公开(公告)号：EP4405578A1

公开(公告)日：2024-07-31

申请号：EP22789636.2

申请日：2022-09-15

申请人： SAFRAN AIRCRAFT ENGINES

发明人： EMPRIN, Yves ,  FERT, Jérémy Edmond

IPC分类号： F02C3/22 ,  F02C7/22 ,  F02C7/25 ,  F02C7/266 ,  G01N33/00

CPC分类号： F02C3/22 ,  F02C7/25 ,  F02C7/266

公开(公告)号：EP4382741A3

公开(公告)日：2024-07-17

申请号：EP23214454.3

申请日：2023-12-05

申请人： Hamilton Sundstrand Corporation

发明人： McBRIEN, Gary M. ,  DONAHUE, Thomas M.

IPC分类号： F02P17/00 ,  F02C7/266 ,  F02P15/00 ,  F02P3/00 ,  F02D41/20 ,  F02P3/08 ,  F02P3/09

CPC分类号： F02D2041/202720130101 ,  F02C7/266 ,  F02P17/00 ,  F02P15/003 ,  F02P3/00 ,  F02P3/096 ,  F02P3/083

摘要： In accordance with at least one aspect of this disclosure, a method can include controlling firing of an exciter of an engine with an electronic controller separate from the exciter as a function of at least one excitation command from the electronic controller and at least one feedback signal from the exciter operatively connected to the electronic controller.

公开(公告)号：EP2255081B1

公开(公告)日：2018-09-05

申请号：EP09710927.6

申请日：2009-02-12

申请人： Foret Plasma Labs, Llc

发明人： FORET, Todd

IPC分类号： F02C3/14 ,  F02C6/12 ,  F02C7/266 ,  F23R3/42 ,  H05H1/24 ,  H05H1/32

CPC分类号： F02K3/12 ,  B64G1/405 ,  B64G1/406 ,  F01D13/00 ,  F02C3/14 ,  F02C7/266 ,  F02K9/425 ,  F23R3/007 ,  F23R3/58 ,  F23R2900/00002 ,  F23R2900/00009 ,  G21D5/02 ,  H05H1/24 ,  H05H1/32 ,  H05H1/48 ,  H05H2001/4695 ,  Y02E50/12 ,  Y02T50/678

摘要： The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle creates a plasma that discharges through the hollow electrode nozzle.

公开(公告)号：EP3196444A1

公开(公告)日：2017-07-26

申请号：EP17152372.3

申请日：2017-01-20

申请人： Champion Aerospace LLC

发明人： KEMPINSKI, Steve J.

IPC分类号： F02C7/266 ,  F02P15/00 ,  F02P3/08

CPC分类号： F02C7/266 ,  F02P3/0807 ,  F02P15/003 ,  F05D2220/323 ,  F05D2270/52

摘要： A solid state spark device that operates as a two terminal spark gap in a CDI exciter of an aircraft ignition system. The device includes a triggering transformer, a triggering circuit, and a control circuit. The triggering circuit is electrically connected to a first coil of the transformer and includes circuit elements connected to supply current to the first coil upon charging of the triggering circuit up to a triggering voltage. This current through the first coil of the triggering transformer induces an output in a second coil of the transformer. The control circuit is electrically connected to the second coil and includes a switch controlled by the output from the second coil. The switch, when activated by the triggering circuit, discharges energy from the exciter into an igniter of the aircraft ignition system.

摘要翻译： 一种固态火花装置，在飞机点火系统的CDI激励器中作为两端火花间隙工作。 该装置包括一个触发变压器，一个触发电路和一个控制电路。 触发电路电连接到变压器的第一线圈并且包括电路元件，所述电路元件被连接以在触发电路充电到触发电压时向第一线圈供应电流。 通过触发变压器的第一线圈的电流在变压器的第二线圈中感应输出。 控制电路电连接到第二线圈并且包括由来自第二线圈的输出控制的开关。 该开关在被触发电路激活时将激励器的能量释放到飞机点火系统的点火器中。

公开(公告)号：EP2513561B1

公开(公告)日：2016-08-17

申请号：EP10805618.5

申请日：2010-12-03

申请人： SNECMA

发明人： BUNEL, Jacques, Marcel, Arthur ,  DE SOUSA, Mario, César ,  LEBLOND, Nicolas, Christian, Raymond ,  SEVI, Guillaume ,  SANDELIS, Denis, Jean, Maurice ,  PIEUSSERGUES, Christophe

IPC分类号： F23R3/00 ,  F23R3/50 ,  F23R3/60 ,  F02C7/266 ,  F02C7/20

CPC分类号： F23R3/50 ,  F02C7/266 ,  F23D2207/00 ,  F23R3/002 ,  F23R3/60

公开(公告)号：EP3016273A1

公开(公告)日：2016-05-04

申请号：EP15185708.3

申请日：2014-01-30

申请人： Bell Helicopter Textron Inc.

发明人： Sowden, Chandler

IPC分类号： H02P9/08 ,  F02N11/08 ,  F02C7/26 ,  F02C7/262 ,  H02J1/00

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： An apparatus comprises a series switching logic 202 configured to receive an input signal. When the series switching logic receives the input signal, the series switching logic transmits an output signal. The apparatus further comprises a relay control switch 204 configured to receive the output signal from the series switching logic and configured to activate a series-parallel relay 108. When the output signal from the series switching logic is received, the relay control switch activates the series- parallel relay that configures a first battery 104 and a second battery 106 between a series and parallel connection. The series switching logic is further configured to detect the presence of an external power source or an on-board generator, and the series switching logic is precluded from transmitting the output signal to the relay control switch when an external power source or on-board generator is detected.

摘要翻译： 一种装置包括被配置为接收输入信号的串联切换逻辑202。 当串联切换逻辑接收输入信号时，串联切换逻辑发送输出信号。 该装置还包括继电器控制开关204，其被配置为从串联开关逻辑接收输出信号，并且被配置为启动串联并联继电器108.当接收到来自串联开关逻辑的输出信号时，继电器控制开关激活串联 - 并联继电器，其在串联和并联连接之间配置第一电池104和第二电池106。 串联切换逻辑还被配置为检测外部电源或车载发电机的存在，并且当外部电源或板载发电机 被检测到。

公开(公告)号：EP2954260A1

公开(公告)日：2015-12-16

申请号：EP14706719.3

申请日：2014-02-05

申请人： Siemens Aktiengesellschaft

发明人： WILLIAMS, Steven ,  FOX, Timothy A. ,  SCHILP, Reinhard

IPC分类号： F23D14/22 ,  F23D14/24 ,  F23R3/34 ,  F23R3/36 ,  F23R3/38

CPC分类号： F23R3/343 ,  F02C7/266 ,  F23D3/22 ,  F23D11/38 ,  F23D11/42 ,  F23D14/22 ,  F23D14/24 ,  F23D2207/00 ,  F23R3/36 ,  F23R3/38

摘要： A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body.

公开(公告)号：EP1963640B1

公开(公告)日：2015-04-29

申请号：EP06835693.0

申请日：2006-12-12

申请人： Micro Turbine Technology B.V.

发明人： VAN BERKEL, Arij, Iza??k ,  WITTEVEEN, Gustaaf, Jan ,  AHOUT, Willibald, Mattheus, Petrus ,  DE GOEY, Laurentius Philippus Hendrika ,  BASTIAANS, Robert Johan Maria

IPC分类号： F02C3/16 ,  F02C7/266

CPC分类号： F02C7/266 ,  F02C3/165 ,  F05D2250/82 ,  Y02T50/67

公开(公告)号：EP2779422A1

公开(公告)日：2014-09-17

申请号：EP14153240.8

申请日：2014-01-30

申请人： Bell Helicopter Textron Inc.

发明人： Sowden, Chandler

IPC分类号： H02P9/08 ,  F02N11/08 ,  F02C7/26 ,  F02C7/262

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 (110) for starting an aircraft turbine engine (102) and method (400) thereof is provided, wherein the battery series start controller (110) connects two batteries (104, 106) in series when an aircraft engine starter (114) is engaged to provide a higher voltage to start the aircraft engine (102) and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller (110) reconnects the batteries (104, 106) in parallel when the electrical load drawn by the starting aircraft engine (102) decreases and the supplied voltage to the aircraft (100) rises to a predetermined threshold.

摘要翻译： 提供一种用于启动飞行器涡轮发动机（102）的系列电池启动控制器（110）及其方法（400），其中当飞行器发动机起动器（110）连接时，电池组起动控制器（110）串联连接两个电池（104,106） （114）被接合以提供更高的电压以启动飞机发动机（102）并向飞机发动机仪器和其它飞行器电气系统提供足够的操作电压，并且其中电池组起动控制器（110）重新连接电池 106）并联时，由起动飞机发动机（102）牵引的电力负载减小并且提供给飞行器（100）的电压上升到预定阈值。

公开(公告)号：EP2743588A1

公开(公告)日：2014-06-18

申请号：EP12196533.9

申请日：2012-12-11

申请人： Siemens Aktiengesellschaft

发明人： Dolmansley, Timothy

IPC分类号： F23R3/34 ,  F23D11/24 ,  F23D11/10

CPC分类号： F23R3/343 ,  F02C7/26 ,  F02C7/264 ,  F02C7/266 ,  F23D11/108 ,  F23D11/24 ,  F23D14/02 ,  F23D2900/00014 ,  F23Q9/00 ,  F23R3/12 ,  F23R3/286 ,  F23R3/36 ,  F23R2900/00015

摘要： The present invention relates to a combustion chamber for a gas turbine. The combustion chamber comprises a pilot burner device, a fuel injector (102) and an ignitor unit (103). The pilot burner device comprises a pilot body (100) with a pilot surface (101) which is facing an inner volume of the combustion chamber. The fuel injector (102) comprises a fuel outlet for injecting a fuel into the inner volume. The ignitor unit (103) is adapted for igniting the fuel inside the inner volume, wherein the ignitor unit (103) is arranged at the pilot surface (101) such that fuel which passes the ignitor unit (103) is ignitable. The pilot body (100) comprises a recess (501), wherein the fuel outlet is arranged within the recess (501).

摘要翻译： 燃气轮机的燃烧室技术领域本发明涉及燃气轮机的燃烧室。 燃烧室包括先导燃烧器装置，燃料喷射器（102）和点火器单元（103）。 该引燃器装置包括具有面向燃烧室的内部容积的引导表面（101）的引导主体（100）。 燃料喷射器（102）包括用于将燃料喷射到内部容积中的燃料出口。 点火器单元（103）适于点燃内部容积内的燃料，其中点火器单元（103）布置在导向表面（101）处，使得通过点火器单元（103）的燃料可点燃。 先导主体（100）包括凹部（501），其中燃料出口布置在凹部（501）内。