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1. 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。

2. 发明授权

US08899917B2 Gas flow separator with a thermal bridge de-icer 有权
标题翻译：带热桥式除冰器的气流分离器
公开(公告)号：US08899917B2
公开(公告)日：2014-12-02
申请号：US13429627
申请日：2012-03-26
申请人： Denis Bajusz , Nicholas Raimarckers , Antoine Stephany , Georges Broers , Yves Culot , Marc Strengnart , Albert Cornet , David Depaepe
发明人： Denis Bajusz , Nicholas Raimarckers , Antoine Stephany , Georges Broers , Yves Culot , Marc Strengnart , Albert Cornet , David Depaepe
IPC分类号： F01D25/02 , F02C7/047
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。流动分离器还包括具有“S”形式的纵向部分的金属叶片，并且位于与前缘的后部接触的鼻部并且在一定距离处从分离器的前缘延伸到后端从前缘开始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

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。

4. 发明授权

US08967958B2 Integration of an air-liquid heat exchanger on an engine 有权
标题翻译：在发动机上集成了空气 - 液体热交换器
公开(公告)号：US08967958B2
公开(公告)日：2015-03-03
申请号：US12971532
申请日：2010-12-17
申请人： Denis Bajusz , David Depaepe , Jacques Charlier , Nicolas Raimarckers
发明人： Denis Bajusz , David Depaepe , Jacques Charlier , Nicolas Raimarckers
IPC分类号： F02C7/14 , F02K3/115
CPC分类号： F02K3/115 , F02C7/14 , Y02T50/675
摘要： A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.
摘要翻译：旁路轴向涡轮机包括风扇，低压定子级，高压定子级，压缩机被称为涡轮机的主流的流动，至少一次通过主流的流量控制定向级之一朝向次级流动，表面空气 - 油（ACOC）型热交换器平面布置在围绕定子级的壁上或壁上，并且限定二级流的内表面，直接位于第排出流量与所述壁通过，以便通过富集排出流速的二次流通过。

5. 发明申请

US20110150634A1 Integration of an Air-Liquid Heat Exchanger on an Engine 有权
标题翻译：发动机上的空气 - 液体换热器的集成
公开(公告)号：US20110150634A1
公开(公告)日：2011-06-23
申请号：US12971532
申请日：2010-12-17
申请人： Denis Bajusz , David Depaepe , Jacques Charlier , Nicolas Raimarckers
发明人： Denis Bajusz , David Depaepe , Jacques Charlier , Nicolas Raimarckers
IPC分类号： F01D17/00 , F25B43/02 , F01D25/08
CPC分类号： F02K3/115 , F02C7/14 , Y02T50/675
摘要： A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.
摘要翻译：旁路轴向涡轮机包括风扇，低压定子级，高压定子级，压缩机被称为涡轮机的主流的流动，至少一次通过主流的流量控制定向级之一朝向次级流动，表面空气 - 油（ACOC）型热交换器平面布置在围绕定子级的壁上或壁上，并且限定二级流的内表面，直接位于第排出流量与所述壁通过，以便通过富集排出流速的二次流通过。

6. 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。

7. 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。

8. 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）。

9. 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。

10. 发明授权

US08601791B2 Integration of a surface heat exchanger to the wall of an aerodynamic flowpath by a structure of reinforcement rods 有权
标题翻译：通过加强杆的结构将表面热交换器整合到空气动力学流路的壁上
公开(公告)号：US08601791B2
公开(公告)日：2013-12-10
申请号：US12977226
申请日：2010-12-23
申请人： Denis Bajusz , David Depaepe , Alain Derclaye , Régis Dupuy
发明人： Denis Bajusz , David Depaepe , Alain Derclaye , Régis Dupuy
IPC分类号： F02K99/00
CPC分类号： F02C7/14 , F01D25/14 , F01D25/18 , F02C7/18 , F02K3/02 , F05D2260/213 , F05D2260/232 , F28D9/0018 , F28D2021/0089 , F28F3/048 , F28F9/0075 , Y02T50/676
摘要： Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.
摘要翻译：在旁路涡轮机的二次流的壁中设置一个或多个冷却器。壁从中间壳体延伸到主流和次流之间的分离器鼻部的前缘。该壁包括连接到中间壳体的一系列支撑臂，分布在壁的周边上并且被引向上游。一系列形成壁段的表面空气 - 油热交换器在支撑臂上端对端设置，以形成环形壁。具有前缘的护罩布置并固定在热交换器的上游边缘的区域中，以便完成壁。支撑臂包括在每个臂上彼此连接的液压连接器，其适于与热交换器区域中的相应连接器和中间壳体的区域配合。

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