公开(公告)号：US10384799B2

公开(公告)日：2019-08-20

申请号：US15032782

申请日：2014-10-29

申请人： Microturbo

发明人： Jean-Francois Rideau

IPC分类号： B64D41/00 ,  F01D19/00 ,  F02C7/26 ,  F02C7/32 ,  F04B35/06 ,  F04C18/02 ,  F04C18/16 ,  F04C23/02

摘要： 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.

公开(公告)号：US10183759B2

公开(公告)日：2019-01-22

申请号：US15100607

申请日：2014-12-04

申请人： Microturbo

发明人： Olivier Cazenave ,  Clement Lalanne ,  Luc Dionne

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

摘要： 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.

公开(公告)号：US10014707B2

公开(公告)日：2018-07-03

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： H02J7/02 ,  H02J9/00 ,  B64D41/00 ,  H02J4/00 ,  H02J3/00

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).

公开(公告)号：US20150296650A1

公开(公告)日：2015-10-15

申请号：US14441882

申请日：2013-11-12

申请人： MICROTURBO

发明人： Ludovic Pasquier ,  Daniel Averous ,  Remi Joachim

IPC分类号： H05K7/14 ,  H05K5/04 ,  F01D21/02

CPC分类号： H05K7/1417 ,  F01D21/02 ,  F01D21/045 ,  F02C9/46 ,  F05D2270/09 ,  H05K5/04 ,  Y02T50/671

摘要： An aircraft turbomachine calculator including a parallelepiped metal casing including an electronic circuit wherein a control channel and a monitoring channel are integrated. The casing includes a first cavity wherein a first electronic board is provided for managing the control channel and a second cavity, independent of the first cavity, wherein a second electronic board is provided for managing the monitoring channel, these electronic boards being provided in two planes oriented with respect to each other at an angle of 90°.

摘要翻译： 一种飞机涡轮机计算器，包括包括电子电路的平行六面体金属外壳，其中集成了控制通道和监控通道。 所述壳体包括第一腔体，其中设置有用于管理所述控制通道的第一电子板和独立于所述第一腔的第二腔，其中设置有用于管理所述监测通道的第二电子板，所述电子板设置在两个平面 相对于彼此以90°的角度取向。

公开(公告)号：US20150292348A1

公开(公告)日：2015-10-15

申请号：US14441668

申请日：2013-11-12

申请人： MICROTURBO

发明人： Ludovic Pasquier ,  Remi Joachim

IPC分类号： F01D17/06 ,  G01P3/00 ,  B64D41/00 ,  G01M15/14 ,  B64D31/06 ,  G01P21/00 ,  G01M17/00

CPC分类号： F01D17/06 ,  B64D31/06 ,  B64D41/00 ,  G01M15/14 ,  G01M17/00 ,  G01P3/00 ,  G01P21/00 ,  G01P21/02 ,  Y02T50/671

摘要： A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor. Analyzing the error signals, exceeding the determined deviation can control stopping the turbomachine.

摘要翻译： 一种保护飞机涡轮机计算机免受速度测量误差的装置，包括：在速度调节通道上：涡轮机齿轮箱轴的速度传感器，速度测量电路和速度调节电路; 在监视通道上：涡轮机气体发生器轴的速度传感器，速度测量电路和涡轮机停止控制电路。 每个通道使用不同的特性消除常见模式错误。 每个速度传感器提供伪正弦频率信号。 在每个通道上，速度监测电路将频率信号与最小阈值进行比较，当测量的频率低于最小阈值时传递误差信号。 普通速度交叉检查电路检测超过两个频率之间的确定偏差，所监视的偏差高于或低于对应于任一传感器上的频率周期损失的最大偏差。 分析误差信号，超过确定的偏差可以控制停止涡轮机。

公开(公告)号：US20150089921A1

公开(公告)日：2015-04-02

申请号：US13845862

申请日：2013-03-18

申请人： Microturbo

发明人： Jean-Francois Rideau ,  Fabien Silet

IPC分类号： F02C9/46

CPC分类号： F02C9/46 ,  B64D41/00 ,  F02C7/26 ,  F05D2220/50

摘要： An auxiliary power supply architecture includes one APU and a fuel supply basic circuit with a common fuel storage tank, a primary circulation conduct and secondary conducts for injecting such fuel into the combustion chambers of the APU unit through appropriate injectors. Such architecture also includes another independent fuel supply circuit to supply the APU unit with an emergency tank, a specific primary conduct for emergency fuel circulation and secondary conducts for injecting emergency fuel into the combustion chambers through appropriate injectors.

摘要翻译： 辅助电源架构包括一个APU和具有公共燃料储罐的燃料供应基本电路，主循环导管和二次导管，用于通过适当的注射器将这种燃料喷射到APU单元的燃烧室中。 这种结构还包括另一个独立的燃料供应回路，以向APU单元提供紧急罐，用于紧急燃料循环的特定主要行为，以及通过适当的注射器将紧急燃料喷射到燃烧室中的二次导管。

公开(公告)号：US10301036B2

公开(公告)日：2019-05-28

申请号：US15103277

申请日：2014-12-08

申请人： MICROTURBO

发明人： Olivier Cazenave ,  Clement Lalanne ,  Xavier Barneto

IPC分类号： G05D1/12 ,  B64D41/00 ,  B64D33/04 ,  B64D33/08

摘要： The invention relates to an assembly comprising a structure (2) and a tubular element (6), which is mounted isostatically in the structure (2), said tubular element (6) comprising a first end (7) connected to said structure by at least four connecting rods 10a-10b-10c-10d, thus setting four first degrees of freedom, and a second end (8) connected to said structure (2) by an attachment means (20) that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof. In particular, it relates to an exhaust suitable for an auxiliary power unit in the compartment thereof and to the mounting method for aligning them.

公开(公告)号：US20160347457A1

公开(公告)日：2016-12-01

申请号：US15115137

申请日：2015-01-29

申请人： SNECMA ,  SAFRAN ,  MICROTURBO

发明人： Nicolas Claude Paramentier ,  Pierre Froment ,  Jean-François Rideau ,  Bruno Thoraval

IPC分类号： B64D13/06 ,  B64D13/02 ,  F04D29/56 ,  F04D29/58 ,  F04D29/32 ,  F04D29/52

摘要： An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a first gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

摘要翻译： 飞机涡轮螺旋桨发动机至少具有低压体和高压体。 低压体通过第一齿轮箱驱动螺旋桨。 涡轮螺旋桨发动机还包括用于向飞机机舱的空调回路供应空气的装置，其中所述供应装置具有至少一个压缩机，转子与低压体联接。 压缩机具有连接到用于从涡桨发动机的空气入口管道排出空气的装置的进气口。

公开(公告)号：US09238974B2

公开(公告)日：2016-01-19

申请号：US13732661

申请日：2013-01-02

申请人： MICROTURBO

发明人： Serge Cot ,  Clement Lalanne

IPC分类号： F01D25/18

CPC分类号： F01D25/18 ,  F05D2240/61

摘要： 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.

摘要翻译： 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。

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。