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1. 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。

2. 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。

3. 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。

4. 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。

5. 发明申请

US20120168115A1 INTEGRATION OF A SURFACE HEAT-EXCHANGER WITH REGULATED AIR FLOW IN AN AIRPLANE ENGINE 审中-公开
标题翻译：一个表面换热器与一个机动发动机的调节空气流的集成
公开(公告)号：US20120168115A1
公开(公告)日：2012-07-05
申请号：US13334422
申请日：2011-12-22
申请人： Nicolas Raimarckers , Cédric Borbouse , Albert Cornet , Denis Bajusz
发明人： Nicolas Raimarckers , Cédric Borbouse , Albert Cornet , Denis Bajusz
IPC分类号： B60H1/32
CPC分类号： F01D25/02 , F01D25/08 , F01D25/12 , F02C7/047 , F02C7/14 , F02K1/827 , F02K3/06 , Y02T50/672 , Y02T50/675
摘要： The present invention relates to a surface air-cooled oil cooler (1) in an airplane engine comprising at least one first oil circuit (4) and at least a first (2) and a second (3) exchange surface positioned on either side of the first oil circuit (4) and each able to be swept by an air flow, said second exchange surface (3) being positioned in the cavity (9) provided with an air inlet (6) and an air outlet (7), said inlet (6) and/or said outlet (7) comprising covering means (8) that allow to regulate the air supply on the second exchange surface (3).
摘要翻译：本发明涉及一种飞机发动机中的表面空冷油冷却器（1），其包括至少一个第一油回路（4）和至少第一（2）和第二（3）交换表面，位于所述第一油回路（4）并且每个能够被空气流扫过，所述第二交换表面（3）定位在设置有空气入口（6）和空气出口（7）的空腔（9）中，所述空气出口入口（6）和/或所述出口（7）包括允许调节第二交换表面（3）上的空气供应的覆盖装置（8）。

6. 发明申请

US20090159246A1 Heat Exchange System In A Turbomachine 审中-公开
标题翻译：涡轮机热交换系统
公开(公告)号：US20090159246A1
公开(公告)日：2009-06-25
申请号：US12338257
申请日：2008-12-18
申请人： Albert Cornet , Nicolas Raimarckers , Denis Bajusz
发明人： Albert Cornet , Nicolas Raimarckers , Denis Bajusz
IPC分类号： F28F7/00
CPC分类号： F28D7/0066 , F01D25/08 , F05D2260/20 , F05D2260/213 , F28D1/0426 , F28D9/0093 , F28D2021/0021 , Y02T50/671 , Y02T50/675
摘要： The present invention relates to a heat exchange system in a turbine engine comprising a number of units and equipment (10,20) to be cooled and/or lubricated, sais system comprising at least two distinct oil circuits (2,3) to cool and/or lubricate said equipment (10,20), characterized in that said system is configured to put said oil circuits (2,3) in thermal contact with each other on the one hand and with a fluid playing the part of a cold source on the other hand.
摘要翻译：本发明涉及一种涡轮发动机中的热交换系统，其包括要冷却和/或润滑的多个单元和设备（10,20），该系统包括至少两个不同的油回路（2,3）以冷却和 /或润滑所述设备（10,20），其特征在于，所述系统被配置成一方面将所述油回路（2,3）彼此热接触，并且将流体播放冷源的一部分另一方面。

7. 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）。

8. 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。

9. 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）。

10. 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。

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