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公开(公告)号：US11643968B2
公开(公告)日：2023-05-09
申请号：US17313267
申请日：2021-05-06
CPC分类号： F02C7/057 , B64D33/02 , F02C7/055 , B64D2033/0253 , F05D2220/329 , F05D2240/12
摘要： An air intake system for an aircraft, which is switchable between a performance mode and a filtered mode, includes a duct forming filtered air inlet slits. The air intake system also includes interconnected gills adjacent to the filtered air inlet slits. The gills are movable between various gill positions including a closed position substantially covering the filtered air inlet slits and an open position substantially exposing the filtered air inlet slits. The air intake system also includes an actuator configured to move the gills into the closed position in the performance mode and the open position in the filtered mode.
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公开(公告)号：US09656760B2
公开(公告)日：2017-05-23
申请号：US14074265
申请日：2013-11-07
CPC分类号： B64D33/02 , B64D2033/0253 , F02C7/042 , Y10T137/0536
摘要： A variable area engine inlet of a helicopter is provided and includes first inlet portions disposed to face one another in opposite directions and at a distance from one another and second inlet portions extending between the first inlet portions and being disposed to face one another in opposite directions and at a distance from one another. The first and second inlet portions define a capture area and at least one or both of the first and second inlet portions include a movable portion disposed to occupy and move between first and second positions. The first position is associated with a non-constricted condition of the capture area and the second position is associated with a constricted condition of the capture area.
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公开(公告)号：US20150344158A1
公开(公告)日：2015-12-03
申请号：US14763299
申请日：2014-01-17
CPC分类号： B64D33/02 , B64D2033/0253 , B64D2033/026 , B64G1/14 , B64G1/40 , F02C7/042 , F02C7/05
摘要： According to the invention, said space aircraft comprises, at the front of each of the air inlets of the turbo engines, a mobile flap that can move, in both directions, between a first position for which said flap opens said air inlet and a second position for which said flap prevents air from entering said air inlet.
摘要翻译： 根据本发明，所述太空飞行器在涡轮发动机的每个空气入口的前部包括可移动的翼片，其能够在两个方向上在所述翼片打开所述空气入口的第一位置和第二位置之间移动， 所述挡板防止空气进入所述空气入口的位置。
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公开(公告)号：US20150090844A1
公开(公告)日：2015-04-02
申请号：US14496378
申请日：2014-09-25
发明人： Ralf BRAEUTIGAM
CPC分类号： B64D33/02 , B64C27/04 , B64D27/02 , B64D2033/0253
摘要： A helicopter with a fuselage, at least two engines substantially inside said fuselage, an air intake for each of said two engines and at least two separate lateral air inlet ports for said at least two engines in said fuselage. Said separate lateral air inlet ports being arranged on sides opposed to each other relative to an essentially vertical midplane of said fuselage and oriented with their respective cross section substantially parallel to a forward flight direction of the helicopter. At least one frontal air inlet port with a forward portion is provided separate from said lateral air inlet ports, said frontal air inlet port being located on a gear cowling of the fuselage oriented with its cross section substantially perpendicular to the forward flight direction of the helicopter.
摘要翻译： 具有机身的直升机，基本上位于所述机身内的至少两个发动机，所述两个发动机中的每一个的进气口和用于所述机身中的所述至少两个发动机的至少两个分开的侧向进气口。 所述单独的横向进气口相对于所述机身的基本上垂直的中平面相对地设置，并且其各自横截面基本上平行于直升机的向前飞行方向定向。 具有前部的至少一个前部空气入口与所述侧向空气入口分开设置，所述正面空气入口位于机身的齿轮罩上，其定向成其横截面基本上垂直于直升机的前方飞行方向 。
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5.发明申请公开(公告)号：US20180312269A1
公开(公告)日：2018-11-01
申请号：US15962179
申请日：2018-04-25
申请人： AIRBUS HELICOPTERS
发明人： Damien DESVIGNE
CPC分类号： B64D33/02 , B64C27/001 , B64C27/04 , B64D2033/0253 , B64D2033/0293
摘要： An aircraft having a static air inlet system. The static air inlet system comprises a static air intake, the static air intake having a through opening formed in a top structural assembly, the through opening forming an interface between a medium and an inside space of the top structural assembly. The static air inlet system has at least one separator subdividing the through opening into at least two distinct slots, the separator comprising a first portion extended by a second portion, the first portion extending inside the inside space and the second portion extending outside the inside space.
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公开(公告)号：US20180118362A1
公开(公告)日：2018-05-03
申请号：US15459943
申请日：2017-03-15
CPC分类号： B64D33/02 , B64D2033/0253 , F02C7/042 , Y10T137/0536
摘要： A variable area engine inlet of a helicopter is provided and includes first inlet portions disposed to face one another in opposite directions and at a distance from one another and second inlet portions extending between the first inlet portions and being disposed to face one another in opposite directions and at a distance from one another. The first and second inlet portions define a capture area and at least one or both of the first and second inlet portions include a movable portion disposed to occupy and move between first and second positions. The first position is associated with a non-constricted condition of the capture area and the second position is associated with a constricted condition of the capture area.
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公开(公告)号：US09731831B2
公开(公告)日：2017-08-15
申请号：US14849093
申请日：2015-09-09
发明人： Sebastian Mores , Frank Loeser , Stefan Probst , Michael Matt
CPC分类号： B64D33/02 , B64C27/04 , B64D2033/022 , B64D2033/0253 , F02C7/052 , F02C7/055 , F05D2220/329 , F05D2260/607 , Y02T50/675
摘要： An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation.
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公开(公告)号：US20160075439A1
公开(公告)日：2016-03-17
申请号：US14849093
申请日：2015-09-09
发明人： Sebastian MORES , Frank LOSER , Stefan PROBST , Michael MATT
CPC分类号： B64D33/02 , B64C27/04 , B64D2033/022 , B64D2033/0253 , F02C7/052 , F02C7/055 , F05D2220/329 , F05D2260/607 , Y02T50/675
摘要： An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation.
摘要翻译： 一种具有机身的飞机，其容纳至少一个空气呼吸推进发动机，所述机身具有在所述至少一个呼吸推进发动机的区域中确定的最大机身宽度，并且包括至少一个前机身罩和至少一个后机身罩 其至少部分地覆盖所述至少一个呼吸推进发动机，所述至少一个前机身和后机身整流罩在横向于所述至少一个空气呼吸推进发动机的纵向轴线的方向上彼此间隔开 预定的整流罩偏移以限定动态空气入口，通过所述动态空气入口在运行中将进气流供应到所述至少一个空气呼吸推进发动机。
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公开(公告)号：US09067679B2
公开(公告)日：2015-06-30
申请号：US13730233
申请日：2012-12-28
发明人： Michael J. Scimone
CPC分类号： B64D15/00 , B64C27/28 , B64D15/12 , B64D33/02 , B64D2033/022 , B64D2033/0233 , B64D2033/0246 , B64D2033/0253 , B64D2033/0293 , F02C7/047 , F02C7/055 , Y02T50/672
摘要： An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an air intake. At least a portion of the air intake generally faces the forward direction for receiving intake air during forward flight. A filter assembly is mounted adjacent the air intake and disposed to impinge air and block objects from passing therethrough. A heated screen includes a heater and is mounted adjacent the air intake and upstream of the engine such that ice entering the air intake contacts the heated screen before entering the engine. A power source is provided to supply power to the heater.
摘要翻译： 飞机包括机身和安装在机身两侧的机翼，用于持续向前飞行。 发动机安装在机身或至少一个机翼上并且包括进气口。 进气口的至少一部分通常面向向前的方向，用于在向前飞行期间接收进气。 过滤器组件安装在进气口附近并设置成撞击空气并阻止物体从其中通过。 加热屏幕包括加热器并且安装在进气口和发动机上游附近，使得进入进气口的冰在进入发动机之前接触加热的筛网。 提供电源以向加热器供电。
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公开(公告)号：US20240026844A1
公开(公告)日：2024-01-25
申请号：US18354008
申请日：2023-07-18
申请人： BMC S.R.L.
发明人： Gaetano BERGAMI
CPC分类号： F02M35/10262 , B64D33/02 , B64D2033/0253
摘要： An air intake unit for an engine of a vehicle includes a housing, a bypass air intake, a shutter element, and actuator. A plenum is defined inside the housing which can be connected to the engine. Air coming from the outside needed for the operation of the engine can be sucked into the plenum through the bypass air intake. The shutter element is coupled to the bypass air intake and is mounted to move between a closed position, in which the shutter element closes the bypass air intake, and an open position, in which the shutter element leaves the passage through the bypass air intake free. The actuator is configured to move the shutter element between the closed position and the open position. The actuator has a spring configured to generate, by expanding, an opening movement moving the shutter element from the closed position to the open position.
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