公开(公告)号：US20150143950A1

公开(公告)日：2015-05-28

申请号：US14410671

申请日：2013-06-12

Applicant: TURBOMECA ,  MICROTURBO ,  LABINAL POWER SYSTEMS

Inventor： Olivier Bedrine ,  Christian Sarrat ,  Fabien Silet ,  Sebastien Viellard

IPC: B64D41/00 ,  B64D27/24

CPC classification number: B64D41/00 ,  B64C27/04 ,  B64C27/12 ,  B64D27/24 ,  B64D2027/026 ,  B64D2041/002 ,  B64D2221/00 ,  Y10T74/19014

Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

Abstract translation: 一种通过允许发动机在飞行期间提供非推进和/或推进动力来优化包括辅助发动机的直升机上可用的整个牵引系统的方法和配置。 辅助发动机被联接以直接参与向飞行器提供机械或电推进动力和电非推进动力。 架构配置包括车载供电网络，两个主发动机，以及用于将机械能转换成主齿轮箱与推进构件之间的电能的系统，以及接收包括车载网络和电力电子装置的电能的机构 与主发动机的起动器相结合。 辅助动力发动机通过能量转换系统和用于在辅助发动机与至少一个推进构件之间的机械联接的机构向机构提供电能以接收电能。

公开(公告)号：US10329023B2

公开(公告)日：2019-06-25

申请号：US15115213

申请日：2015-01-29

Applicant: SNECMA ,  SAFRAN ,  MICROTURBO

Inventor： Nicolas Claude Parmentier ,  Pierre Froment ,  Jean-Francois Rideau ,  Bruno Thoraval

IPC: B64D13/06 ,  F02C6/20 ,  B64D13/00 ,  B64D13/02 ,  B64D13/08 ,  B64D27/10 ,  F04D29/32 ,  F04D29/52 ,  F04D29/56 ,  F04D29/58 ,  F02C7/27 ,  F02C9/18

Abstract: An aircraft turboprop engine (310) including at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body. At least one of the bodies includes a compressor. The low-pressure body drives a first gearbox (16) The turboprop engine also includes at least one load compressor (60) for supplying air to an air-conditioning circuit of an aircraft cabin. A rotor (61) of the load compressor is coupled to the low-pressure body. The load compressor (60) includes an air inlet (62) connected to a conduit (72) to bleed air from the compressor of the turboprop engine when all of the aforementioned bodies include only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies include at least two compressors.

公开(公告)号：US20160332736A1

公开(公告)日：2016-11-17

申请号：US15115213

申请日：2015-01-29

Applicant: SNECMA ,  SAFRAN ,  MICROTURBO

Inventor： Nicolas Claude PARMENTIER ,  Pierre FROMENT ,  Jean-Francois RIDEAU ,  Bruno THORAVAL

IPC: B64D13/02 ,  B64D13/08 ,  B64D27/10 ,  B64D13/06

CPC classification number: B64D13/06 ,  B64D13/00 ,  B64D13/02 ,  B64D13/08 ,  B64D27/10 ,  B64D2013/0618 ,  B64D2013/0696 ,  F02C6/206 ,  F02C7/27 ,  F02C9/18 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/5833 ,  F05B2220/303 ,  F05B2260/20 ,  F05D2220/323 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2240/60 ,  F05D2260/4031 ,  Y02T50/56 ,  Y02T50/671 ,  Y02T50/675

Abstract: The invention relates to an aircraft turboprop engine (310) comprising at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propeller by means of a first gearbox (16), the turboprop engine also comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, characterised in that said supply means comprise at least one compressor (60) of which the rotor (61) is coupled to the low-pressure body, said load compressor (60) including an air inlet (62) connected to means (72) for bleeding air from the compressor of the turboprop engine when all of the aforementioned bodies comprise only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies comprise at least two compressors.

Abstract translation: 本发明涉及一种飞机涡轮螺旋桨发动机（310），其包括至少一个低压主体（12）和高压体（14），也可能包括中压体，至少一个所述主体包括压缩机， 所述低压体通过第一齿轮箱（16）驱动螺旋桨，所述涡轮螺旋桨发动机还包括用于向飞机机舱的空调回路提供空气的装置，其特征在于，所述供给装置包括至少一个压缩机 60），其中转子（61）联接到低压体，所述负载压缩机（60）包括连接到装置（72）的空气入口（62），用于当涡轮螺旋桨发动机全部 当所有的主体包括至少两个压缩机时，上述主体仅包括单个压缩机，或者来自涡轮螺旋桨发动机的中压装置的低压主体的压缩机或压缩机。

公开(公告)号：US20160297539A1

公开(公告)日：2016-10-13

申请号：US15100607

申请日：2014-12-04

Applicant: Microturbo

Inventor： Olivier CAZENAVE ,  Clement LALANNE ,  Luc DIONNE

IPC: B64D41/00 ,  G09B25/02 ,  G09B19/00 ,  B64F5/00 ,  F16M13/02

CPC classification number: B64D41/00 ,  B64D2041/002 ,  B64F5/00 ,  F16M13/02 ,  G09B19/0069 ,  G09B25/02 ,  Y02T50/44

Abstract: The invention relates to a method for mounting an engine module (1) in a support comprising a first structure (3) and a second structure (2) that is offset relative to the first structure (3), method intended for positioning at least a specified part (4) of the engine module (1) relative to an element (6) of the second structure (2) by means of an isostatic suspension connecting the engine module (1) to said first structure (3) by means of first connecting rods (10a, 10b, 10c, 10d) and to said second structure (2) by means of second connecting rods (10e, 10f), the length of said first and second connecting rods being defined in advance, method wherein the length of at least two (10c, 10f) of said first and second connecting rods is adjusted relative to the previously defined length thereof, in order to position said specified part (4) of the engine module (1) relative to said element (6) of the second structure (2) in said support. The invention also relates to said support comprising adjustable connecting rods, in an installation comprising in particular an auxiliary power unit for an aircraft.

Abstract translation: 本发明涉及一种用于将发动机模块（1）安装在包括相对于第一结构（3）偏移的第一结构（3）和第二结构（2））的支撑件中的方法，其用于将至少一个 发动机模块（1）的相对于第二结构（2）的元件（6）的指定部分（4）借助于通过第一结构将发动机模块（1）连接到所述第一结构（3）的等静压悬架 连接杆（10a，10b，10c，10d）和借助于第二连接杆（10e，10f）连接到所述第二结构（2），所述第一和第二连杆的长度预先限定，其中， 至少两个（10c，10f）的所述第一和第二连杆相对于其先前限定的长度被调节，以便相对于所述元件（6）将所述发动机模块（1）的所述指定部分（4）相对于所述元件 所述支撑件中的第二结构（2）。 本发明还涉及包括可调连接杆的所述支撑件，该装置尤其包括用于飞行器的辅助动力单元。

公开(公告)号：US20160264252A1

公开(公告)日：2016-09-15

申请号：US15032782

申请日：2014-10-29

Applicant: MICROTURBO

Inventor： Jean-Francois Rideau

IPC: B64D41/00 ,  F04C23/02 ,  F04C18/16 ,  F04B35/06 ,  F04C18/02

CPC classification number: B64D41/00 ,  B64D2041/002 ,  F01D19/00 ,  F02C7/26 ,  F02C7/32 ,  F04B35/06 ,  F04C18/0215 ,  F04C18/16 ,  F04C23/02 ,  F05D2220/50

Abstract: The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a supercharger (7), and transferring non-propulsive energy from the auxiliary power unit (6) to the aircraft. The invention also concerns a system (5) for generating auxiliary power in an aircraft and an aircraft implementing such a method.

Abstract translation: 本发明涉及一种用于在飞行器中产生辅助动力的方法，其包括以下步骤：通过从增压器（7）向辅助动力单元（6）供应压缩空气来启动飞行器的辅助动力单元（6） 并将非推进能量从辅助动力单元（6）传送到飞行器。 本发明还涉及用于在飞行器中产生辅助动力的系统（5）和实现这种方法的飞行器。

公开(公告)号：US20150367952A1

公开(公告)日：2015-12-24

申请号：US14763796

申请日：2014-01-23

Applicant: MICROTURBO

Inventor： Jean-Francois Rideau ,  Fabien Silet

IPC: B64D33/02 ,  B64D41/00

CPC classification number: B64D33/02 ,  B64D41/00 ,  B64D2033/0213 ,  F01D25/10 ,  F02C7/08 ,  Y02T50/675

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract translation: 本发明涉及一种用于将空气供给到包括加压舱（10）和辅助动力单元（2）的飞行器（1）的辅助动力单元（2）的结构（3），该结构包括：管道（30） 用于将空气供给到辅助动力单元; 用于控制供给到辅助动力单元的气流的单元（4）; 以及用于在飞机外部进入空气的阀（31），其设置在进料管（30）的入口处，阀的开口由控制单元（4）驱动。 该结构的特征在于，它还包括用于将空气从加压舱喷射到辅助动力单元进料管中的回路（32）。 本发明还涉及一种将空气供给到辅助动力单元的方法。

公开(公告)号：US20150360630A1

公开(公告)日：2015-12-17

申请号：US14763720

申请日：2014-01-20

Applicant: MICROTURBO

Inventor： Jean-François Rideau ,  Florent Dalmas

IPC: B60R16/03 ,  B64D41/00

CPC classification number: B60R16/03 ,  B64D41/00 ,  B64D2221/00 ,  H02J4/00

Abstract: A method and a system for supplying electrical energy to an aircraft that is equipped with a plurality of loads to be powered, said power supply system comprising a plurality of power sources and an on-board energy management module, the energy management module being electrically connected to said power sources and to said loads to be powered. The energy management module is arranged so as to control a supply of power to at least one of said loads using at least two different power sources in parallel in the event of increased energy requirements, said load being initially powered by a single power source.

Abstract translation: 一种用于向配备有要供电的多个负载的飞机提供电能的方法和系统，所述电源系统包括多个电源和车载能量管理模块，所述能量管理模块电连接 到所述电源和所述负载供电。 能量管理模块被布置成在增加的能量需求的情况下并行地使用至少两个不同的电源来控制至少一个所述负载的电力供应，所述负载最初由单个电源供电。

公开(公告)号：US20130333365A1

公开(公告)日：2013-12-19

申请号：US13911346

申请日：2013-06-06

Applicant: MICROTURBO SA

Inventor： Fabien SILET ,  Stephane CHEVALIER ,  Jean-Francois RIDEAU

IPC: F15B15/00

CPC classification number: F15B15/00 ,  B64D41/00 ,  F01D17/00 ,  F01D17/06 ,  F01D17/08 ,  F01D17/105 ,  F01D17/16 ,  F02C6/06 ,  F02C6/08 ,  F02C7/32 ,  F02C9/18 ,  F02C9/26 ,  F02C9/28 ,  F04D27/02 ,  F04D27/0207 ,  F04D27/0215 ,  F04D27/0223 ,  F04D27/023 ,  F05B2220/60 ,  F05D2220/50 ,  F05D2270/3015 ,  F05D2270/304

Abstract: A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.

Abstract translation: 用于向气动网络供应压缩空气的系统包括负载压缩机，空气源和驱动负载压缩机的动力轴。 该系统还包括在这种负载压缩机的空气出口中，连接通道在一侧上连接有与气动网络连接的通道，另一方面连接到朝向排气喷嘴的空气排放导管。 通过作为压力传感器和速度传感器的函数的伺服回路由处理单元控制空气流量放气阀。

公开(公告)号：US20130177390A1

公开(公告)日：2013-07-11

申请号：US13732661

申请日：2013-01-02

Applicant: MICROTURBO

Inventor： Serge COT ,  Clement Lalanne

IPC: F01D25/18

CPC classification number: F01D25/18 ,  F05D2240/61

Abstract: A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet.

Abstract translation: 一种用于涡轮发动机的轴，所述轴具有轴向地分成第一和第二腔室的空腔。 轴还包括具有轴向管道，第一径向孔口和第二径向孔口的分配器构件。 轴向管道具有敞开的第一端和沿轴向封闭的第二端。 第一径向孔将轴向管道的第二端连接到第一室，以便向第一轴承供给润滑流体，并且第二径向孔将轴向管道的第二端连接到第二室以将第二轴承与 润滑液。 分配器构件的第一径向孔和第二径向孔距离润滑流体入口基本相等的轴向距离。