-
公开(公告)号：US20190186286A1
公开(公告)日：2019-06-20
申请号：US15848441
申请日：2017-12-20
申请人： Plasma Igniter, LLC
发明人： Andrew D. Lowery , James E. Smith
CPC分类号： F01D21/003 , F02C9/28 , F02M27/06 , F02P23/045 , F05D2260/80 , F05D2270/092 , H05H1/2406 , H05H1/46 , H05H2001/2412 , H05H2001/4645
摘要： Example implementations relate to jet engines that include resonator-based diagnostics. An example implementation includes a jet engine. The jet engine includes a combustion chamber configured to house a combustion event of a fuel mixture. The jet engine also includes a resonator having a characteristic impedance and a resonant wavelength. The resonator includes a first conductor and a second conductor separated from one another by an interstitial space that is exposed to an environment of the combustion chamber. Further, the jet engine includes a controller communicatively coupled to the resonator and configured to perform operations. The operations include determining a characteristic of the resonator selected from the group consisting of the characteristic impedance and the resonant wavelength. The operations also include, based on the determined characteristic, determining a parameter of the combustion chamber.
-
公开(公告)号：US20180328817A1
公开(公告)日：2018-11-15
申请号：US15592553
申请日：2017-05-11
CPC分类号： G01M15/14 , F02C9/28 , F05D2270/092 , F05D2270/81 , F23N5/16 , F23N5/242 , F23N2025/04 , F23N2041/20 , F23R2900/00013 , G01L9/0008
摘要： A system for controlling an operation of a combustor in a gas turbine that includes: an acoustic sensor configured to periodically measure a pressure of the combustor and generate a raw data stream having the pressure data points resulting from the periodic measurements; and a blowout detection unit configured to receive the raw data stream from the acoustic sensor. The blowout detection unit may include a processor and a machine-readable storage medium on which is stored instructions that cause the processor to execute a procedure related to a detection of a blowout precursor. The procedure may include an ensemble approach in which the detection of the blowout precursor depends upon a outcomes generated respectively by separate detection analytics.
-
公开(公告)号：US10081438B2
公开(公告)日：2018-09-25
申请号：US15288612
申请日：2016-10-07
发明人： Yoshihiro Nagashima
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.
-
24.发明申请公开(公告)号：US20180216820A1
公开(公告)日：2018-08-02
申请号：US15747490
申请日：2016-07-28
发明人： Ghenadie Bulat , Timothy Dolmansley
CPC分类号： F23N5/242 , F02C9/28 , F05D2220/32 , F05D2240/35 , F05D2260/80 , F05D2270/092 , F05D2270/14 , F05D2270/3032 , F05D2270/44 , F23N2023/06 , F23N2023/10 , F23N2025/04 , F23N2025/16 , F23N2041/20 , F23R3/28
摘要： A method for predicting a combustion error type of a combustion flame. A raw signal of an error parameter of the combustion flame within a predefined time span is measured, the error parameter is adapted for determining the combustion error type. A predefined frequency range from the raw signal is extracted using a by-pass filter, where the raw signal is decomposed. The number of peaks of the predefined frequency range within the time span is counted. An actual reference value is determined by dividing the number of counted peaks by the time span. The actual reference value is compared with a nominal reference value, wherein the nominal reference value is determined by dividing a predefined number of peaks of the predefined frequency range by the time span, so that the combustion error type is predictable if the actual reference value differs to the nominal reference value.
-
公开(公告)号：US20180128182A1
公开(公告)日：2018-05-10
申请号：US15344778
申请日：2016-11-07
发明人： Mauro Hayama , Xin Zhao , Ming Tian , Mikhel Hawkins , Koji Asari , Thomas Charles Swager , Michael Allen Clawson
IPC分类号： F02C7/262
CPC分类号： F02C7/262 , F05D2220/32 , F05D2220/323 , F05D2260/85 , F05D2270/092 , F05D2270/304
摘要： A method of starting a gas turbine engine includes determining an abnormal shutdown condition during operation of the gas turbine engine and determining a first set of lightoff parameters for the gas turbine engine. The method also includes restarting the gas turbine engine using the first set of lightoff parameters. The method further includes iteratively determining subsequent first sets of lightoff parameters and restarting the gas turbine engine using a respective subsequent first set of the determined subsequent first sets of lightoff parameters until the gas turbine maintains a first set of operational parameters, where the first set of operational parameters is representative of a robust lightoff of the gas turbine engine.
-
公开(公告)号：US20170241346A1
公开(公告)日：2017-08-24
申请号：US15428005
申请日：2017-02-08
申请人： ROLLS-ROYCE PLC
发明人： Graham THOMPSON , Daniel WATERS
CPC分类号： F02C7/228 , F02C3/04 , F02C7/224 , F02C7/232 , F02C9/26 , F05D2270/092 , F05D2270/301 , F05D2270/31 , Y02T50/671
摘要： A combustion staging system includes a splitting unit receiving a metered fuel flow and controllably splitting the received flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel. A cooling flow recirculation line provides a cooling flow to the mains manifold during pilot-only operation, and a return section to collect mains manifold cooling flow. The cooling flow enters a delivery section and exits the return section. A fuel recirculating control valve on the delivery section has an open position so that the cooling flow enters the delivery section during pilot-only operation; a shut off position prevents the cooling flow entering the delivery section through the cooling flow orifice during pilot and mains operation. A supplementary valve bleeds or feeds cooling flow. The mains manifold cooling flow pressure is determined by the cooling flow and pressure raising orifices flow numbers, and a control setting of the supplementary valve.
-
公开(公告)号：US09574500B2
公开(公告)日：2017-02-21
申请号：US14595591
申请日：2015-01-13
CPC分类号： F02C9/30 , F02C7/232 , F02C7/236 , F02C7/32 , F02C9/26 , F02C9/263 , F05D2260/607 , F05D2270/092 , F05D2270/3062 , F05D2270/64 , Y02T50/675
摘要： A direct metering architecture is provided having a metering pump and a servo pump wherein the metering and servo pumps are driven by an engine shaft by way of a gearbox transmission. The system reduces wasted horsepower previously occurring with oversized fixed displacement pumps, reduces instances of engine flameout and reduces the amount of heat added to fuel which ultimately improves engine oil cooling.
摘要翻译： 提供了具有计量泵和伺服泵的直接计量结构，其中计量和伺服泵由发动机轴通过齿轮箱传动来驱动。 该系统减少了过大的固定排量的泵浪费的功率，减少了发动机熄火的情况，并减少了添加到燃料中的热量，从而最终改善了发动机机油冷却。
-
公开(公告)号：US20170021936A1
公开(公告)日：2017-01-26
申请号：US15288612
申请日：2016-10-07
发明人： Yoshihiro NAGASHIMA
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。
-
29.发明授权Servo flow recirculation for an advanced thermal efficient aircraft engine fuel system 有权先进的热效率飞机发动机燃油系统的伺服流量再循环公开(公告)号：US09388778B2
公开(公告)日：2016-07-12
申请号：US13946121
申请日：2013-07-19
申请人： Carthel C. Baker
发明人： Carthel C. Baker
CPC分类号： F02M37/0052 , F02C7/22 , F02C7/232 , F02C7/236 , F02C9/263 , F02M37/0047 , F05D2260/606 , F05D2270/092 , F05D2270/64 , Y10T137/0318 , Y10T137/85986 , Y10T137/87917
摘要： A fuel circulation system and methods are provided. The system includes a supply pump for providing an outlet flow of fuel. The system also includes at least a first and a second servo. The first servo is connected to an outlet of the supply pump. A flow regulation device is interposed between the first and second servos. At least a portion of the outlet flow from the supply pump is directed through the first servo, flow regulation device, and second servo and is returned to an inlet of the supply pump.
摘要翻译： 提供燃料循环系统和方法。 该系统包括用于提供燃料的出口流的供应泵。 该系统还包括至少第一和第二伺服系统。 第一个伺服系统连接到供水泵的出口。 流量调节装置插在第一和第二伺服机构之间。 来自供应泵的出口流的至少一部分被引导通过第一伺服，流量调节装置和第二伺服，并返回到供给泵的入口。
-
公开(公告)号：US20150300918A1
公开(公告)日：2015-10-22
申请号：US14242214
申请日：2014-04-01
发明人： Alan Greubel
IPC分类号： G01M15/10
CPC分类号： G01M15/102 , F02C9/46 , F05D2260/80 , F05D2270/092 , F05D2270/303
摘要： A method for detecting a flame condition in a combustor of an engine is disclosed. The method may include detecting a temperature of an exhaust gas from the engine, and determining the flame condition in the combustor based on the detected temperature.
摘要翻译： 公开了一种用于检测发动机的燃烧器中的火焰状态的方法。 该方法可以包括检测来自发动机的废气的温度，并且基于检测到的温度来确定燃烧器中的火焰状态。
-
-
-
-
-
-
-
-
-
搜索结果
119 条记录 (耗时 0.027 秒)
