公开(公告)号：US20160332736A1

公开(公告)日：2016-11-17

申请号：US15115213

申请日：2015-01-29

申请人： SNECMA ,  SAFRAN ,  MICROTURBO

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

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

CPC分类号： 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

摘要： 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.

摘要翻译： 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：US20150333527A1

公开(公告)日：2015-11-19

申请号：US14655707

申请日：2013-12-24

申请人： MICROTURBO

发明人： Jean-Francois RIDEAU ,  Florent DALMAS

IPC分类号： H02J5/00 ,  B64D41/00 ,  H02J9/00

CPC分类号： H02J7/02 ,  B64D41/00 ,  B64D2221/00 ,  H02J3/006 ,  H02J4/00 ,  H02J9/00 ,  H02J2003/001 ,  Y10T307/406

摘要： A method for managing an electrical power supply system (1) of an aircraft, the power supply system (1) comprising at least one distribution bus arranged so as to power the electrical loads, at least one generator (G1, G2) of a propulsion engine of the aircraft, at least one engine-class main power unit (MPS1, MPS2), a plurality of contactors (C1-C18) which are capable of electrically connecting the distribution buses to the propulsion engine generator (G1, G2) and/or the main power unit (MPS1, MPS2); and a management module which is capable of controlling the contactors (C1-C18), a method wherein, during normal operating conditions of the aircraft, the distribution bus is powered by the engine-class main power unit (MPS1, MPS2) and, during the back-up operating mode of the aircraft, the distribution bus is powered by the propulsion engine generator (G1, G2).

摘要翻译： 一种用于管理飞机的电力供应系统（1）的方法，所述电力供应系统（1）包括布置成为所述电力负载供电的至少一个配电总线，所述至少一个发电机（G1，G2） 飞机的发动机，至少一个发动机级主动力单元（MPS1，MPS2），能够将分配总线电连接到推进发动机发电机（G1，G2）的多个接触器（C1-C18）和/ 或主电源单元（MPS1，MPS2）; 以及能够控制接触器（C1-C18）的管理模块，其中在飞行器的正常操作条件期间，分配总线由发动机级主动力单元（MPS1，MPS2）供电，并且在 飞机的备用操作模式，分配总线由推进发动机发电机（G1，G2）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

申请人： MICROTURBO SA

发明人： Fabien SILET ,  Stephane CHEVALIER ,  Jean-Francois RIDEAU

IPC分类号： F15B15/00

CPC分类号： 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

摘要： 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.

摘要翻译： 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：US20170361490A1

公开(公告)日：2017-12-21

申请号：US15524166

申请日：2015-11-03

申请人： SAFRAN POWER UNITS

发明人： Emilie HERNY ,  Jean-Francois RIDEAU ,  Moataz ATTALLAH ,  Gang LIU ,  Tim BUTTON ,  Yun JIANG

IPC分类号： B28B7/34 ,  B28B1/00 ,  F01D5/28 ,  B28B1/24 ,  B22D19/00 ,  B22C9/04

CPC分类号： B28B7/346 ,  B22C9/04 ,  B22D19/00 ,  B28B1/001 ,  B28B1/24 ,  F01D5/284 ,  F05D2230/21 ,  F05D2300/21 ,  Y02P10/292

摘要： A method of fabricating a ceramic turbine blade, the method includes selective melting on a powder bed in order to obtain a blade mold cavity in a mold, a ceramic-based suspension is provided, the suspension is introduced into the blade mold cavity, the suspension is subjected to a gelation step in the mold cavity in order to obtain a blade suitable for being extracted from the mold cavity, and the blade is extracted from the mold cavity.