公开(公告)号：US06978597B2

公开(公告)日：2005-12-27

申请号：US10482406

申请日：2003-03-20

申请人： Terence McKelvey ,  Eishi Marui ,  Masahiro Miyamoto ,  Tadashi Kataoka ,  Tai Furuya

发明人： Terence McKelvey ,  Eishi Marui ,  Masahiro Miyamoto ,  Tadashi Kataoka ,  Tai Furuya

IPC分类号： F02C7/262 ,  F02C9/28 ,  F02C9/46 ,  F23N5/24 ,  F02C9/00 ,  F02G3/00

CPC分类号： F02C9/28 ,  F02C7/262 ,  F02C9/46 ,  F05D2270/092 ,  F05D2270/3013

摘要： A gas turbine apparatus is provided wherein a turbine is driven or rotated by burning a mixture of a fuel and compressed air and supplying a combustion gas generated by the combustion. A flameout determination unit is provided in the apparatus which is adapted to calculate the air/fuel ratio in the air/fuel mixture, correct the calculated air/fuel ratio to calculate a corrected air/fuel ratio which is substantially constant, compare the calculated corrected air/fuel ratio with a predetermined reference air/fuel ratio, and generate a signal indicative of occurrence of a flameout when the corrected air/fuel ratio is smaller than the reference air/fuel ratio. The corrected air/fuel ratio is calculated by calculating a deviation of a compressor discharge pressure of the compressed air from an air compressor, from a predetermined reference pressure, multiplying the pressure deviation by a predetermined constant, and adding the pressure deviation multiplied by the predetermined constant to the calculated air/fuel ratio. In this way, the corrected air/fuel ratio can be maintained substantially constant even if a load increases in steps.

摘要翻译： 提供了一种燃气轮机装置，其中通过燃烧燃料和压缩空气的混合物并提供由燃烧产生的燃烧气体来驱动或旋转涡轮机。 在该装置中设置有熄火确定单元，其适于计算空气/燃料混合物中的空气/燃料比，校正计算出的空气/燃料比以计算基本上恒定的校正空气/燃料比，将计算出的校正的 空燃比，并且当校正后的空气/燃料比小于参考空气/燃料比时，生成表示发生熄火的信号。 通过计算来自空气压缩机的压缩空气的压缩机排出压力与预定的基准压力的偏差，将压力偏差乘以预定的常数，并将加上预定的压力偏差 恒定到计算出的空气/燃料比。 以这种方式，即使负荷逐步增加，校正的空气/燃料比也可以保持基本恒定。

公开(公告)号：US5617717A

公开(公告)日：1997-04-08

申请号：US332053

申请日：1994-10-31

申请人： Joseph G. Asquith ,  William P. Peschel ,  Jacob L. Sperling

发明人： Joseph G. Asquith ,  William P. Peschel ,  Jacob L. Sperling

IPC分类号： F02C7/262 ,  F02C7/266 ,  F23R3/18 ,  H05H1/46 ,  F02K3/10

CPC分类号： F02C7/262 ,  F02C7/264 ,  F02C7/266 ,  F23R3/18 ,  H05H1/46 ,  F05D2270/092 ,  F05D2270/101

摘要： A flame stabilizing system for an augmentor, or a ramjet engine, which utilizes continuously operating microwave powered plasma plume igniters to generate a stable source of ignition for the flowing combustible mixture within the augmentor combustion chamber.

摘要翻译： 一种用于增压器或冲压式喷气发动机的火焰稳定系统，其利用连续操作的微波动力等离子体羽流点火器来为增压器燃烧室内的流动可燃混合物产生稳定的点火源。

公开(公告)号：US5235802A

公开(公告)日：1993-08-17

申请号：US894871

申请日：1992-06-08

申请人： B. Melvin Barnum ,  Russell C. Bell

发明人： B. Melvin Barnum ,  Russell C. Bell

IPC分类号： F02C9/28 ,  F23N5/00

CPC分类号： F23N5/00 ,  F02C9/28 ,  F05D2270/092

摘要： A dual rotor gas generator of a gas turbine generator is fired with fuel delivery based on a fuel demand signal. Actual air flow is determined by sensing the low pressure rotor speed. A ratio of the fuel demand and actual air flow is calculated. Actual fuel flow is not used. Loss of flame is detected based on a fuel/air ratio as compared to a preselected value.

摘要翻译： 燃料涡轮发电机的双转子气体发生器基于燃料需求信号被燃烧输送。 通过感测低压转子速度确定实际气流。 计算燃料需求与实际气流的比率。 不使用实际燃油流量。 与预选值相比，基于燃料/空气比来检测火焰的损失。

公开(公告)号：US5170621A

公开(公告)日：1992-12-15

申请号：US687145

申请日：1991-04-18

申请人： B. Melvin Barnum ,  Russell C. Bell

发明人： B. Melvin Barnum ,  Russell C. Bell

IPC分类号： F02C9/00 ,  F02C9/28 ,  F23N5/00

CPC分类号： F02C9/28 ,  F23N5/00 ,  F05D2270/092

摘要： A dual rotor gas generator of a gas turbine generator is fired with fuel delivery based on a fuel demand signal. Actual air flow is determined by sensing the low pressure rotor speed. A ratio of the fuel demand and actual air flow is calculated. Actual fuel flow is not used. Loss of flame is detected based on a fuel/air ratio as compared to a preselected value.

公开(公告)号：US3080708A

公开(公告)日：1963-03-12

申请号：US5590260

申请日：1960-09-14

申请人： PHILLIPS PETROLEUM CO

发明人： CARR DONALD E

IPC分类号： F02C9/28

CPC分类号： F02C9/28 ,  F05D2270/02 ,  F05D2270/04 ,  F05D2270/092 ,  Y02T50/671

公开(公告)号：US11719155B2

公开(公告)日：2023-08-08

申请号：US17835518

申请日：2022-06-08

申请人： TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION

发明人： Yasunori Iwai ,  Shinju Suzuki ,  Masao Itoh ,  Yuichi Morisawa ,  Yoshihisa Kobayashi

IPC分类号： F02C3/34 ,  F02C9/50 ,  F23R3/26 ,  F02C1/08 ,  F23N1/02 ,  F02C1/00

CPC分类号： F02C3/34 ,  F02C1/08 ,  F02C9/50 ,  F23R3/26 ,  F02C1/005 ,  F05D2260/85 ,  F05D2270/092 ,  F23N1/02 ,  F23N2227/02 ,  F23N2241/20

摘要： In a method for operating a combustor of an embodiment, before ignition in the combustor, a mixed gas containing oxygen is circulated through the combustor as a circulating gas. Then, in an operating time from the time of ignition in the combustor to the time of a rated load of a turbine, from the time of ignition until reaching stable combustion conditions allowing stable combustion, a combustion gas in which a controller controls a flow rate of a fuel supplied from a fuel supply part and a flow rate of an oxidant supplied from an oxidant supply part to maintain the same oxygen concentration as an oxygen concentration in the mixed gas is circulated as the circulating gas.

公开(公告)号：US20170114723A1

公开(公告)日：2017-04-27

申请号：US15301939

申请日：2015-04-03

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN HELICOPTER ENGINES ,  SAFRAN CERAMICS

发明人： Patrick Marconi ,  Romain Thiriet ,  Camel Serghine ,  Francois Danguy ,  Philippe Barrat ,  Jean-Louis Besse ,  Pascal Guillemet ,  Guillaume Demezon ,  Jean-Michel Sannino ,  Nicolas Marucheau De Chanaud

IPC分类号： F02C7/36 ,  F02C3/10 ,  F02C7/266

CPC分类号： F02C7/36 ,  F02C3/10 ,  F02C7/266 ,  F02C7/277 ,  F05D2220/329 ,  F05D2260/40 ,  F05D2270/09 ,  F05D2270/092 ,  Y02T50/671

摘要： The invention relates to a device for assisting a propulsion system of a single-engine helicopter, comprising an engine connected to a power transmission gearbox (15) suitable for rotating a rotor (88) of the helicopter, characterised in that it comprises: a turbine (18) for driving in rotation an output shaft (34) that is mechanically connected to said power transmission gearbox (15); and controlled means (16) for supplying said drive turbine (18) with pressurised fluid in order to allow said turbine (18) to transform the power from said pressurised fluid into mechanical power for rotating said output shaft (34).

公开(公告)号：US20170016401A1

公开(公告)日：2017-01-19

申请号：US15186805

申请日：2016-06-20

申请人： ROLLS-ROYCE plc

发明人： Mark Thomas STOCKWELL

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

CPC分类号： F02C9/28 ,  F02C7/22 ,  F02C7/262 ,  F05D2220/32 ,  F05D2260/85 ,  F05D2270/092 ,  F05D2270/304

摘要： A method of controlling fuel flow for combustion in a gas turbine engine comprising a low pressure spool, a high pressure spool and a fuel metering valve is disclosed. The method comprises scheduling the fuel metering valve in dependence upon the speed of the high pressure spool.

摘要翻译： 公开了一种控制燃气涡轮发动机燃料流量的方法，其包括低压阀芯，高压阀芯和燃料计量阀。 该方法包括根据高压阀芯的速度调度燃料计量阀。

公开(公告)号：US20160195025A1

公开(公告)日：2016-07-07

申请号：US14911318

申请日：2014-08-26

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Andre M. Ajami ,  Jason Eric Turner ,  Kenneth W. Winston

IPC分类号： F02C9/26 ,  F02C9/28

CPC分类号： F02C9/263 ,  F02C9/28 ,  F05D2260/80 ,  F05D2270/0831 ,  F05D2270/09 ,  F05D2270/092 ,  F05D2270/303 ,  F05D2270/309 ,  G01K3/10 ,  G01K13/02 ,  G01K2013/024

摘要： A method includes receiving an indication of exhaust gas temperature (EGT) for a gas turbine engine, and determining, by at least one processor, based on the received indication of the EGT, a representation of a second derivative with respect to time of the EGT. The method further includes comparing the representation of the second derivative of the EGT to a threshold value, and determining, based on the comparing, an engine flameout condition of the gas turbine engine. In some embodiments, the at least one processor can determine a representation of a first derivative with respect to time of the EGT. The representation of the first derivative of the EGT can be compared to a threshold value, determined based on the received indication of the EGT, to determine the engine flameout condition.

摘要翻译： 一种方法包括接收燃气涡轮发动机的排气温度（EGT）的指示，以及由至少一个处理器基于接收到的EGT指示确定相对于EGT的时间的二阶导数的表示 。 该方法还包括将EGT的二阶导数的表示与阈值进行比较，并且基于比较来确定燃气涡轮发动机的发动机熄火状态。 在一些实施例中，至少一个处理器可以确定关于EGT的时间的一阶导数的表示。 可以将EGT的一阶导数的表示与基于EGT的接收指示确定的阈值进行比较，以确定发动机熄火状况。

公开(公告)号：US20150148994A1

公开(公告)日：2015-05-28

申请号：US14547384

申请日：2014-11-19

申请人： MITSUBISHI AIRCRAFT CORPORATION

发明人： Yoshihiro NAGASHIMA

IPC分类号： B64D31/06

CPC分类号： B64D31/06 ,  B64D31/04 ,  B64D31/14 ,  F02C7/262 ,  F02C9/28 ,  F05D2270/092 ,  F05D2270/312 ,  G05D1/042

摘要： The invention deals with the restriction on the mode change of an engine due to latching in the case of restarting the engine that has stopped in flight. A FADEC that controls an engine of an aircraft in accordance with a mode, includes a latch operating section that latches the mode, and an in-parking/in-flight determining section that determines whether the aircraft is on the ground or flying off the ground. The latch operating section operates when the in-parking/in-flight determining section determines the aircraft is on the ground, and does not operate when the in-parking/in-flight determining section determines that the aircraft is in fight.

摘要翻译： 本发明涉及在重新启动在飞行中停止的发动机的情况下由于锁定引起的发动机的模式变化的限制。 根据模式控制飞行器的发动机的FADEC包括锁定模式的闩锁操作部分和用于确定飞机是在地面上还是从地面飞行的飞行中的停车/飞行中确定部分 。 当停车/飞行中确定部分确定飞机在地面时，闩锁操作部分操作，并且在停车/飞行中确定部分确定飞机正在进行战斗时不操作。