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公开(公告)号：US12025266B1
公开(公告)日：2024-07-02
申请号：US18319179
申请日：2023-05-17
CPC分类号： F16N21/00 , F16N33/00 , F16N2210/08 , F16N2210/12
摘要： A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube having an interior surface defining a flow passage for the hydrocarbon fluid. The tube is formed of (i) a shape memory alloy or (ii) a first metal and a second metal having a coefficient of thermal expansion different from the first metal. At least one of a plurality of recesses and a plurality of protrusions are formed on the interior surface of the tube within the flow passage. The tube is characterized by a conduit contortion factor (CCF) from two tenths degrees Fahrenheit (0.2° F.) to fourteen degrees Fahrenheit (14° F.), and the conduit contortion factor (CCF) is one of an elastic conduit contortion factor (CCFE) and thermal expansion conduit contortion factor (CCFTE).
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公开(公告)号：US20190003642A1
公开(公告)日：2019-01-03
申请号：US16100768
申请日：2018-08-10
CPC分类号： F16N29/02 , B63H3/08 , B64C11/00 , B64C11/303 , B64C11/40 , F16N2210/08 , F16N2230/00 , F16N2250/04 , F16N2250/08 , F16N2270/20 , G01F15/003
摘要： There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.
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公开(公告)号：US10072796B2
公开(公告)日：2018-09-11
申请号：US15209215
申请日：2016-07-13
CPC分类号： F16N29/02 , B63H3/08 , B64C11/00 , B64C11/303 , B64C11/40 , F16N2210/08 , F16N2230/00 , F16N2250/04 , F16N2250/08 , F16N2270/20 , G01F15/003
摘要： There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.
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公开(公告)号：US20170175875A1
公开(公告)日：2017-06-22
申请号：US15372634
申请日：2016-12-08
申请人： AIRBUS HELICOPTERS
CPC分类号： F16H57/0442 , F01D25/18 , F01D25/20 , F05D2260/98 , F16H57/02 , F16H57/0435 , F16H57/0436 , F16H57/045 , F16H57/0456 , F16N7/02 , F16N21/00 , F16N25/00 , F16N29/02 , F16N39/04 , F16N2200/12 , F16N2210/08 , F16N2260/24 , F16N2270/56 , F16N2280/00 , Y02T50/671
摘要： An emergency lubrication device of simplified architecture for a mechanical system. The emergency lubrication device has a tank, trigger means, at least one pipe, and at least one distribution means. The tank contains a lubrication liquid and it is arranged inside the mechanical system and above the pipes and the distribution means. Each distribution means includes at least one constriction means for limiting the flow rate of the lubrication liquid. The lubrication liquid is heated by the mechanical system, and the viscosity of the lubrication liquid decreases so that the flow rate of the lubrication liquid through each distribution means is substantially equal to or greater than a minimum flow rate so long as the tank contains the lubrication liquid.
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公开(公告)号：US20170067599A1
公开(公告)日：2017-03-09
申请号：US15269626
申请日：2016-09-19
发明人： Thomas Gray Wilson
CPC分类号： F16N31/006 , B64C27/04 , B64D27/00 , B64D47/00 , F16N31/002 , F16N2210/08 , Y10T29/49826
摘要： A drip pan apparatus for use in a helicopter includes a drip pan and a frame having a plurality of frame sides and a plurality of frame corners that define an inwardly-facing peripheral surface. A first frame angle is formed between a first inwardly-facing surface and a second inwardly-facing surface. The first frame angle is an acute angle. The drip pan has an outwardly-facing peripheral surface. The outwardly-facing peripheral surface defines a plurality of sides, including a first side and a second side, to cooperate with the inwardly-facing peripheral surface of the frame. A first angle is formed between the first side and the second side. The first angle is an acute angle. A method of installing a drip pan includes modifying at least a portion of a skirt on the helicopter and then securing the frame to one or both of the modified skirt and the helicopter structure.
摘要翻译： 用于直升机的滴水盘装置包括滴水盘和具有多个框架侧面的框架和限定向内的周向表面的多个框架拐角。 在第一向内的表面和第二向内的表面之间形成第一框架角度。 第一帧角度是锐角。 滴水盘具有向外的外围表面。 面向外的外围表面限定了包括第一侧和第二侧的多个侧面，以与框架的向内的外周表面配合。 在第一侧和第二侧之间形成第一角度。 第一个角度是一个锐角。 安装滴水盘的方法包括修改直升机上的裙部的至少一部分，然后将框架固定到修改的裙部和直升机结构中的一个或两个上。
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公开(公告)号：US08459413B2
公开(公告)日：2013-06-11
申请号：US12522268
申请日：2007-01-19
申请人： Yuriy Gmirya , Mikhail Gelfand
发明人： Yuriy Gmirya , Mikhail Gelfand
IPC分类号： F01M1/20
CPC分类号： F16N17/00 , B64C27/12 , F01M5/00 , F01M5/002 , F01M11/10 , F01M13/0011 , F01M2011/0045 , F16N39/02 , F16N2210/08
摘要： A lubrication system includes an external pump system which pumps air out of the housing and develop negative pressure therein in response to a loss of lubrication condition. The negative pressure operates as an air lock to minimize or prevent lubricating oil loss from the housing while an internal lubrication system continues to distribute lubricating oil—which although now increasing in temperature—still operates to lubricate the gearbox components. For further ballistic tolerance, the housing is a compound housing that reduces or closes the penetration and further minimizes lubricating oil and negative pressure loss. The housing may be still further hardened by an armor layer.
摘要翻译： 润滑系统包括外部泵系统，其将空气从壳体中抽出并且响应于润滑状况的损失而在其中产生负压。 当内部润滑系统继续分配润滑油时，负压作为气锁来最小化或防止润滑油损失，尽管现在温度上升仍然运行以润滑齿轮箱部件。 为了进一步的防弹性能，外壳是复合外壳，可减少或关闭穿透，进一步减少润滑油和负压损失。 壳体可以通过铠装层进一步硬化。
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公开(公告)号：US20100025159A1
公开(公告)日：2010-02-04
申请号：US12522268
申请日：2007-01-19
申请人： Yuriy Gmirya , Mikhail Gelfand
发明人： Yuriy Gmirya , Mikhail Gelfand
CPC分类号： F16N17/00 , B64C27/12 , F01M5/00 , F01M5/002 , F01M11/10 , F01M13/0011 , F01M2011/0045 , F16N39/02 , F16N2210/08
摘要： A lubrication system includes an external pump system which pumps air out of the housing and develop negative pressure therein in response to a loss of lubrication condition. The negative pressure operates as an air lock to minimize or prevent lubricating oil loss from the housing while an internal lubrication system continues to distribute lubricating oil—which although now increasing in temperature—still operates to lubricate the gearbox components. For further ballistic tolerance, the housing is a compound housing that reduces or closes the penetration and further minimizes lubricating oil and negative pressure loss. The housing may be still further hardened by an armor layer.
摘要翻译： 润滑系统包括外部泵系统，其将空气从壳体中抽出并且响应于润滑状况的损失而在其中产生负压。 当内部润滑系统继续分配润滑油时，负压作为气锁来最小化或防止润滑油损失，尽管现在温度上升仍然运行以润滑齿轮箱部件。 为了进一步的防弹性能，外壳是复合外壳，可减少或关闭穿透，进一步减少润滑油和负压损失。 壳体可以通过铠装层进一步硬化。
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公开(公告)号：US20230152297A1
公开(公告)日：2023-05-18
申请号：US17525446
申请日：2021-11-12
发明人： Guy RIVERIN
CPC分类号： G01N33/2858 , F01M1/10 , F01M11/10 , F16N29/00 , G01N15/0656 , G01N33/2888 , F01M2001/1042 , F01M2011/144 , F01M2250/60 , F16N2200/04 , F16N2210/08
摘要： Magnetic chip detectors and associated for detecting metallic chips in engine fluid of an engine are provided. A magnetic chip detector includes first and second magnetic chip capture zones. The first magnetic chip capture zone includes a first electrically conductive terminal spaced apart from a second electrically conductive terminal to define a first chip-receiving gap therebetween. The second magnetic chip capture zone includes a third electrically conductive terminal and either the second electrically conductive terminal or a fourth electrically conductive terminal to define a second chip-receiving gap therebetween. The magnetic chip detector includes an electric circuit including both the first chip-receiving gap and the second chip-receiving gap. The electric circuit provides an output indicative of a chip detection by one or both of the first magnetic chip capture zone and the second magnetic capture zone.
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公开(公告)号：US20180128128A1
公开(公告)日：2018-05-10
申请号：US15727796
申请日：2017-10-09
申请人： Florian Cleyet , Stephane Bougelet
发明人： Florian Cleyet , Stephane Bougelet
CPC分类号： F01D25/28 , B22F3/1055 , B22F5/009 , B22F2301/15 , B22F2301/205 , B33Y80/00 , F01D25/18 , F01M2011/0091 , F02C7/06 , F16N19/00 , F16N2210/08
摘要： The invention relates to a turbojet engine oil tank (30). The tank (30) comprises a main chamber and an envelope (34) delimiting the main chamber, and a fixing portion (44) for example with fixing flanges (46) and a branch (48). The envelope (34) features in particular an envelope part (34) relative to which the fixing portion (44) projects. The envelope part (34) and the fixing portion (44) are produced by layered additive fabrication so as to be in one piece. The invention also relates to a method of fabricating an oil tank (30).
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公开(公告)号：US09897254B2
公开(公告)日：2018-02-20
申请号：US15269626
申请日：2016-09-19
发明人： Thomas Gray Wilson
CPC分类号： F16N31/006 , B64C27/04 , B64D27/00 , B64D47/00 , F16N31/002 , F16N2210/08 , Y10T29/49826
摘要： A drip pan apparatus for use in a helicopter includes a drip pan and a frame having a plurality of frame sides and a plurality of frame corners that define an inwardly-facing peripheral surface. A first frame angle is formed between a first inwardly-facing surface and a second inwardly-facing surface. The first frame angle is an acute angle. The drip pan has an outwardly-facing peripheral surface. The outwardly-facing peripheral surface defines a plurality of sides, including a first side and a second side, to cooperate with the inwardly-facing peripheral surface of the frame. A first angle is formed between the first side and the second side. The first angle is an acute angle. A method of installing a drip pan includes modifying at least a portion of a skirt on the helicopter and then securing the frame to one or both of the modified skirt and the helicopter structure.
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