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公开(公告)号：US20210054782A1
公开(公告)日：2021-02-25
申请号：US16545281
申请日：2019-08-20
摘要： A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a low speed spool; a first compressor, a turbine and a generator rotationally coupled via the low speed spool; a high speed spool; and a second compressor and a motor rotationally coupled via the high speed spool.
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公开(公告)号：US20190383218A1
公开(公告)日：2019-12-19
申请号：US16012295
申请日：2018-06-19
摘要： A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.
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公开(公告)号：US20190203643A1
公开(公告)日：2019-07-04
申请号：US16297001
申请日：2019-03-08
CPC分类号： F02C3/34 , F02C1/06 , F02C3/305 , F02C6/02 , F02C7/224 , F05D2220/76 , F05D2260/61 , F23L7/007 , F25J3/04018 , F25J3/04066 , Y02E20/16
摘要： The present disclosure relates to systems and methods for power production utilizing an ion transfer membrane (ITM) unit. An air stream and a fuel stream can be passed through the ITM unit so that the fuel is at least partially oxidized or combusted to form an outlet stream comprising CO2. The CO2 stream can be compressed and expanded to generate power.
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公开(公告)号：US10099796B2
公开(公告)日：2018-10-16
申请号：US15284827
申请日：2016-10-04
摘要： In one aspect, a method for dynamically controlling the operation of an aircraft having a first gas turbine engine and a second gas turbine engine may generally include receiving, by a first engine controller and a second engine controller, one or more operator commands deriving from an operator manipulated input device. The method may also include controlling the operation of the first gas turbine engine via the first engine controller, and the second gas turbine engine via the second engine controller. In addition, the method may include detecting a fault condition associated with the first engine controller, and subsequently switching control of the first gas turbine engine from the first engine controller to the second engine controller. The method may further include dynamically controlling the operation of the first gas turbine engine with the second engine controller.
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15.发明申请公开(公告)号：US20180208322A1
公开(公告)日：2018-07-26
申请号：US15745770
申请日：2016-07-21
摘要： The present invention relates to an aircraft comprising a fuselage and a thruster downstream of the fuselage. The thruster includes a power turbine, located inside a main flow jet, and at least one fan, located inside a secondary flow jet and mechanically driven by the power turbine. The main flow jet of the power turbine and the secondary flow jet of the fan are concentric. The power turbine is supplied with gases from two gas turbine gas generators via two supply channels. Said aircraft is characterized in that said gas turbine gas generators have axes parallel to that of the fuselage. The air inlet sleeve is spaced apart from the fuselage, and the supply channels each have a hatch for controlling the flow between a position for guiding the gas flow to the power turbine and a position for ejecting the gases into the atmosphere while bypassing the power turbine.
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公开(公告)号：US09828911B2
公开(公告)日：2017-11-28
申请号：US14327013
申请日：2014-07-09
发明人： Sascha Burghardt
CPC分类号： F02C3/045 , F01D13/003 , F01D13/02 , F02C3/10 , F02C6/02 , F05D2250/312
摘要： A turbofan engine includes a core engine, having a high-pressure compressor, a combustion chamber and a high-pressure turbine which are coupled to one another via a high-pressure shaft, at least one fan from which gas is supplied into both a primary flow duct and a secondary flow duct of the turbofan engine, at least one low-pressure turbine arranged behind the core engine, and at least one low-pressure shaft, with each low-pressure shaft coupling a fan to a low-pressure turbine. It has been provided that no low-pressure shaft of the turbofan engine passes through the core engine.
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17.发明申请METHOD OF REGULATING A THREE-ENGINED POWER PLANT FOR A ROTARY WING AIRCRAFT 审中-公开调整用于旋转式飞机的三座发电厂的方法公开(公告)号：US20160376017A1
公开(公告)日：2016-12-29
申请号：US15182663
申请日：2016-06-15
申请人： AIRBUS HELICOPTERS
发明人： Regis ROSSOTTO
CPC分类号： B64D31/06 , B64C27/04 , B64C27/12 , B64D35/08 , F02C6/02 , F02C6/206 , F02C9/42 , F05D2220/329 , F05D2270/023 , F05D2270/052 , F05D2270/13 , Y02T50/671
摘要： A power plant comprising two engine groups and a main power transmission gearbox. Each engine group drives the main gearbox mechanically in order to rotate a main rotor of an aircraft at a frequency of rotation NR. A first engine group comprising two main engines is regulated on a first setpoint NR* for the frequency of rotation NR, while a second engine group comprising a secondary engine is regulated on a second setpoint W2* for power of the second engine group. In addition, each engine operates with margins relative to operating limits. The second setpoint W2* for power is determined so that each secondary engine operates with a lowest second margin that is equal to the lowest first margin of the first engine group.
摘要翻译： 一个发电厂，包括两个发动机组和一个主动力传动齿轮箱。 每个发动机组以机械方式驱动主变速箱，以便以旋转频率NR旋转飞行器的主转子。 包括两个主发动机的第一发动机组在第一设定点NR *上针对旋转频率NR进行调节，而包括二次发动机的第二发动机组被调节在第二设定点W2 *上，用于第二发动机组的功率。 此外，每个发动机的运行边际相对于运行极限。 确定用于功率的第二设定点W2 *，使得每个次级发动机以等于第一发动机组的最低第一余量的最低第二余量运行。
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公开(公告)号：US09422863B2
公开(公告)日：2016-08-23
申请号：US13807143
申请日：2011-07-05
摘要： A method and architecture for recombining power of a turbomachine improving on problems of size, mass, or reliability. In the method energy is recovered in an exhaust nozzle and converted and recirculated using a mechanical and/or electrical power recombining mechanism. An example of an architecture of a turbomachine includes a main turbine engine and a heat exchanger positioned in the exhaust nozzle and coupled, via pipes, to an independent system that converts thermal energy into mechanical energy. This independent system is connected to a localized mechanical recombination mechanism via a power shaft to supply power to a power transmission shaft according to aircraft requirements.
摘要翻译： 一种用于重新组合涡轮机功率的方法和架构，改善了尺寸，质量或可靠性的问题。 在该方法中，在废气喷嘴中回收能量，并使用机械和/或电力重组机构进行转化和再循环。 涡轮机的结构的一个例子包括主涡轮发动机和位于排气喷嘴中的热交换器，并通过管道耦合到将热能转换成机械能的独立系统。 该独立系统通过动力轴连接到局部机械复合机构，以根据飞机要求向动力传递轴提供动力。
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公开(公告)号：US20150322856A1
公开(公告)日：2015-11-12
申请号：US14684918
申请日：2015-04-13
发明人： Lee J. Robinson , James A. McEwen
CPC分类号： F02B37/004 , F02B37/001 , F02B37/002 , F02B37/007 , F02B37/013 , F02B37/16 , F02B37/18 , F02B37/183 , F02B39/00 , F02D9/06 , F05D2210/12 , F05D2220/40 , F05D2240/40 , F05D2270/3013 , Y02T10/144
摘要： A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.
摘要翻译： 涡轮增压器系统包括第一相对较小的涡轮增压器和串联连接的第二较大涡轮增压器和排气流量控制阀。 排气控制阀具有与第一涡轮机上游的废气流连通的入口端口，与所述第一涡轮机下游的排气流，与所述第二涡轮机的上游连通的第一出口端口，以及与排气流连通的第二出口 在所述第二涡轮机的下游。 阀可操作以选择性地允许或阻止流过第一和第二出口。
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公开(公告)号：US20150121838A1
公开(公告)日：2015-05-07
申请号：US14190175
申请日：2014-02-26
发明人： Gabriel L. Suciu , Brian D. Merry
CPC分类号： B64D29/06 , B64D27/20 , F01D13/003 , F02K1/52 , F02K1/54 , F02K1/60 , F02K1/64 , F05D2250/314
摘要： A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.
摘要翻译： 联合燃气涡轮发动机的系统具有第一发动机，第一发动机具有第一推进器和第二发动机，第一发动机具有第一轴线，第一发动机机芯具有第二轴线，第二发动机具有带有第三轴线的第二推进器和具有第四轴线的第二发动机机芯 。 第一轴和第三轴彼此平行; 并且第二轴线和第四轴线彼此成角度。
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