公开(公告)号：US20180362136A1

公开(公告)日：2018-12-20

申请号：US15627968

申请日：2017-06-20

Applicant: Gulfstream Aerospace Corporation

Inventor： Gregg Wozniak

IPC: B64C1/14

CPC classification number: B64C1/1453 ,  B60R15/04 ,  B61D35/007 ,  B64D1/16 ,  B64D11/02

Abstract: A drainage system for an aircraft is taught herein. The drainage system includes a drain tube defining an orifice. The drainage system further includes a cover movable between a first cover position and a second cover position. The cover is configured to overlay the orifice when the cover is in the first cover position. The cover is configured to expose the orifice when the cover is in the second cover position. The cover is configured to move between the first cover position and the second cover position in the presence of air pressure.

公开(公告)号：US20180265210A1

公开(公告)日：2018-09-20

申请号：US15463879

申请日：2017-03-20

Applicant: Bell Helicopter Textron Inc.

Inventor： Joseph Daniel Leachman

IPC: B64D37/00 ,  B64C27/64 ,  F16L55/07

CPC classification number: B64D37/005 ,  B64C1/1453 ,  B64C27/605 ,  B64C27/64 ,  B64C27/82 ,  F02M25/0872 ,  F02M37/0052 ,  F02M2025/0863 ,  F16L23/167 ,  F16L55/07 ,  F16L55/168 ,  F16L2201/30 ,  Y10T137/5762

Abstract: An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.

公开(公告)号：US20160376931A1

公开(公告)日：2016-12-29

申请号：US15039003

申请日：2014-11-25

Applicant: SNECMA

Inventor： Alexandre LEON ,  Julien PAVILLET ,  Julien SAYN-URPAR

IPC: F01D25/32 ,  F02C7/30 ,  G01L7/00 ,  B64D29/00

CPC classification number: B64C1/1453 ,  B64D29/00 ,  F01D25/32 ,  F02C7/30 ,  F05D2220/323 ,  G01L7/00 ,  Y10T137/2012

Abstract: Drained fluid evacuation stub (16) for a propulsion assembly (10), comprising a drained fluid storage cavity and at least one orifice (32) for evacuation of the fluids contained in said cavity, characterized in that it comprises means (36, 38) for detecting a pressure difference with the exterior of the stub and a component for purging the cavity which is movable between a first closed position of the evacuation orifice and a second release position of the orifice, the component being configured to move from the first to the second position when the pressure difference is greater than or equal to a predetermined value.

Abstract translation: 用于推进组件（10）的排放流体排出短管（16），包括排出的流体储存空腔​​和用于抽出包含在所述空腔中的流体的至少一个孔口（32），其特征在于，其包括装置（36,38） 用于检测与所述短截线外部的压差和用于清除所述空腔的部件，所述部件可在所述排气口的第一关闭位置和所述孔的第二释放位置之间移动，所述部件被配置为从所述第一到第 当压力差大于或等于预定值时的第二位置。

公开(公告)号：US09452833B2

公开(公告)日：2016-09-27

申请号：US14336085

申请日：2014-07-21

Applicant: Airbus Operations S.L.

Inventor： Carlos Casado Montero ,  Jose Angel Hernanz Manrique ,  Jose Grana Otero ,  Ignacio Esteban Parra Fabian ,  Miguel Angel Gallego Lorenzo

IPC: B64D1/00 ,  B64D1/16 ,  B64C1/14

CPC classification number: B64D1/16 ,  B64C1/1453

Abstract: A drainage mast able to drain effectively the liquid contained in the compartment of an aircraft when the pressure within the compartment is lower than the outside pressure without using any pressure control active device and without causing any significant perturbation to the aerodynamic behavior of the aircraft. The drainage mast is configured with a cross section area decreasing from its entry section to the compartment to its outlet section and is disposed at an acute angle α relative to the compartment in the airflow direction. The entry and outlet sections have two perpendicular symmetry axes of different length, the entry section is arranged with its longer axis of symmetry substantially parallel to the airflow direction. The drainage mast has a symmetrical configuration with respect to a plane substantially perpendicular to the fuselage envelope passing through the longer axis of symmetry of the entry section.

Abstract translation: 当排气室内的压力低于外部压力时，不使用任何压力控制有源装置并且不会对飞行器的空气动力学行为产生任何明显的扰动，排水桅杆能够有效地排出飞机内部所含的液体。 排水桅杆构造有从入口部分到隔室到其出口部分的横截面面积，并且相对于隔室在气流方向上以锐角α设置。 入口和出口部分具有不同长度的两个垂直对称轴，入口部分布置成具有与气流方向基本平行的较长对称轴。 排水桅杆相对于基本上垂直于通过入口部分的较长对称轴的机身外壳的平面具有对称的构造。

公开(公告)号：US09358410B2

公开(公告)日：2016-06-07

申请号：US14594532

申请日：2015-01-12

Applicant: AIRBUS HELICOPTERS

Inventor： Thibault Jullie ,  Franck Morente

IPC: B64D45/00 ,  A62C4/00 ,  A62C3/08 ,  B64C1/14 ,  B64D29/00

CPC classification number: A62C4/00 ,  A62C3/08 ,  B64C1/1453 ,  B64D29/00 ,  B64D2045/009

Abstract: An installation for draining liquid away from an aircraft engine compartment. Said drainage installation comprises a collector for collecting said liquid and provided with an opening putting the collector into fluid flow communication with an upstream inlet of a drainage line that is open to the outside via a downstream outlet. The drainage line includes an obstacle to the flow of the liquid that allows the liquid to flow towards the downstream outlet of the drainage line when there is a predefined quantity of liquid retained by said obstacle. The opening of the collector is provided with a firebreak grille arranged as a cap extending in elevation over the opening and including a plurality of orifices distributed at the periphery of the firebreak grille going from its base towards its top.

Abstract translation: 将液体从飞机发动机舱排出的装置。 所述排水装置包括收集器，用于收集所述液体并设置有开口，该收集器将收集器与经由下游出口向外开放的排水管的上游入口流体流动连通。 当存在由所述障碍物保留的预定量的液体时，排水管线包括允许液体朝向排水管线的下游出口流动的液体流动的障碍物。 收集器的开口设置有烟火格栅，其布置成在开口上方高度延伸的盖，并且包括分布在从其底部朝向其顶部的防火格栅的周边处的多个孔。

公开(公告)号：US08764867B2

公开(公告)日：2014-07-01

申请号：US13572671

申请日：2012-08-12

Applicant: Gregory Ray Brannon

Inventor： Gregory Ray Brannon

IPC: F02C7/06

CPC classification number: B64D33/00 ,  B64C1/1453

Abstract: An oil flow management system reduces the amount of oil directed from an aircraft engine to the environment outside of the aircraft, even when the aircraft is in inverted flight. This decreases the amount of oil that becomes attached to exterior surfaces of the aircraft fuselage. A gaseous mixture including air and oil is directed from the aircraft engine to a separator, which separate the mixture into a gaseous component and an oil component. The oil component is directed from the separator to a reservoir via a unidirectional valve. When in a first orientation, the unidirectional valve allows oil to flow from the separator to the reservoir. However, when in a second orientation, the unidirectional valve blocks oil from flowing from the reservoir to the separator.

Abstract translation: 油流管理系统将飞机引擎的油量减少到飞机外部的环境，即使飞机处于倒飞行驶状态。 这减少了附着在飞机机身外表面上的油量。 包括空气和油的气体混合物从飞机发动机引导到分离器，其将混合物分离成气态组分和油组分。 油分量通过单向阀从分离器引导到储存器。 当处于第一方向时，单向阀允许油从分离器流到储存器。 然而，当处于第二方向时，单向阀阻止油从贮存器流到分离器。

公开(公告)号：US20140026583A1

公开(公告)日：2014-01-30

申请号：US13604086

申请日：2012-09-05

Applicant: Ian C. D. CARE ,  John D. BLACK

Inventor： Ian C. D. CARE ,  John D. BLACK

IPC: F01D25/18 ,  G01N21/84 ,  H05B6/80

CPC classification number: F01D25/18 ,  B64C1/1453 ,  B64D33/04 ,  F02C7/06 ,  F05D2250/52 ,  F05D2260/605 ,  F05D2260/609 ,  F05D2260/80 ,  F05D2260/98 ,  F05D2270/804 ,  G01N21/71 ,  G01N21/84 ,  G01N21/94 ,  H05B6/80

Abstract: A fluid management apparatus and method, the apparatus including: a fluid conduit for the passage of a dispersion containing particulate matter; a laser arranged to provide laser light inside the fluid conduit; wherein, in use, the laser light heats the particulate matter sufficiently to generate incandescence; one or more sensors for detecting the incandescence of the particulate matter so as to determine a characteristic of the dispersion; and an electromagnetic wave generator operable to provide electromagnetic waves inside the fluid conduit at a position downstream of the laser light so as to vaporise at least a portion of the dispersion.

Abstract translation: 一种流体管理装置和方法，所述装置包括：用于通过含有颗粒物质的分散体的流体导管; 设置成在流体导管内提供激光的激光器; 其中，在使用中，所述激光将所述颗粒物质充分加热以产生白炽; 一个或多个传感器，用于检测颗粒物质的白炽，以确定分散体的特性; 以及电磁波发生器，其可操作以在所述激光下游的位置处在所述流体导管内部提供电磁波，以使所述分散体的至少一部分蒸发。

公开(公告)号：US20110103941A1

公开(公告)日：2011-05-05

申请号：US12883400

申请日：2010-09-16

Applicant: Christopher T. J. SHEAF ,  Zahid M. HUSSAIN

Inventor： Christopher T. J. SHEAF ,  Zahid M. HUSSAIN

IPC: F01D25/24

CPC classification number: B64C1/1453 ,  B64C7/02

Abstract: A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is at least one clean air outlet bounding the exhaust port and arranged to expel, in use, a vortical flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.

Abstract translation: 一种燃气涡轮发动机，其包括机舱和通气管。 通气管道提供机舱内的发动机的部件与机舱的外部之间的连通，并且在机舱的外表面上的排气口处打开。 至少一个清洁空气出口限定排气口，并布置成在使用中排出干净空气的涡旋流，以在机舱的外表面与从排气口排出的通气空气流之间形成空气动力学屏障。

公开(公告)号：US20100293964A1

公开(公告)日：2010-11-25

申请号：US12767989

申请日：2010-04-27

Applicant: Christopher T.J. SHEAF ,  Zahid M. Hussain

Inventor： Christopher T.J. SHEAF ,  Zahid M. Hussain

IPC: F02C7/06 ,  F16N29/00

CPC classification number: B64C1/1453 ,  B64C7/02 ,  F01D25/18 ,  F02C7/00 ,  F05D2240/14

Abstract: A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.

Abstract translation: 一种燃气涡轮发动机，其包括机舱和通气管。 通气管道提供机舱内的发动机的部件与机舱的外部之间的连通，并且在机舱的外表面上的排气口处打开。 存在位于排气口下游的清洁的空气出口槽，并布置成在使用中排出清洁空气的片材流，以在机舱的外表面与从排气口排出的呼吸空气流之间形成空气动力学屏障 。

公开(公告)号：US07677500B2

公开(公告)日：2010-03-16

申请号：US11817885

申请日：2006-03-10

Applicant: Robert Redecker

Inventor： Robert Redecker

IPC: B64D1/00

CPC classification number: B64C1/1453

Abstract: An aircraft structural element having a cavity. The structural element has an opening in a wall of the cavity through which moisture located in the cavity can escape into the surroundings, wherein a drainage element for sealing the opening in the wall of the cavity is provided in the opening. In order that the structural element can be produced with a low expenditure on components and assembly equipment, the drainage element comprises a hollow cylinder which connects the cavity of the structural element to the surroundings, which is provided with an external thread having a predefined external diameter, and a head at one end which has a predefined diameter, wherein the external diameter of the thread is smaller than the head diameter.

Abstract translation: 具有空腔的飞机结构元件。 结构元件在空腔的壁中具有开口，通过该开口，位于空腔中的水分可以通过该开口逸出到周围，其中在开口中设置有用于密封空腔壁中的开口的排水元件。 为了在组件和组装设备上以低成本制造结构元件，排水元件包括将结构元件的空腔连接到周围的中空圆筒，该中空圆筒具有预定外径的外螺纹 ，并且具有预定直径的一端的头部，其中所述螺纹的外径小于所述头部直径。