公开(公告)号：US10077675B2

公开(公告)日：2018-09-18

申请号：US15272768

申请日：2016-09-22

申请人： ROLLS-ROYCE plc

发明人： Robert John Irving

IPC分类号： B08B5/02 ,  B64D13/00 ,  F01D25/00 ,  F02C7/04 ,  F01D25/12 ,  F02C7/18 ,  B64D33/08 ,  F02C6/08 ,  B64D33/02

CPC分类号： F01D25/002 ,  B08B5/02 ,  B64D13/00 ,  B64D33/08 ,  B64D2033/024 ,  B64D2241/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/04 ,  F02C7/18 ,  F05D2250/18 ,  Y02T50/671 ,  Y02T50/675 ,  Y10T137/0536

摘要： A fluid system comprising a surface that is fluid washed in use by a fluid flow travelling substantially parallel to the surface is disclosed. The system has a first port through the surface and a second port through the surface, the first and second ports having respective first and second port inlets that are substantially flush with the fluid washed surface. The first and second port inlets are stacked in a direction parallel to the normal flow of fluid over the fluid washed surface such that the first port is upstream of the second port and fluid travelling closer to the fluid-washed surface entering into the first port tends to entrain fluid travelling further from the fluid-washed surface for entry into the second port.

公开(公告)号：US10035601B2

公开(公告)日：2018-07-31

申请号：US14231993

申请日：2014-04-01

申请人： Airbus Operations GmbH

发明人： Martin Schmid ,  Christian Bartels ,  Frank Klimpel ,  Klaus Vehlhaber

IPC分类号： B64D13/00 ,  B64D13/06

CPC分类号： B64D13/00 ,  B64D2013/0611 ,  B64D2013/0618 ,  B64D2241/00 ,  Y02T50/56

摘要： An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

公开(公告)号：US09340296B2

公开(公告)日：2016-05-17

申请号：US13471835

申请日：2012-05-15

申请人： Renaud Loison

发明人： Renaud Loison

IPC分类号： B64D37/08 ,  B64D41/00

CPC分类号： B64D37/08 ,  B64D41/00 ,  B64D2241/00 ,  Y02T50/44 ,  Y10T137/0318 ,  Y10T137/85978

摘要： An aircraft fuel storage device having at least one main reservoir designed to contain a first batch of fuel and at least one feed line for supplying a propulsion engine of the aircraft with the first batch of fuel contained in the main reservoir and having at least one auxiliary reservoir, designed to contain a second batch of fuel separate from the first batch of fuel, and wherein the auxiliary reservoir is connected to the main reservoir. The device also having an intake line for bringing the second batch of fuel contained in the auxiliary reservoir toward a combustion chamber of the aircraft independent of the propulsion engine of the aircraft.

摘要翻译： 一种飞机燃料储存装置，具有至少一个主容器，其设计成容纳第一批燃料和至少一个供给管线，用于为飞行器的推进发动机提供容纳在主容器中的第一批燃料，并具有至少一个辅助 储存器，设计成容纳与第一批燃料分开的第二批燃料，并且其中辅助储存器连接到主储存器。 该装置还具有用于将容纳在辅助储存器中的第二批燃料朝向飞机的燃烧室独立于飞行器的推进发动机的进气管线。

公开(公告)号：US20150369065A1

公开(公告)日：2015-12-24

申请号：US14743584

申请日：2015-06-18

申请人： United Technologies Corporation

发明人： John M. Feiereisen

IPC分类号： F01D9/02 ,  F01D25/24

CPC分类号： F01D9/02 ,  B64C7/02 ,  B64D2241/00 ,  F01D25/24 ,  F02C6/06 ,  F02C7/04 ,  F02K3/075 ,  F05D2260/60

摘要： An air scoop assembly that may be for a nacelle of a turbofan engine includes a surface defining at least in-part a primary flowpath and a hood formed to the surface and projecting into the primary flowpath. The hood includes a distal, leading, edge that is irregular in shape thereby producing air vortices that shed from the leading edge and co-extend in a downstream direction with an airstream in the primary flowpath. The vortices are thereby controlled such that air flow disruption and undesired resonance is minimized or eliminated.

摘要翻译： 可用于涡轮风扇发动机的发动机舱的空气铲组件包括至少部分地限定主要流动路径的表面和形成于该表面并且突出到主流路中的罩。 发动机罩包括一个远端的前缘，其形状不规则，从而产生从前缘离开的空气涡流，并沿主流道中的气流沿下游方向共同延伸。 由此控制涡流，使得气流中断和不期望的共振被最小化或消除。

公开(公告)号：US20130168502A1

公开(公告)日：2013-07-04

申请号：US13725534

申请日：2012-12-21

申请人： EMBRAER S.A.

发明人： Carlos Roberto Ilàrio DA SILVA ,  André Luis RONCATTO ,  Antônio Nunes BELÉM ,  Marcelo Faria DA CUNHA

IPC分类号： B64D41/00

CPC分类号： B64D41/00 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0213 ,  B64D2241/00 ,  Y02T50/53

摘要： Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.

摘要翻译： 用于飞机空气入口的分流器组件包括至少基本上围绕空气入口的分流器结构，以及整流罩，其安装在分流器结构的上部边缘的前方。

公开(公告)号：US20110290943A1

公开(公告)日：2011-12-01

申请号：US12786474

申请日：2010-05-25

申请人： Andrew WILDE ,  Jean-claude BOSSUT ,  Marc REVEL ,  Alan John HAYLES ,  Ruchir DAYAL ,  Hannah KENDALL

发明人： Andrew WILDE ,  Jean-claude BOSSUT ,  Marc REVEL ,  Alan John HAYLES ,  Ruchir DAYAL ,  Hannah KENDALL

IPC分类号： B64D37/04 ,  B64D13/08

CPC分类号： B64D37/04 ,  B64D37/02 ,  B64D37/06 ,  B64D37/32 ,  B64D2013/0659 ,  B64D2241/00

摘要： Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air.

摘要翻译： 飞机机身燃料箱中的燃料通过从飞机外部流到飞机内的冷却区域的冷空气冷却。 冷却区域可以是（a）位于燃料箱的外部，（b）与燃料箱热连通，（c）与所述冷却区域的下游和远离区域流体连通，例如 ，飞机外侧的排气口。 空气流可能是空气进入冲击空气进气口，由于空中飞行器相对于周围空气的运动，空气通过。

公开(公告)号：US20110073716A1

公开(公告)日：2011-03-31

申请号：US12894488

申请日：2010-09-30

申请人： Dipl.-Ing Frank Klimpel

发明人： Dipl.-Ing Frank Klimpel

IPC分类号： B64D33/00

CPC分类号： B64D13/00 ,  B64D2241/00 ,  Y02T50/56

摘要： A ram air duct flap arrangement (22) comprises at least one ram air duct flap (24, 26) which is designed to close, in a closed position, a ram air inlet (14) or a ram air outlet (18) of a ram air duct (10) and, at least partly open, in an open position, the ram air inlet (14) or the ram air outlet (18) of the ram air duct (10). Furthermore, the ram air duct flap arrangement (22) comprises an actuator (32) for actuating the ram air duct flap (24, 26) between its closed position and its open position. A pressure control device (42) is designed to control a pressure (pi), which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an inner surface (44) of the ram air duct flap (24, 26) facing an interior of the aircraft, in such a way that it corresponds substantially to a pressure (pa) which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an outer surface (38) of the ram air duct flap (24, 26) facing the external environment.

摘要翻译： 冲压空气管道翼片装置（22）包括至少一个冲压空气管道挡板（24,26），其设计成在关闭位置关闭压头空气入口（14）或冲压空气出口（18） 冲压空气管道（10），并且在打开位置至少部分地打开冲压空气管道（10）的冲压空气入口（14）或冲压空气出口（18）。 此外，冲压空气管道翼片装置（22）包括致动器（32），用于在其关闭位置和其打开位置之间致动冲压空气管道挡板（24,26）。 压力控制装置（42）被设计成控制压力（pi），当压头空气管道挡板装置（22）安装在飞行器中时，该压力作用在冲压空气管道挡板的内表面（44）上 24,26）面向飞行器的内部，使得其基本上对应于当冲压空气管道翼片装置（22）安装在飞行器中时的压力（pa）作用在外表面（38）上 ）的冲击空气管道翼片（24,26）面向外部环境。

公开(公告)号：US07849702B2

公开(公告)日：2010-12-14

申请号：US11765748

申请日：2007-06-20

申请人： Pradip G. Parikh

发明人： Pradip G. Parikh

IPC分类号： B60H1/32 ,  F25D9/00 ,  B64D33/02

CPC分类号： B64D13/00 ,  B64D2241/00 ,  Y02T50/44 ,  Y02T50/54 ,  Y02T50/56

摘要： Aircraft environmental control systems having a single ram air inlet providing air to both cabin air compressors and associated heat exchangers are disclosed herein. In one embodiment, and environmental control system for use with an aircraft includes a ram air inlet, an air conditioning pack, and an associated heat exchanger. In this embodiment, the ram air inlet provides a first portion of air to the air conditioning pack, and a second portion of air to the associated heat exchanger. The first portion of air flows from the air conditioning pack and through the heat exchanger before flowing into an aircraft cabin. The second portion of air from the ram air inlet cools the first portion of air in the heat exchanger before exiting the aircraft through a ram air outlet. The inlet and outlet can be modulated on an optimized schedule to minimize the net drag of the ram system.

摘要翻译： 本文公开了具有向舱室空气压缩机和相关热交换器提供空气的单个冲压空气入口的飞行器环境控制系统。 在一个实施例中，与飞行器一起使用的环境控制系统包括冲压空气入口，空调组件和相关联的热交换器。 在该实施例中，冲压空气入口将空气的第一部分提供给空调组件，并将空气的第二部分提供给相关联的热交换器。 第一部分的空气在流入飞机机舱之前从空气调节组件流过热交换器。 来自冲压空气入口的空气的第二部分在离开飞行器之前通过冲压空气出口冷却热交换器中的第一部分空气。 入口和出口可以按照优化的时间表进行调节，以最小化压头系统的净阻力。

公开(公告)号：US07624944B2

公开(公告)日：2009-12-01

申请号：US11553181

申请日：2006-10-26

申请人： Pradip G Parikh ,  Warren A Atkey

发明人： Pradip G Parikh ,  Warren A Atkey

IPC分类号： B64D33/02

CPC分类号： B64D13/02 ,  B64C21/00 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2241/00 ,  Y02T50/166 ,  Y02T50/56 ,  Y10T137/0536

摘要： A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inlet is disposed forwardly of the Pitot inlet and longitudinally aligned with the Pitot inlet, for supplying cooling air to a heat exchanger of the air conditioning pack. By locating the heat exchanger inlet forwardly and longitudinally in line with the Pitot inlet, the heat exchanger inlet is able to effectively swallow a large portion of the boundary layer, which results in a thinner boundary layer at the inlet face of the Pitot inlet. This enables a smaller throat area Pitot inlet to be used, as well as a shorter diverter height to be employed with the Pitot inlet, while still realizing an improved recovery factor (RF) performance with the Pitot inlet. The reduced height Pitot inlet also enables drag to be reduced.

摘要翻译： 一种与高速移动平台（例如商用或军用飞机）一起使用的串联入口装置。 串联入口设备包括皮托特入口，用于将空气供给到在移动平台上承载的空调包的客舱空气压缩机（CAC）。 冲洗式热交换器入口设置在皮托特入口的前方并与皮托特入口纵向对准，以将冷却空气供应到空调包装的热交换器。 通过将热交换器入口向前和纵向设置为与皮托特入口一致，热交换器入口能够有效地吞下边界层的大部分，这导致在皮托特入口的入口面处更薄的边界层。 这使得能够使用较小的喉部区域Pitot入口，以及与皮托特入口一起使用的更短的分流器高度，同时仍然使用皮托特入口实现改进的恢复因子（RF）性能。 减小的皮托托入口也可以减少拖曳。

公开(公告)号：US4674704A

公开(公告)日：1987-06-23

申请号：US804034

申请日：1985-12-03

申请人： Frank E. Altoz ,  John J. Buckley

发明人： Frank E. Altoz ,  John J. Buckley

IPC分类号： H05K7/20 ,  B64C21/02

CPC分类号： H05K7/20136 ,  B64D2241/00 ,  Y10S62/05

摘要： A direct air cooling system 12 for electronics carried by aircraft. The cooling system provides a submerged air scoop 16 which directs outside air to several electronic modules 14. The air flows through passages 76 in the modules 14 which are adjacent to circuit boards 74, 78 bearing discrete electronic components 88. A foil layer 86 and aluminum fin stock help transfer heat from the electronic components to the directed air. Heated air is then exhausted through exhaust port 24 or 28.

摘要翻译： 由飞机运载的电子设备的直接空气冷却系统12。 冷却系统提供了一个浸没的空气勺16，其将外部空气引导到几个电子模块14.空气流过模块14中的通道76，模块14与承载离散电子部件88的电路板74,78相邻。箔层86和铝 散热片有助于将热量从电子部件传递到定向空气。 加热空气然后通过排气口24或28排出。