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公开(公告)号：EP3147214B1
公开(公告)日：2018-06-27
申请号：EP16190009.7
申请日：2016-09-21
摘要： An outflow valve (22) is provided. The outflow valve includes a frame (34) and a first door (30) rotatably coupled to the frame. The first door has a first side (50) opposite a second side (52) and a bellmouth (56). The bellmouth is defined by a super-ellipse (70), with a major axis (72) of the super-ellipse substantially parallel to the second side and a minor axis (74) of the super-ellipse substantially perpendicular to the second side (52). The outflow valve also includes a second door (32) rotatably coupled to the frame. The first door and the second door are substantially simultaneously movable between at least a first position and a second position.
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公开(公告)号：EP3135586B1
公开(公告)日：2018-01-31
申请号：EP16168591.2
申请日：2016-05-06
申请人： The Boeing Company
CPC分类号： B64D13/04 , B64C1/1407
摘要： Disclosed herein is a hybrid mechanical/reactive pressure prevention system that includes a passive pressure control device (202) operably coupled to a door that allows air within a pressurized vehicle to flow out of the pressurized vehicle. An event module detects a door event in the pressurized vehicle. The door event indicates that a door is not secure and air within the pressurized vehicle is being released through the passive pressure control device. An altitude module (208) determines an altitude of the pressurized vehicle in response to detecting the door event. An electronic pressure control device (204) one or more of reduces air inflow into the pressurized vehicle and increases air outflow out of an active pressure control device of the pressurized vehicle in response to the altitude of the pressurized vehicle being below a cutoff altitude.
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3.发明公开
公开(公告)号：EP3190050A1
公开(公告)日：2017-07-12
申请号：EP17150623.1
申请日：2017-01-09
CPC分类号： G01F25/0007 , B64D13/02 , B64D13/04 , B64D13/06 , B64D2013/0603 , G01F1/44 , G01F1/50 , G01F1/6842
摘要： A matched venturi assembly is provided and includes a venturi component (20) configured to provide for fluid communication between an inlet (21) and an outlet (23), sensors (30) coupled to the venturi component and configured to generate readings of characteristics of fluid flows proceeding through the venturi component and a venturi controller (40), which is receptive of the readings from the sensors. The venturi controller is configured to interpret the readings and is trimmable in a test phase where fluid flows with known characteristics are flown through the venturi component and interpretations of the readings are calibrated in accordance with differences between the readings and the known characteristics.
摘要翻译： 提供了匹配的文丘里管组件，并且包括构造成提供入口（21）和出口（23）之间的流体连通的文氏管部件（20），联接到文丘里管部件上并且被配置为产生特征读数的传感器（30） 流体流动通过文丘里管部件和文氏管控制器（40），其接受来自传感器的读数。 文丘里控制器被配置为解释读数并且在具有已知特性的流体流经文氏管部件的测试阶段是可修整的，并且根据读数和已知特性之间的差异校准读数的解释。
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公开(公告)号：EP2492190A3
公开(公告)日：2015-11-04
申请号：EP12001193.7
申请日：2012-02-22
CPC分类号： B64C1/066 , B64C1/18 , B64C2001/009 , B64D13/04
摘要： A decompression arrangement (10) for an aircraft comprises a first cabin lining element (12) with an edge region (14), a second cabin lining element (20) with an edge region (22), the edge region (22) of the second cabin lining element (20) being arranged at a smaller distance from an aircraft outer skin (26) than the edge region (14) of the first cabin lining element (12), an air discharge opening (28), which is arranged between the edge region (14) of the first cabin lining element (12) and the edge region (22) of the second cabin lining element (20) and which is adapted, in the normal operation of the aircraft, to discharge air from an inner region of the cabin (18) delimited by the cabin lining elements (12, 20) into a region (30) of the aircraft lying between the cabin lining elements (12, 20) and the aircraft outer skin (26), and a decompression element (32), which is integrated in the second cabin lining element (20) and has a flap (34) which is pivotable about an axis (A) from a closed position, in which it closes a pressure equalising opening (35) formed in the decompression element (32), into a first open position, in which it opens the pressure equalising opening (35) formed in the decompression element (32) if a first predetermined differential pressure acts on the decompression element (32). The flap (34) of the decompression element (32) furthermore is pivotable about the axis (A) in a second direction opposite the first direction into a second open position, in which it opens the pressure equalising opening (35) formed in the decompression element (32) if a second predetermined differential pressure acts on the decompression element (32), the decompression element (32) being positioned relative to the first and the second cabin lining element (12, 20) in such a manner that the flap (34) in its second open position keeps clear a through-flow cross-section of the air discharge opening (28).
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5.发明公开Method and system for controlling the pressure in an aircraft cabin 有权Verfahren und System zur Steuerung des Drucks in einer Flugzeugkabine
公开(公告)号：EP2921408A1
公开(公告)日：2015-09-23
申请号：EP14161066.7
申请日：2014-03-21
发明人： Krittian, Sebastian
摘要： In a method for controlling the pressure in an aircraft cabin (11), during flight operation of the aircraft, an effective flow cross-sectional area of at least one outflow valve (12) is controlled so as to adjust an air flow exiting the aircraft cabin (11) through the outflow valve (12) such that the pressure within the aircraft cabin (11) is controlled in accordance with a predetermined cabin pressure control strategy. Further, during flight operation of the aircraft, an effective flow cross-sectional area of at least one negative relief valve (14) is controlled so as to adjust an air flow entering the aircraft cabin (11) through the negative relief valve (14) such that a negative differential pressure between the pressure within the aircraft cabin (11) and an ambient pressure prevailing outside of the aircraft cabin (11) is prevented from exceeding a predetermined threshold value. During ground operation of the aircraft, the effective flow cross-sectional area of the at least one negative relief valve (14) is controlled so as to allow an equalization between the pressure within the aircraft cabin (11) and the ambient pressure prevailing outside of the aircraft.
摘要翻译： 在用于控制飞机机舱（11）中的压力的方法中，在飞行器的飞行操作期间，控制至少一个流出阀（12）的有效流动横截面积，以便调节离开飞行器的空气流 （11）通过流出阀（12），使得飞机机舱（11）内的压力根据预定的机舱压力控制策略进行控制。 此外，在飞行器的飞行操作期间，控制至少一个负的安全阀（14）的有效流动横截面积，以便通过负的安全阀（14）调节进入飞机机舱（11）的空气流， 使得防止飞机机舱（11）内的压力与飞机机舱（11）外部的主要压力之间的负压差超过预定的阈值。 在飞行器的地面操作期间，控制至少一个负的安全阀（14）的有效流动横截面积，以便使飞机机舱（11）内的压力与主要在 飞机。
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6.发明授权
公开(公告)号：EP2603428B1
公开(公告)日：2015-07-22
申请号：EP11720103.8
申请日：2011-05-17
发明人： STEINERT, Martin , SPRINGER, Axel
CPC分类号： B64D13/04 , B64D13/02 , F16K1/223 , F16K39/028 , G05D7/0647 , Y02T50/44 , Y10T137/87917
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7.发明公开Ventil zur Steuerung des Innendrucks in einer Kabine eines Luftfahrzeugs 审中-公开Ventine zur Steuerung des Innendrucks在einer Kabine eines Luftfahrzeugs
公开(公告)号：EP2851297A1
公开(公告)日：2015-03-25
申请号：EP14190707.1
申请日：2011-05-17
发明人： Steinert, Martin , Springer, Axel
CPC分类号： B64D13/04 , B64D13/02 , F16K1/223 , F16K39/028 , G05D7/0647 , Y02T50/44 , Y10T137/87917
摘要： Die Erfindung betrifft ein Ventil (10) zur Steuerung des Innendrucks p i in einer Kabine eines Luftfahrzeugs, mit einer ersten Klappe (11) und einer zweiten Klappe (12), wobei die Klappen (11, 12) einen den Druck verändernden Fluidstrom (L) zwischen der Umgebung und der Kabine durch eine Öffnung (15) eines Begrenzungselements (14) der Kabine steuern. Um in der Einströmstellung der Klappen ein Ausströmen der Luft zu verhindern, ist eine Verschlusseinrichtung vorgesehen, die in der Einströmstellung der Klappen (11,12) einen Bereich (18) zwischen der ersten Klappe (11) und der zweiten Klappe (12) verschließt, der durch die Klappen (11,12) begrenzt wird.
摘要翻译： 本发明涉及一种用于控制飞行器舱室内部压力p的阀门（10），其包括第一挡板（11）和第二挡板（12），其中所述挡板（11,12）控制压力变化 通过机舱的限制元件（14）的开口（15）在周围和车厢之间的流体流（L）。 为了增加流体的流入体积，根据本发明，至少一个襟翼（11,12）可以相对于开口（15）在周围的方向上相对于流入位置是可调节的，使得 空气流（L）的叶片（11,12）的流动面增加。 此外，根据本发明，至少一个翼片（11,22）具有闭合装置（21），其减少了在流入过程中预先流入的流体的流出。 根据本发明，还布置了闭合装置（21），其中所述闭合装置在所述翼片（11,12）的流入位置中封闭所述第一翼片（11）和所述第二翼片（12）之间的区域。
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8.发明公开Environmental control system (ECS) including a compressing device 审中-公开Umweltkontrollsystem（ECS）mit Kompressorvorrichtung
公开(公告)号：EP2845804A1
公开(公告)日：2015-03-11
申请号：EP14182692.5
申请日：2014-08-28
发明人： Bruno, Louis J. , Hipsky, Harold W.
IPC分类号： B64D13/06
CPC分类号： B64D13/04 , B64D13/06 , B64D13/08 , B64D2013/0614 , B64D2013/0618 , B64D2013/0644 , F02C7/185 , Y02T50/56
摘要： A compressing device (220) is added to a cabin air conditioning system to increase a pressure of air in the cabin air conditioning system itself and, thus, allow for lower pressure air to be bled from the engine. For instance, the compressing device allows air to be bled from a low, rather than a high, pressure locations of the engine.
摘要翻译： 压缩装置（220）被添加到机舱空调系统中以增加机舱空调系统本身的空气压力，从而允许从发动机排出较低压力的空气。 例如，压缩装置允许空气从发动机的低压而不是高的压力位置排出。
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9.发明公开System and method for refrigerating galley compartments 有权系统与Verfahren zurKühlungvonBordküchenabteilen
公开(公告)号：EP2845802A1
公开(公告)日：2015-03-11
申请号：EP14183463.0
申请日：2014-09-03
申请人： The Boeing Company
发明人： Moran, Thomas J. , Rumill, David M.
CPC分类号： B64D13/04 , B64D11/0007 , B64D11/04 , B64D13/08 , F25D15/00 , F25D17/045 , F25D17/06 , F25D2700/08
摘要： A refrigeration system (10) for providing cooled air to a plurality of galley compartments. The refrigeration system (10) includes a plurality of galley compartments configured to receive therein at least one galley cart (102), a refrigeration unit (20) configured to supply cooled air to the plurality of galley compartments, and an airflow supply and return system (30) coupling the refrigeration unit (20) to the plurality of compartments. The refrigeration system (10) also includes a plurality of valves (50, 52) coupled in the airflow supply and return system (30) for controlling flows of the cooled air through airflow supply and return system (30), each valve of the plurality of valves (50, 52) associated with a compartment of the plurality of compartments and a controller (60) in control communication with the plurality of valves (50, 52), the controller (60) configured to control the plurality of valves (50, 52) to achieve a first temperature in a first galley compartment of the plurality of galley compartments and a second temperature in a second galley compartment of the plurality of galley compartments, the first temperature being different than the second temperature.
摘要翻译： 一种用于向多个厨房隔间提供冷却空气的制冷系统（10）。 制冷系统（10）包括多个厨房室，其构造成在其中容纳至少一个厨房推车（102），构造成将冷却的空气供应到多个厨房隔间的制冷单元（20），以及气流供应和返回系统 （30）将制冷单元（20）连接到多个隔间。 制冷系统（10）还包括联接在气流供应和返回系统（30）中的多个阀（50,52），用于控制冷却空气通过气流供应和返回系统（30）的流动，多个阀 与所述多个隔室的隔间相关联的阀门（50,52）以及与所述多个阀门（50,52）控制连通的控制器（60），所述控制器（60）被配置成控制所述多个阀门 ，52）以实现所述多个厨房隔室中的第一厨房隔室中的第一温度和所述多个厨房隔室中的第二厨房隔室中的第二温度，所述第一温度不同于所述第二温度。
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公开(公告)号：EP2634092A1
公开(公告)日：2013-09-04
申请号：EP13157154.9
申请日：2013-02-28
CPC分类号： B64D13/006 , B64D13/00 , B64D13/04 , B64D2013/0655
摘要： An active airflow control system 100, for an aircraft includes an air conditioning system 102, an air conditioning controller 110, configured to control operation of the air conditioning system, a plurality of flow control devices 104, in fluid communication with the air conditioning system and in signal communication with the air conditioning controller, wherein the plurality of flow control devices 104, are configured to increase and decrease an amount of air flowing therethrough in response to receiving a controlling signal from the air conditioning controller 110, and a plurality of zones in fluid communication with the air conditioning system, wherein each zone of the plurality of zones 105, is a pressurized zone of the aircraft, and wherein each zone of the plurality of zones is in fluid communication with at least one flow control device of the plurality of flow control devices.
摘要翻译： 用于飞行器的主动气流控制系统100包括空调系统102，空调控制器110，其被配置为控制空调系统的操作;多个流量控制装置104，其与空调系统流体连通;以及 与空调控制器进行信号通信，其中多个流量控制装置104被配置为响应于接收到来自空调控制器110的控制信号而增加和减少流过其中的空气量，以及多个区域 与空调系统的流体连通，其中多个区域105中的每个区域是飞机的加压区域，并且其中多个区域中的每个区域与多个区域的至少一个流量控制装置流体连通 流量控制装置。
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