公开(公告)号：US11879384B2

公开(公告)日：2024-01-23

申请号：US18107758

申请日：2023-02-09

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Sean Durand

IPC分类号： F02C9/26 ,  F02C7/236 ,  F02C9/28 ,  F02C3/06 ,  F02C7/262

CPC分类号： F02C9/26 ,  F02C3/06 ,  F02C7/236 ,  F02C7/262 ,  F02C9/28

摘要： Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine.

公开(公告)号：US20230184171A1

公开(公告)日：2023-06-15

申请号：US17988504

申请日：2022-11-16

申请人： ROLLS-ROYCE plc

发明人： Gareth E. MOORE ,  Paul R. DAVIES ,  Stephen M. HUSBAND ,  David R. TRAINER ,  David P. SCOTHERN ,  Luke GEORGE ,  Douglas M M. HERBERT

IPC分类号： F02C7/262

CPC分类号： F02C7/262 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/85 ,  F05D2270/092 ,  F05D2270/093

摘要： Multi-engine aircraft power and propulsion systems and methods of restarting an engine of a multi-engine aircraft during fight are provided. One such method comprises: determining a condition to the effect that a flame in the combustion equipment of the second gas turbine engine has been extinguished; responsive to the determination, supplying electrical power from the electrical energy storage system to one or more of the electric machines of the second gas turbine engine and operating said one or more electric machines as motors to limit a reduction in a speed of the one or more spools of the second gas turbine engine following extinguishment of the flame in its combustion equipment; and restarting the second gas turbine engine by relighting the combustion equipment of the second gas turbine engine.

公开(公告)号：US20180187604A1

公开(公告)日：2018-07-05

申请号：US15129240

申请日：2015-03-26

申请人： SAFRAN HELICOPTER ENGINES

发明人： Vincent POUMAREDE ,  Thomas KLONOWSKI ,  Fabien MERCIER-CALVAIRAC ,  Camel SERGHINE

IPC分类号： F02C7/275 ,  B64C27/12 ,  B64D35/02 ,  B64D35/08 ,  F02C3/107 ,  F02C3/10 ,  F02C7/262 ,  F02C9/42 ,  F02C7/32 ,  H02K7/20 ,  H02K7/18

CPC分类号： F02C7/275 ,  B64C27/12 ,  B64D35/02 ,  B64D35/08 ,  F02C3/10 ,  F02C3/107 ,  F02C7/262 ,  F02C7/32 ,  F02C7/36 ,  F02C9/42 ,  F05D2220/329 ,  F05D2220/76 ,  H02K7/1823 ,  H02K7/20 ,  Y02T50/671

摘要： An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.

公开(公告)号：US10012387B2

公开(公告)日：2018-07-03

申请号：US14946109

申请日：2015-11-19

申请人： General Electric Company

发明人： Nayan Vinodbhai Patel ,  Alfred Albert Mancini ,  Duane Douglas Thomsen

IPC分类号： F02C9/34 ,  F02C7/22 ,  F23R3/28 ,  F02C7/232 ,  F02C7/262 ,  F23K5/06 ,  F02C7/224

CPC分类号： F23R3/28 ,  F02C7/22 ,  F02C7/222 ,  F02C7/224 ,  F02C7/232 ,  F02C7/262 ,  F02C9/34 ,  F23K5/06 ,  Y02T50/671

摘要： In one aspect, a fuel supply system may include a fuel injector having a primary and a secondary pilot fuel nozzle in fluid communication with a primary and a secondary fuel circuit, respectively, and a main fuel nozzle in fluid communication with a main fuel circuit. The fuel injector may also define a by-pass fuel circuit connected between the primary circuit and the secondary circuit and/or the main circuit. The system may also include a primary fuel manifold configured to be fluidly connected to the primary pilot fuel nozzle via the primary fuel circuit. Moreover, the system may include a by-pass valve provided in operative association with the by-pass fuel circuit. The by-pass valve may be configured to be opened such that a portion of the fuel flowing through the primary circuit from the primary fuel manifold is directed to the secondary circuit and/or the main circuit.

公开(公告)号：US20180045122A1

公开(公告)日：2018-02-15

申请号：US15236605

申请日：2016-08-15

申请人： Hamilton Sundstrand Corporation

发明人： Leo J. Veilleux

IPC分类号： F02C9/28 ,  F02C7/262 ,  F01D21/00 ,  F02C7/22

CPC分类号： F02C9/28 ,  F01D21/003 ,  F02C7/22 ,  F02C7/236 ,  F02C7/262 ,  F05D2220/323 ,  F05D2260/80 ,  F05D2260/81 ,  F05D2260/83 ,  F05D2270/304 ,  F05D2270/54

摘要： According to an aspect, a ground-based health test of a fuel pump of a fuel control system of a gas turbine engine is initiated. A starter speed of the gas turbine engine is determined while the ground-based health test is in progress. Fuel flow is initiated from the fuel pump to an ignition system of the gas turbine engine with the starter speed set below a nominal ground-based engine starting speed. A parameter of the gas turbine engine is monitored to verify light-off. A health status of the fuel pump is determined based on the starter speed at which light-off is achieved.

公开(公告)号：US20170022907A1

公开(公告)日：2017-01-26

申请号：US15149256

申请日：2016-05-09

申请人： Rolls-Royce North American Technologies, Inc.

发明人： Christopher Argote ,  John K. Harvell ,  Arthur L. Rowe

IPC分类号： F02C9/56 ,  F02C7/262 ,  F02C9/28

CPC分类号： F02C9/56 ,  F01D21/04 ,  F02C7/262 ,  F02C9/28 ,  F05D2270/02 ,  F05D2270/3015 ,  F05D2270/303

摘要： A method for use in a turbine control system includes controlling fuel supply to a gas turbine engine at least in part using a fuel supply limit determined as a first function of a rotational speed of a shaft of the gas turbine engine. The method also includes obtaining a first value representative of a rotational speed of the shaft, and differentiating the first value within a processing unit. The processing unit determines an adjusted fuel supply limit as an adjusted function of the first value. The adjusted function is based on the first function and the differentiated first value. The method further includes controlling the fuel supply to the gas turbine engine at least in part using the adjusted fuel supply limit.

摘要翻译： 一种用于涡轮机控制系统的方法包括至少部分地使用被确定为燃气涡轮发动机的轴的转速的第一函数的燃料供给极限来控制对燃气涡轮发动机的燃料供给。 该方法还包括获得代表轴的转速的第一值，并且将第一值区分在处理单元内。 处理单元将调整后的燃料供给极限确定为第一值的调整函数。 调整后的功能基于第一个功能和差分的第一个值。 该方法还包括至少部分地使用调节的燃料供应限制来控制燃气涡轮发动机的燃料供应。

公开(公告)号：US09488109B2

公开(公告)日：2016-11-08

申请号：US14877409

申请日：2015-10-07

申请人： Bell Helicopter Textron Inc.

发明人： Chandler Sowden

IPC分类号： H02J7/14 ,  H02J7/00 ,  F02C7/266 ,  H02J1/00 ,  F02N11/08 ,  F02C7/26 ,  F02C7/262 ,  H02P9/08 ,  F02C7/275

CPC分类号： F02C7/266 ,  F02C7/26 ,  F02C7/262 ,  F02C7/275 ,  F02N11/0866 ,  F02N11/087 ,  F02N2011/0877 ,  F05D2220/329 ,  F05D2270/52 ,  H02J1/00 ,  H02P9/08 ,  Y10T307/653

摘要： A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold.

公开(公告)号：US20160290239A1

公开(公告)日：2016-10-06

申请号：US15083752

申请日：2016-03-29

申请人： United Technologies Corporation

发明人： Ashok K. Jain ,  Michael Winter

IPC分类号： F02C7/262 ,  F01D25/24 ,  F02K1/06 ,  F02C9/16

CPC分类号： F02C7/262 ,  F01D25/24 ,  F02C9/16 ,  F02K1/06 ,  F02K1/1207 ,  F02K1/15 ,  F02K3/075 ,  F05D2220/32 ,  F05D2260/85 ,  F05D2270/092

摘要： An example turbofan engine starting system includes a core nacelle housing a compressor and a turbine. The core nacelle is disposed within a fan nacelle. The fan nacelle includes a turbofan. A bypass flow path downstream from the turbofan is arranged between the two nacelles. A controller is programmed to manipulate the nozzle exit area to facilitate startup of the engine. In one example, manipulates the nozzle exit area using nozzles, in response to an engine shutdown condition. The nozzles open and close to adjust the nozzle exit area.

摘要翻译： 一个例子涡扇发动机起动系统包括一个容纳压缩机和涡轮的核心机舱。 核心机舱设置在风扇机舱内。 风扇机舱包括涡轮风扇。 在两个发动机舱之间设置有涡轮风扇下游的旁路流路。 控制器被编程为操纵喷嘴出口区域以便于启动发动机。 在一个示例中，响应于发动机关闭状态，使用喷嘴来操纵喷嘴出口区域。 喷嘴打开和关闭，以调整喷嘴出口区域。

公开(公告)号：US09267439B2

公开(公告)日：2016-02-23

申请号：US13418983

申请日：2012-03-13

申请人： Michael Corson ,  Kenneth W. Winston

发明人： Michael Corson ,  Kenneth W. Winston

IPC分类号： F02C7/26 ,  F02C9/26 ,  F02C7/32 ,  F02C7/268 ,  F02C7/262 ,  F02C9/28

CPC分类号： F02C7/26 ,  F02C7/262 ,  F02C7/268 ,  F02C7/32 ,  F02C9/26 ,  F02C9/28

摘要： A system for starting a gas turbine engine includes an engine controller and a fuel controller. The engine controller varies the engine speed between a minimum start speed and a maximum start speed until light-off of the engine occurs. The fuel controller operates a fuel command to vary fuel provided to a combustion chamber of the engine until light-off of the engine occurs.

摘要翻译： 用于启动燃气涡轮发动机的系统包括发动机控制器和燃料控制器。 发动机控制器在最小启动速度和最大启动速度之间改变发动机转速，直到发动机发光。 燃料控制器操作燃料命令以改变提供给发动机的燃烧室的燃料，直到发动机发光。

公开(公告)号：US20160040599A1

公开(公告)日：2016-02-11

申请号：US14887363

申请日：2015-10-20

申请人： HAMILTON SUNDSTRAND CORPORATION

发明人： DAIH-YEOU CHEN

IPC分类号： F02C7/262 ,  F23R3/14 ,  F23R3/00 ,  F02C7/228

CPC分类号： F02C7/262 ,  F02C7/228 ,  F02C7/266 ,  F05D2300/607 ,  F23R3/002 ,  F23R3/06 ,  F23R3/12 ,  F23R3/14 ,  F23R3/28 ,  F23R3/286 ,  F23R3/343 ,  F23R3/54 ,  Y02T50/671 ,  Y02T50/675

摘要： Combustion systems for a gas turbine engines are provided. The combustion system is configured to provide a fuel-air mist to achieve light-off during high altitude start (e.g., at altitudes greater than 45,000 ft.) without flame out. The combustion system may also be configured to provide additional air to the combustion chamber at high altitude to facilitate flame propagation and second stage burn.

摘要翻译： 提供燃气涡轮发动机的燃烧系统。 燃烧系统被配置为提供燃料空气雾以在高空起飞期间（例如，在高于45,000英尺高度的高度）处实现熄火而不熄火。 燃烧系统还可以被配置为在高海拔地区向燃烧室提供额外的空气以便于火焰传播和第二级燃烧。