公开(公告)号：US08226028B2

公开(公告)日：2012-07-24

申请号：US12602110

申请日：2008-06-02

Applicant: Herve Marche

Inventor： Herve Marche

IPC: F02C7/20

CPC classification number: B64D27/12 ,  B64D2027/264

Abstract: An engine unit for an aircraft including a turboprop engine and its device for mounting on to a wing surface. The device includes a rigid structure and a mechanism for fastening the turboprop engine on to this structure. The fastening mechanism includes six mutually independent hydraulic systems, each one exclusively dedicated to the transfer, to the rigid structure, of forces exerted respectively according to one of the six degrees of freedom of movement. Each hydraulic system includes at least one hydraulic jack with a piston attached to one of the two elements, i.e. either the turboprop engine or the rigid structure, together with a cylinder housing the piston and attached to the other of the two elements.

Abstract translation: 一种用于飞机的发动机单元，包括涡轮螺旋桨发动机及其装置，用于安装在机翼表面上。 该装置包括刚性结构和用于将涡轮螺旋桨发动机紧固到该结构的机构。 紧固机构包括六个相互独立的液压系统，每个独立的液压系统专门用于分别根据六个运动自由度中的一个自动地施加到刚性结构上的力。 每个液压系统包括至少一个液压千斤顶，其具有连接到两个元件中的一个，即涡轮螺旋桨发动机或刚性结构中的一个的活塞，以及容纳活塞并连接到两个元件中的另一个的柱塞。

公开(公告)号：US20090218441A1

公开(公告)日：2009-09-03

申请号：US12084393

申请日：2006-10-24

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D27/16

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: A front attachment device for fastening a turbojet engine to an aircraft fixing strut. The attachment device is adapted to absorb the turbojet engine thrust loads, and includes a top bracket, and a lower bracket. A thrust load absorption vector results from a first convergence point of primary vectors passing through primary fixing points that couple the top bracket to the lower bracket and a second convergence point of secondary vectors passing through secondary fixing points that couple the lower bracket to the turbojet engine. The thrust load absorption vector transmits the turbojet engine thrust loads to the fixing strut, and extends along a longitudinal axis of the turbojet engine.

Abstract translation: 用于将涡轮喷气发动机紧固到飞机固定支柱的前附接装置。 附接装置适于吸收涡轮喷气发动机推力载荷，并且包括顶部支架和下部支架。 推力负载吸收矢量来自于通过将顶部支架耦合到下部支架的主要固定点的主要矢量的第一收敛点和通过将下部支架耦合到涡轮喷气发动机的辅助矢量的次要矢量的第二收敛点 。 推力负载吸收矢量将涡轮喷气发动机推力负载传递到固定支柱，并沿着涡轮喷气发动机的纵向轴线延伸。

公开(公告)号：US20050194492A1

公开(公告)日：2005-09-08

申请号：US11059440

申请日：2005-02-17

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D27/26 ,  B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of a strut, comprising a thrust resistance device (20) comprising a spreader beam (28) provided with two lateral lower ends (32a) placed such that a horizontal plane passes through them and through a longitudinal axis of the engine. Moreover, the device (20) is also fitted with two fittings (44) each comprising a forward end (44a) through which the said horizontal plane also passes and fixed to a forward part of a central casing (22), and an aft end (44b) connected to one of the ends (32a). Furthermore, the spreader beam is connected to the forward mount and to the rigid structure through its upper end (30b).

Abstract translation: 本发明涉及一种插入飞机发动机和支柱刚性结构之间的安装系统（1），包括一个推力阻力装置（20），该推力阻力装置（20）包括一个吊架梁（28） 水平面通过它们并通过发动机的纵向轴线。 此外，装置（20）还装配有两个配件（44），每个配件包括前端（44a），所述水平面也通过该前端（44a）通过并固定到中心壳体（22）的前部，并且后部 端部（44b）连接到端部（32a）之一。 此外，吊架梁通过其上端（30b）连接到前部安装件和刚性结构。

公开(公告)号：US07823624B2

公开(公告)日：2010-11-02

申请号：US11491648

申请日：2006-07-24

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B60H3/00 ,  B60H1/00 ,  F28D7/02 ,  F04D31/00 ,  F01D1/00 ,  F01D25/08 ,  B64D33/02 ,  B64D33/10

CPC classification number: B64D13/00 ,  F28D7/0058 ,  F28D21/0014 ,  F28D2021/0021

Abstract: A heat exchanger comprising a main heat exchange housing, a cooling air inlet line and a hot air inlet line to bring a cooling airflow and a hot airflow in the main housing. A heat pre-exchanger is disposed upstream from the main housing, the heat pre-exchanger being able to be crossed by the cooling airflow and the hot airflow prior to the main housing. The invention also relates to a propulsion unit and an aircraft comprising such a heat exchanger.

Abstract translation: 一种热交换器，其包括主热交换壳体，冷却空气入口管线和热空气入口管线，以在主壳体中产生冷却气流和热气流。 热预交换器设置在主壳体的上游，热交换器能够在主壳体之前被冷却气流和热气流交叉。 本发明还涉及一种包括这种热交换器的推进装置和飞行器。

公开(公告)号：US20100237200A1

公开(公告)日：2010-09-23

申请号：US11490195

申请日：2006-07-20

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D33/02 ,  F02K99/00 ,  F04D29/56

CPC classification number: F02K3/06 ,  F01D9/065 ,  F02C6/08 ,  F02C7/185 ,  Y02T50/675 ,  Y10T137/0645

Abstract: A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine. The turbojet engine comprises a regulation device to regulate an air flow-rate in a cooling air lead-in conduit conveying a stream of cooling air into a thermal exchanger, The regulation device regulates the air flow-rate upstream with respect to the cooling air lead-in conduit

Abstract translation: 推进单元包括位于涡轮喷气发动机上方的涡轮喷气发动机和热交换器。 涡轮喷气发动机包括调节装置，以调节将冷却空气流输送到热交换器中的冷却空气导入管道中的空气流量。调节装置调节相对于冷却空气引导管的上游的空气流速 在管道

公开(公告)号：US07784735B2

公开(公告)日：2010-08-31

申请号：US11994205

申请日：2006-06-26

Applicant: Herve Marche

Inventor： Herve Marche

IPC: F02K1/54

CPC classification number: F02K1/70 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  Y02T50/671

Abstract: A pod for an aircraft including a cowling, an engine housed in the inner volume of the cowling, an annular channel circulating a secondary thrust flow arranged between the engine and the cowling, and at least one thrust reverser for forming a reverse flow from the secondary thrust flow circulating in the annular channel. The thrust reverser including a plurality of doors provided in the rear part of the cowling, so as to form a trailing edge of the cowling. The thrust reverser can include means for actuating the doors such that at lease one actuating means actuates two adjacent doors and at least one door is actuated by two actuating means.

Abstract translation: 一种用于飞机的荚，包括整流罩，容纳在整流罩的内部容积中的发动机，环绕通道布置在发动机和整流罩之间的次级推力流，以及至少一个推力反向器，用于从次级 推力流在环形通道中循环。 推力反向器包括设置在整流罩的后部的多个门，以形成整流罩的后缘。 推力反向器可以包括用于致动门的装置，使得至少一个致动装置致动两个相邻的门，并且至少一个门由两个致动装置致动。

公开(公告)号：US07156343B2

公开(公告)日：2007-01-02

申请号：US11059440

申请日：2005-02-17

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of a strut, comprising a thrust resistance device (20) comprising a spreader beam (28) provided with two lateral lower ends (32a) placed such that a horizontal plane passes through them and through a longitudinal axis of the engine. Moreover, the device (20) is also fitted with two fittings (44) each comprising a forward end (44a) through which the said horizontal plane also passes and fixed to a forward part of a central casing (22), and an aft end (44b) connected to one of the ends (32a). Furthermore, the spreader beam is connected to the forward mount and to the rigid structure through its upper end (30b).

Abstract translation: 本发明涉及一种插入飞机发动机和支柱刚性结构之间的安装系统（1），包括一个推力阻力装置（20），该推力阻力装置（20）包括一个吊架梁（28） 水平面通过它们并通过发动机的纵向轴线。 此外，装置（20）还装配有两个配件（44），每个配件包括前端（44a），所述水平面也通过该前端（44a）通过并固定到中心壳体（22）的前部，并且后部 端部（44b）连接到端部（32a）之一。 此外，吊架梁通过其上端（30b）连接到前部安装件和刚性结构。

公开(公告)号：US08196859B2

公开(公告)日：2012-06-12

申请号：US12509818

申请日：2009-07-27

Applicant: Herve Marche ,  Fabien Raison

Inventor： Herve Marche ,  Fabien Raison

IPC: B64D27/16 ,  B64D27/18 ,  B64D27/20

CPC classification number: B64D27/20 ,  B64C39/10 ,  B64D27/26 ,  B64D2027/264 ,  B64D2027/266

Abstract: A system for attaching an engine to the structure of an aircraft, such as a sail wing aircraft is disclosed. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure, and firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft which is inclined relative to the Y-direction and to the Z-direction so that they bear the forces along the longitudinal direction and forces which are inclined relative to the Z-direction and Y-direction.

Abstract translation: 公开了一种用于将发动机附接到诸如帆翼飞机的飞行器的结构的系统。 该系统包括上梁，该上梁在其前端牢固地固定到安装在飞行器结构上的第一框架上，并且将其中间部分牢固地固定到位于第一框架后部的第二框架。 发动机挂在上梁下方。 该系统相对于纵向轴线X，横向轴线Y和垂直轴线Z定向。两个前部发动机附接点对称地布置在发动机的垂直中心平面的任一侧上。 前附接点包括相对于Y方向和Z方向倾斜的轴，使得它们承受沿着纵向方向的力和相对于Z方向和Y方向倾斜的力。

公开(公告)号：US07997061B2

公开(公告)日：2011-08-16

申请号：US11490195

申请日：2006-07-20

Applicant: Herve Marche

Inventor： Herve Marche

IPC: F02C6/04 ,  F02K3/04

CPC classification number: F02K3/06 ,  F01D9/065 ,  F02C6/08 ,  F02C7/185 ,  Y02T50/675 ,  Y10T137/0645

Abstract: A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine. The turbojet engine comprises a regulation device to regulate an air flow-rate in a cooling air lead-in conduit conveying a stream of cooling air into a thermal exchanger, The regulation device regulates the air flow-rate upstream with respect to the cooling air lead-in conduit.

Abstract translation: 推进单元包括位于涡轮喷气发动机上方的涡轮喷气发动机和热交换器。 涡轮喷气发动机包括调节装置，以调节将冷却空气流输送到热交换器中的冷却空气导入管道中的空气流量。调节装置调节相对于冷却空气引导管的上游的空气流速 在管道。

公开(公告)号：US07232091B2

公开(公告)日：2007-06-19

申请号：US11059444

申请日：2005-02-17

Applicant: Herve Marche

Inventor： Herve Marche

IPC: B64D27/18

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: This invention relates to a mounting system (100) inserted between an aircraft engine (2) and a rigid structure (4) of an attachment strut (6) fixed under a wing (8) of this aircraft, the system including a forward mount (16), an aft mount (18) and a device (20, 120, 220) for resisting thrusts generated by the engine (2). The system also comprises additional means (23) for opposing the longitudinal bending of the engine (2), these additional means (23) being designed to resist loads only starting from a predetermined deformation of this engine (2). According to the invention, the additional means (23) comprise at least one connecting rod (32) capable of opposing longitudinal bending of the engine (2), each connecting rod (32) being connected firstly to the rigid structure (4) of the strut (6) and secondly to a fan casing (26) of the engine (2), so that it is only stressed starting from the predetermined deformation of this engine (2).

Abstract translation: 本发明涉及一种插入在飞行器发动机（2）和固定在该飞行器的机翼（8）下方的附接支柱（6）的刚性结构（4）之间的安装系统（100），该系统包括前悬架 16），后部安装件（18）和用于抵抗由发动机（2）产生的推力的装置（20,120,220）。 该系统还包括用于与发动机（2）的纵向弯曲相对的附加装置（23），这些附加装置（23）设计成只能从该发动机（2）的预定变形开始抵抗负载。 根据本发明，附加装置（23）包括能够相对于发动机（2）的纵向弯曲的至少一个连杆（32），每个连杆（32）首先连接到发动机（2）的刚性结构（4） 支柱（6），其次是发动机（2）的风扇壳体（26），从而仅从该发动机（2）的预定变形开始受力。