsiveness to thrust demands for a fan jet engine of the type that includes twin spools and a variable inlet at the fan is enhanced by regulating air flow through the variable inlet while holding low pressure compressor speed constant. The thrust change is targeted as a function of power lever position which generates a low pressure compressor parameter as a function of engine and aircraft operating variables. This parameter is then utilized to control both the inlet variable vanes and fuel flow to 1) attain the targeted value and 2) return the engine to its steady state operating line after a given time interval.
摘要翻译：通过在保持低压压缩机速度恒定的同时调节通过可变入口的空气流量来增强对包括双线轴和风扇可变入口的类型的风扇喷气发动机的推力需求的时间响应性。推力变化是作为功率杆位置的函数，其产生作为发动机和飞行器操作变量的函数的低压压缩机参数。然后利用该参数来控制入口可变叶片和燃料流量，以达到目标值; 2）在给定的时间间隔后将发动机返回到稳态工作线。

49. 发明授权

US4467600A System for controlling the thrust nozzle adjustment of dual cycle gas turbine jet propulsion engines 失效
标题翻译：用于控制双循环燃气轮机喷气推进发动机的推力喷嘴调节系统
公开(公告)号：US4467600A
公开(公告)日：1984-08-28
申请号：US496336
申请日：1983-05-23
申请人： Jurgen Peikert
发明人： Jurgen Peikert
IPC分类号： F02B75/02 , F02C9/34 , F02K1/17 , F02K1/18
CPC分类号： F02K1/17 , F02C9/34 , F02B2075/025 , Y02T50/677
摘要： The thrust nozzle opening angle of two cycle gas turbine jet engines is controlled in a system which comprises a low pressure compressor driven by a low pressure turbine. A first compressor is arranged radially inward for a first flow cycle or circuit and a second compressor is arranged radially outward for a second flow cycle or circuit. A high pressure compressor is driven by a high pressure turbine. A combustion chamber is situated upstream of the high pressure turbine. An afterburner is supplied with the turbine gases from the first, hot flow cycle and with compressed air from the second, relatively cool flow cycle or circuit. The system may have multiple shafts. The control is effected with reference to the instantaneous pressure relationship (.pi.NVZ) between the static pressure (p.sub.sD) downstream of the radially outer compressor (1a) of the second flow cycle (k2) and the static pressure (p.sub.sE) of the air flowing into the propulsion system. This ratio constitutes a variable rated control value (.pi..sub.NVZ-Soll) and is calculated as a function of the reduced rpm (N.sub.r) of the low pressure compressor (1). This type of control guarantees during a steady state operation particularly a minimal fuel consumption in the subsonic region and a maximum thrust in the supersonic region. This type of control further assures during a nonsteady type of operating, particularly the stability between the two aerodynamic limits, compressor surges (G1.sub.B or G1.sub.H) on the one hand and afterburner quenching (G2.sub.B or G2.sub.H) on the other hand.
摘要翻译：在包括由低压涡轮机驱动的低压压缩机的系统中控制两循环燃气轮机喷气发动机的推力喷嘴开度。第一压缩机径向向内布置用于第一流动循环或回路，并且第二压缩机径向向外布置用于第二流动循环或回路。高压压缩机由高压汽轮机驱动。燃烧室位于高压涡轮机的上游。向第一，热流循环的涡轮机气体和来自第二相对较冷的流动循环或回路的压缩空气供给加力燃烧器。该系统可以具有多个轴。参考在第二流动循环（k2）的径向外部压缩机（1a）下游的静态压力（psD）和流动的空气的静态压力（psE）之间的瞬时压力关系（pi NVZ）进行控制进入推进系统。该比率构成可变额定控制值（pi NVZ-Sol1），并且被计算为低压压缩机（1）的减速rpm（Nr）的函数。这种类型的控制在稳态操作期间保证特别是亚音速区域中的最小燃料消耗和超音速区域中的最大推力。这种类型的控制进一步确保在不稳定的操作类型，特别是两个空气动力学极限之间的稳定性，一方面是压缩机浪涌（G1B或G1H），另一方面是后燃烧器淬火（G2B或G2H）。

50. 发明授权

US3528248A Gas turbine engine 失效
公开(公告)号：US3528248A
公开(公告)日：1970-09-15
申请号：US3528248D
申请日：1968-07-01
申请人： ROLLS ROYCE
发明人： CROSS WALTER GEORGE
IPC分类号： B41J15/06 , F02K1/16 , F02K1/17 , F02K1/18 , F02K3/10
CPC分类号： F02K1/16 , B41J15/06 , F02K1/17

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