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公开(公告)号：US20240141839A1
公开(公告)日：2024-05-02
申请号：US17976509
申请日：2022-10-28
CPC分类号： F02C9/28 , F02C9/44 , F05D2220/323 , F05D2270/051 , F05D2270/304 , F05D2270/311 , F05D2270/313 , F05D2270/708
摘要： A method and system for correlating engine thrust and engine thrust lever angle (TLA) during operation of a gas turbine engine powered aircraft is provided. The method includes: a) providing current flight conditions including a Mach number of the aircraft, altitude of the aircraft, and a TLA; b) determining a corrected fan speed value based on a sensed fan speed and flight conditions; c) determining a first corrected net thrust value based on the corrected fan speed value and the Mach number; d) determining a compensation factor using the corrected fan speed value, the Mach number, and the corrected net thrust value; e) determining a second corrected net thrust value as a function of the TLA; and f) correlating an engine fan speed to the TLA using the second corrected net thrust value as a function of the TLA and the compensation factor.
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公开(公告)号：US11674454B2
公开(公告)日：2023-06-13
申请号：US17205435
申请日：2021-03-18
发明人： Matej Rutar , Francis P. Marocchini
CPC分类号： F02C9/263 , F02C7/228 , F05D2220/32 , F05D2270/051
摘要： A system includes a flow inlet conduit. A primary conduit branches from the flow inlet conduit for delivering flow to a set of primary nozzles. An equalization bypass valve (EBV) connects between the flow inlet conduit and a secondary conduit for delivering flow to a set of secondary nozzles. The EBV is connected to be controlled to apportion flow from the flow inlet conduit to the secondary conduit. A secondary equalization valve (SEV) connects between the flow inlet conduit and the secondary conduit. The SEV is connected to be controlled by drain pressure (PD) to apportion flow from the flow inlet conduit to the secondary conduit.
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公开(公告)号：US20180237125A1
公开(公告)日：2018-08-23
申请号：US15446262
申请日：2017-03-01
发明人： Carmine LISIO , Kenneth MATHESON
CPC分类号： B64D31/06 , B64C11/30 , B64C11/303 , B64D27/10 , F02C9/58 , F05D2220/325 , F05D2270/051 , F05D2270/122
摘要： There are described methods and systems for providing an autothrottle mode in a propeller-driven aircraft. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine. When greater than a pre-determined threshold, a setting change to one or more control input(s) of the engine is determined. One or more commands is output to cause the setting change of the control input(s).
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公开(公告)号：US09863367B2
公开(公告)日：2018-01-09
申请号：US14070393
申请日：2013-11-01
申请人： THE BOEING COMPANY
CPC分类号： F02K1/766 , F02K1/1207 , F02K1/625 , F02K1/72 , F02K1/763 , F05D2220/36 , F05D2260/30 , F05D2260/53 , F05D2260/90 , F05D2270/051
摘要： Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.
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公开(公告)号：US20170218882A1
公开(公告)日：2017-08-03
申请号：US15009298
申请日：2016-01-28
申请人： The Boeing Company
CPC分类号： F02K1/18 , F02K1/06 , F02K1/12 , F02K1/15 , F05D2220/32 , F05D2270/051 , F05D2270/804 , F05D2270/808 , G01B11/24 , G01L1/242 , G01L1/246
摘要： A control system for a variable area fan nozzle (VAFN) having a plurality of petals is disclosed. The control system may include at least one fiber optic shape sensor extending along at least one of the plurality of petals, and a light source operatively connected to the at least one fiber optic shape sensor. The control system may further include a receiver operatively connected to the at least one fiber optic shape sensor. The control system may further include a VAFN control unit in operative communication with the plurality of petals and the receiver. The VAFN control unit may be configured to receive a signal from the receiver indicative of the measured strain along the at least one fiber optic shape sensor, and calculate a nozzle area of the VAFN based on the measured strain.
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公开(公告)号：US20170198644A1
公开(公告)日：2017-07-13
申请号：US15314048
申请日：2015-05-13
CPC分类号： F02C9/44 , F02C9/26 , F02C9/28 , F05D2270/051 , F05D2270/101
摘要： A method for controlling thrust from a turbojet that is fuel flow rate regulated by a high limit value for providing protection against surging of a compressor of the turbojet is provided. The method includes: obtaining a first thrust value corresponding to a first operating point of the compressor on the high limit value, the high limit value taking account of an underestimate of the fuel flow rate; controlling the turbojet to reach the first thrust value; monitoring the turbojet to detect underspeed of the compressor; and where applicable: obtaining a second thrust value corresponding to a second operating point that guarantees a predetermined margin relative to the high limit value so as to obtain protection against underspeed of the turbojet; and controlling the turbojet to reach the second value.
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公开(公告)号：US09650996B2
公开(公告)日：2017-05-16
申请号：US14657799
申请日：2015-03-13
申请人： The Boeing Company
发明人： Gregory H. Smith , Julio C. Martinez , Fernando C. Teran , Romy Andrade Reyes , B. Wayne Pauley , Randall W. Watkins
CPC分类号： F02K9/566 , B64G1/402 , B64G1/60 , F02K9/50 , F02K9/56 , F02K9/605 , F05D2220/80 , F05D2270/051 , F05D2270/301
摘要： Method and apparatus for controlling pressure in a pressure vessel. A plurality of valves between a pressure source and a pressure vessel can be selectively opened or turned off, singularly or in combinations, to control pressure in the pressure vessel. A maximum pressure threshold and a minimum pressure threshold can be established based on operating considerations of the pressure vessel. One or more of the valves can be turned on when the pressure in the pressure vessel reaches the minimum pressure threshold. One or more of the valves can be turned off when the pressure in the pressure vessel reaches the maximum pressure threshold.
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8.发明申请公开(公告)号：US20170107914A1
公开(公告)日：2017-04-20
申请号：US14886169
申请日：2015-10-19
发明人： Manxue Lu , Jeffrey Anthony Hamel
CPC分类号： F02C9/58 , B64D27/10 , F02C9/44 , F02C9/54 , F02K1/66 , F02K3/04 , F02K3/06 , F05D2220/323 , F05D2220/325 , F05D2270/051 , F05D2270/3011 , F05D2270/303 , F05D2270/304
摘要： A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided. The method can include receiving into a control system at least one condition input from a respective sensor; receiving into a control system a low pressure shaft speed from a low pressure shaft speed sensor; receiving a control command from a full authority digital engine control (FADEC) in the control system; generating a low pressure shaft speed base reference from a first schedule logic in the control system based upon the at least one condition input received and the control command received; generating a beta angle base reference from a second schedule logic from the at least one condition input received, the low pressure shaft speed, and the control command received; and supplying the low pressure shaft speed base reference and the beta angle base reference to an engine control system, wherein the engine control system adjusts at least the pitch angle of the plurality of fan blades or a fuel flow to the engine.
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公开(公告)号：US09506423B2
公开(公告)日：2016-11-29
申请号：US14206232
申请日：2014-03-12
摘要： A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.
摘要翻译： 燃气涡轮发动机包括核心发动机，围绕核心发动机设置的第一旁路通道和围绕第一旁路通道设置的第二旁路通道。 流量控制器设置在第二旁路内用于控制通过第二旁路的旁路气流。 流量控制在打开位置和关闭位置之间轴向平移以改变和控制通过第二旁路通道的气流。
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公开(公告)号：US20160341149A1
公开(公告)日：2016-11-24
申请号：US15230086
申请日：2016-08-05
CPC分类号： F02K1/605 , F01D25/24 , F02C3/04 , F02K1/60 , F02K1/62 , F02K1/625 , F02K1/64 , F02K1/70 , F02K1/72 , F02K1/763 , F02K1/766 , F05D2220/32 , F05D2230/72 , F05D2240/14 , F05D2270/051
摘要： A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.
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