专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08881870B2 Recirculation valve in an aircraft engine 有权
标题翻译：飞机发动机中的再循环阀
公开(公告)号：US08881870B2
公开(公告)日：2014-11-11
申请号：US12335011
申请日：2008-12-15
申请人： Albert Cornet , Nicolas Raimarckers , Bernard Simeon
发明人： Albert Cornet , Nicolas Raimarckers , Bernard Simeon
IPC分类号： F01D25/18 , F01D25/20
CPC分类号： F01D25/20 , Y02T50/671 , Y10T137/7837
摘要： The present invention relates to an installation for lubricating and/or cooling in an aircraft engine comprising an oil tank (3), a main feed pipe (6) feeding a main pump (1) supplying a flow in a discharge line from the main pump (7) to one or several systems (2) to be lubricated and/or cooled, wherein the installation comprises a feed pipe for an auxiliary pump (8) fitted in parallel onto the main pipe (6) and connected to an auxiliary feed pump (1A), the latter supplying a flow in a discharge line from the auxiliary pump (8A) connected by a three-way circuit on the one hand to a non-return valve (4A) directed towards the main discharge line (7), and on the other hand to a hydraulically-operated (9) recirculation valve (5), in order to divert the flow from the auxiliary feed pump (1A) into a return line (8B) directly towards the tank (3).
摘要翻译：本发明涉及一种用于在飞机发动机中润滑和/或冷却的装置，其包括油箱（3），主供给管（6），主供给管（6）供给主泵（1），主泵（1）从主泵（7）连接到待润滑和/或冷却的一个或多个系统（2），其中所述设备包括用于辅助泵（8）的进料管，所述辅助泵（8）平行安装在所述主管（6）上并连接到辅助进料泵（1A），后者一方面将辅助泵（8A）的排出管路中的流路连接到一个指向主排出管线（7）的止回阀（4A）上，另一方面是液压操作（9）再循环阀（5），以便将来自辅助进料泵（1A）的流量直接转向储罐（3）的返回管线（8B）。

2. 发明申请

US20090165995A1 AIR-OIL HEAT EXCHANGER PLACED AT THE LOCATION OF THE AIR SEPARATOR NOSE OF A TURBOJET, AND A TURBOJET INCLUDING SUCH AN AIR-OIL HEAT EXCHANGER 审中-公开
标题翻译：空气分离器上的空气热交换器设置在涡轮机的空气分离器的位置，以及包括这种空气热交换器的涡轮机
公开(公告)号：US20090165995A1
公开(公告)日：2009-07-02
申请号：US12342206
申请日：2008-12-23
申请人： Denis Bajusz , Albert Cornet , Jerome Friedel , Nicolas Raimarckers
发明人： Denis Bajusz , Albert Cornet , Jerome Friedel , Nicolas Raimarckers
IPC分类号： F01N5/02 , F02C7/14 , F02C7/12 , F02C1/00
CPC分类号： F01D25/02 , F01D25/12 , F01D25/18 , F02C7/047 , F02C7/14 , F02K3/06 , F28D1/03 , F28D2021/0089 , F28F1/34 , F28F3/02 , F28F3/12 , Y02T50/671 , Y02T50/675
摘要： The invention relates to an air-oil heat exchanger located at the inner shroud of the secondary duct of a turbojet. In characteristic manner, it comprises an oil circuit placed inside the separator nose and fins placed outside the top wall of the separator nose, between the leading edge of the separator nose and the outlet guide vanes.
摘要翻译：本发明涉及一种位于涡轮喷气发动机二次管道内护罩处的空气 - 油热交换器。以特征方式，它包括放置在分离器鼻部内部的油回路和位于分离器鼻部的顶壁之外的分离器鼻部的前缘和出口导叶之间的翅片。

3. 发明申请

US20100162889A1 Combined Pumping And Separating Machine For The Oil Circuit Of A Turbojet 有权
标题翻译：涡轮喷油器油路组合抽油机
公开(公告)号：US20100162889A1
公开(公告)日：2010-07-01
申请号：US12643388
申请日：2009-12-21
申请人： Albert Cornet , Nicolas Raimarckers
发明人： Albert Cornet , Nicolas Raimarckers
IPC分类号： B01D19/02
CPC分类号： F04D7/045 , B01D19/0026 , B01D19/0052 , B01D19/0063 , F04D31/00
摘要： The present invention relates to a combined machine for pumping and separating into two distinct and purified phases a two-phase liquid/gas mixture or fluid, preferably oil/air, entering the machine, comprising means for the suction, pumping and partial separation of the two-phase fluid, means for drying and extracting the separated gas and means for degassing and forcing back the separated liquid, comprising at least three physically separated stages (A,B,C) intended to be activated by a means that is internal or external to the machine, and built into a single casing: a first stage (A), equipped with an intake for the two-phase fluid, in which the two-phase fluid is sucked, pumped and partially separated into two distinct phases, one phase being mainly liquid and the other being mainly gaseous; a second stage (B), comprising two zones: a first zone in which the mainly liquid phase extracted from the first stage (A) is degassed, and a second zone in which the mainly gaseous phase extracted from the first stage (A) is dried, equipped with a first outlet for the dried gas; a third stage (C), in which the degassed liquid is forced back and pressurised, equipped with a second outlet for the degassed liquid.
摘要翻译：本发明涉及一种用于泵送和分离成两个不同和纯化阶段的组合机器，两相液体/气体混合物或流体，优选是进入机器的油/空气，包括用于吸入，泵送和部分分离的装置两相流体，用于干燥和提取分离出的气体的装置和用于对分离的液体进行脱气和强制回收的装置，包括至少三个物理上分离的级（A，B，C），其通过内部或外部的方式被激活并装入一个单一的外壳中：第一阶段（A），配备两相流体的进气口，其中两相流体被吸入，泵送并部分分离成两个不同的相，一相主要是液体，另一种主要是气态的; 第二阶段（B），包括两个区域：从第一阶段（A）提取的主要液相的第一区域被脱气，以及从第一阶段（A）提取的主要气相的第二区域是干燥，装有干燥气体的第一出口; 第三阶段（C），其中脱气的液体被强制返回和加压，装备有用于脱气液体的第二出口。

4. 发明申请

US20090159139A1 Recirculation Valve In An Aircraft Engine 有权
标题翻译：飞机发动机中的再循环阀
公开(公告)号：US20090159139A1
公开(公告)日：2009-06-25
申请号：US12335011
申请日：2008-12-15
申请人： Albert Cornet , Nicolas Raimarckers , Bernard Simeon
发明人： Albert Cornet , Nicolas Raimarckers , Bernard Simeon
IPC分类号： F16K15/00
CPC分类号： F01D25/20 , Y02T50/671 , Y10T137/7837
摘要： The present invention relates to an installation for lubricating and/or cooling in an aircraft engine comprising an oil tank (3), a main feed pipe (6) feeding a main pump (1) supplying a flow in a discharge line from the main pump (7) to one or several systems (2) to be lubricated and/or cooled, wherein the installation comprises a feed pipe for an auxiliary pump (8) fitted in parallel onto the main pipe (6) and connected to an auxiliary feed pump (1A), the latter supplying a flow in a discharge line from the auxiliary pump (8A) connected by a three-way circuit on the one hand to a non-return valve (4A) directed towards the main discharge line (7), and on the other hand to a hydraulically-operated (9) recirculation valve (5), in order to divert the flow from the auxiliary feed pump (1A) into a return line (8B) directly towards the tank (3).
摘要翻译：本发明涉及一种用于在飞机发动机中润滑和/或冷却的装置，其包括油箱（3），主供给管（6），主供给管（6）供给主泵（1），主泵（1）从主泵（7）连接到待润滑和/或冷却的一个或多个系统（2），其中所述设备包括用于辅助泵（8）的进料管，所述辅助泵（8）平行安装在所述主管（6）上并连接到辅助进料泵（1A），后者一方面将辅助泵（8A）的排出管路中的流路连接到一个指向主排出管线（7）的止回阀（4A）上，另一方面是液压操作（9）再循环阀（5），以便将来自辅助进料泵（1A）的流量直接转向储罐（3）的返回管线（8B）。

5. 发明申请

US20120251373A1 Gas Flow Separator with a Thermal Bridge De-Icer 有权
标题翻译：带热桥的气流分离器
公开(公告)号：US20120251373A1
公开(公告)日：2012-10-04
申请号：US13429627
申请日：2012-03-26
申请人： Denis Bajusz , Yves Culot , Marc Strengnart , Antoine Stephany , David Depaepe , Albert Cornet , Nicolas Raimarckers , Georges Broers
发明人： Denis Bajusz , Yves Culot , Marc Strengnart , Antoine Stephany , David Depaepe , Albert Cornet , Nicolas Raimarckers , Georges Broers
IPC分类号： F01C1/24 , F16K51/00
CPC分类号： F02C7/047 , F01D25/02 , F05D2260/20 , Y02T50/676 , Y10T137/4245
摘要： The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.
摘要翻译：本发明涉及一种气流分离器，将气流分为主流和次流，特别是用于双转子轴向涡轮机。分离器包括涡轮机的分流器鼻部，并且在待分流的气流中包括大致楔形的前缘。流动分离器还包括金属刀片，其具有S形式的纵向截面并且位于与前缘的后部接触的鼻部中，并且从分离器的前缘延伸到后隔离器的一端前缘，以便与位于与前缘一定距离的热源（例如热交换器）接触。

6. 发明授权

US08676436B2 Method for monitoring the oil system of a turbomachine 有权
标题翻译：用于监测涡轮机油系统的方法
公开(公告)号：US08676436B2
公开(公告)日：2014-03-18
申请号：US13295538
申请日：2011-11-14
申请人： Nicolas Raimarckers , Albert Cornet , Jacques Charlier , Marc Strengnart
发明人： Nicolas Raimarckers , Albert Cornet , Jacques Charlier , Marc Strengnart
IPC分类号： G01M15/09
CPC分类号： F01D21/003 , F01D25/18 , F02C7/06 , F05D2260/80 , F05D2270/11 , F05D2270/44
摘要： A monitoring method that includes calculating the autonomy of a lubrication system of an airplane engine and also providing for the diagnosis and prognosis of a plurality of problems and breakdowns of the engine and of its lubrication system by means of measurements taken by sensors arranged in the lubrication system. The method further comprises the step of calculating the status of the lubrication system at a given moment and calculating its evolution over time in order to determine the remaining lifetime before a breakdown.
摘要翻译：一种监测方法，其包括计算飞机发动机的润滑系统的自主性，并且还通过布置在润滑中的传感器进行的测量提供对发动机及其润滑系统的多个问题和故障的诊断和预测系统。该方法还包括在给定时刻计算润滑系统的状态并计算其随时间变化的步骤，以便确定在击穿之前的剩余寿命。

7. 发明申请

US20120130617A1 METHOD FOR MONITORING THE OIL SYSTEM OF A TURBOMACHINE 有权
标题翻译：用于监测涡轮机油系统的方法
公开(公告)号：US20120130617A1
公开(公告)日：2012-05-24
申请号：US13295538
申请日：2011-11-14
申请人： Nicolas Raimarckers , Albert Cornet , Jacques Charlier , Marc Strengnart
发明人： Nicolas Raimarckers , Albert Cornet , Jacques Charlier , Marc Strengnart
IPC分类号： G01M15/14 , F01D25/18
CPC分类号： F01D21/003 , F01D25/18 , F02C7/06 , F05D2260/80 , F05D2270/11 , F05D2270/44
摘要： The present invention relates to an overall monitoring method allowing to calculate the autonomy of a lubrication system of an airplane engine and also allowing the diagnosis and prognosis of a plurality of problems and breakdowns of the engine and of its lubrication system by means of measurements taken by sensors arranged in said lubrication system, the method comprising the step of calculating the status of the lubrication system at a given moment and calculating its evolution over time in order to determine the remaining lifetime before a breakdown.
摘要翻译：本发明涉及一种允许计算飞机发动机的润滑系统的自主性的整体监测方法，并且还允许通过以下步骤进行的测量来诊断和预测发动机及其润滑系统的多个问题和故障：布置在所述润滑系统中的传感器，所述方法包括以下步骤：在给定时刻计算润滑系统的状态，并计算其随时间的演变，以确定击穿前的剩余寿命。

8. 发明申请

US20100028127A1 TURBINE ENGINE LUBRICATION METHOD AND SYSTEM 审中-公开
标题翻译：涡轮发动机润滑方法与系统
公开(公告)号：US20100028127A1
公开(公告)日：2010-02-04
申请号：US12518665
申请日：2007-12-10
申请人： Albert Cornet , Nicolas Raimarckers
发明人： Albert Cornet , Nicolas Raimarckers
IPC分类号： F01D25/20 , F01D25/18
CPC分类号： F01D25/20 , F01D11/04 , F02C7/06 , F05D2240/50 , F16N7/385
摘要： A method and a system for lubricating a turbomachine including an oil tank, an oil feed pump, an oil/air separator, and at least two enclosures closed by air flow rate seals, each including a low outlet and housing shaft-supporting rolling bearings. The method injects oil from the tank into the enclosures by the pump to lubricate the bearings, introduces compressed air at a low flow rate into the enclosures via the seals to pressurize the enclosures, recuperates all of the air and the oil introduced into the enclosures via their low outlet, uses gravity and the pressurization of the enclosures to convey the oil/air mixture as recovered in this way to the oil/air separator, separates the oil and the air of the mixture by the oil/air separator, returns the oil to the tank, and exhausts the air to outside the turbomachine.
摘要翻译：一种用于润滑涡轮机的方法和系统，包括油箱，给油泵，油/空气分离器以及由气流密封封闭的至少两个外壳，每个包括低出口和外壳轴承滚动轴承。该方法通过泵将油从油罐注入外壳以润滑轴承，通过密封件将压缩空气通过密封件以低流量引入外壳中，以对外壳进行加压，使所有的空气和引入外壳的油恢复通过它们的低出口使用重力和外壳的加压，将以这种方式回收的油/空气混合物输送到油/空气分离器，通过油/空气分离器分离混合物的油和空气，返回油并将空气排放到涡轮机外。

9. 发明申请

US20090164056A1 Method For Controlling The Consumption And For Detecting Leaks In The Lubrication System Of A Turbine Engine 有权
标题翻译：用于控制涡轮发动机润滑系统中的消耗和检测泄漏的方法
公开(公告)号：US20090164056A1
公开(公告)日：2009-06-25
申请号：US12334981
申请日：2008-12-15
申请人： Albert Cornet , Nicolas Raimarckers , Denis Bajusz
发明人： Albert Cornet , Nicolas Raimarckers , Denis Bajusz
IPC分类号： G06F17/00 , F01D25/18
CPC分类号： F01D21/003 , F01M1/18
摘要： The present invention relates to a method for calculating the oil consumption and autonomy associated with the lubrication system of an airplane engine during flights, preferably a turbine engine, on the basis of the measurement of the oil level in the tank of said lubrication system, allowing to manage the refills and maintenance and to detect either abnormal consumption or insufficient autonomy, characterised by at least one of the following methods: comparing different engines of the airplane and possibly a reference value, the engines used for said comparison being in more or less identical condition, in order to detect abnormal oil consumption; taking into account one or more interference effects that affect said oil level in the tank, these being linked at least to the thermal expansion in the tank, to the “gulping” and to the attitude and acceleration, in order to deduce the modification to the oil level due to a decrease in the total quantity of oil available as a result of said interference effects; combining both above-mentioned methods.
摘要翻译：本发明涉及一种用于在飞行期间，优选涡轮发动机中，基于对所述润滑系统的油箱中的油位的测量来计算与飞机发动机的润滑系统相关的油耗和自主性的方法，允许管理补充和维护并检测异常消耗或自主性不足，其特征在于以下方法中的至少一种：比较飞机的不同发动机和可能的参考值，用于所述比较的发动机或多或少相同条件，以检测异常油耗; 考虑到影响油箱中油位的一个或多个干扰效应，这些干扰效应至少与油箱的热膨胀相关，与“加油”以及姿态和加速度相关联，以便推断出对由于所述干扰效应，由于可用的总油量的减少而导致的油位; 结合上述两种方法。

10. 发明授权

US08483902B2 Method for controlling the consumption and for detecting leaks in the lubrication system of a turbine engine 有权
标题翻译：用于控制消耗并检测涡轮发动机的润滑系统中的泄漏的方法
公开(公告)号：US08483902B2
公开(公告)日：2013-07-09
申请号：US12334981
申请日：2008-12-15
申请人： Albert Cornet , Nicolas Raimarckers , Denis Bajusz
发明人： Albert Cornet , Nicolas Raimarckers , Denis Bajusz
IPC分类号： G01M15/00
CPC分类号： F01D21/003 , F01M1/18
摘要： The present invention relates to a method for calculating the oil consumption and autonomy associated with the lubrication system of an airplane engine during flights, preferably a turbine engine, on the basis of the measurement of the oil level in the tank of said lubrication system, allowing to manage the refills and maintenance and to detect either abnormal consumption or insufficient autonomy, characterized by at least one of the following methods: comparing different engines of the airplane and possibly a reference value, the engines used for said comparison being in more or less identical condition, in order to detect abnormal oil consumption; taking into account one or more interference effects that affect said oil level in the tank, these being linked at least to the thermal expansion in the tank, to the “gulping” and to the attitude and acceleration, in order to deduce the modification to the oil level due to a decrease in the total quantity of oil available as a result of said interference effects; combining both above-mentioned methods.
摘要翻译：本发明涉及一种用于在飞行期间，优选涡轮发动机中，基于对所述润滑系统的油箱中的油位的测量来计算与飞机发动机的润滑系统相关的油耗和自主性的方法，允许管理补充和维护并检测异常消耗或自主性不足，其特征在于以下方法中的至少一种：比较飞机的不同发动机和可能的参考值，用于所述比较的发动机或多或少相同条件，以检测异常油耗; 考虑到影响油箱中油位的一个或多个干扰效应，这些干扰效应至少与油箱的热膨胀相关，与“加油”以及姿态和加速度相关联，以便推断出对由于所述干扰效应，由于可用的总油量的减少而导致的油位; 结合上述两种方法。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式