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公开(公告)号：US07430852B2
公开(公告)日：2008-10-07
申请号：US11042052
申请日：2005-01-26
IPC分类号： F02K3/02
CPC分类号： F02K1/68 , F01D5/22 , F02C7/20 , F05D2240/14
摘要： A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.
摘要翻译： 涡轮喷气发动机包括至少一个风扇，压缩机，燃烧室，涡轮机和刚性的大致圆柱形的套管，其紧固在其上游端到中间壳体，并且在其下游端处连接到排气罩，所述护套用于传递力 在中间壳体和排气壳体之间。
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公开(公告)号：US20050172609A1
公开(公告)日：2005-08-11
申请号：US11042052
申请日：2005-01-26
CPC分类号： F02K1/68 , F01D5/22 , F02C7/20 , F05D2240/14
摘要： A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.
摘要翻译： 涡轮喷气发动机包括至少一个风扇，压缩机，燃烧室，涡轮机和刚性的大致圆柱形的套管，其紧固在其上游端到中间壳体，并且在其下游端处连接到排气罩，所述护套用于传递力 在中间壳体和排气壳体之间。
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公开(公告)号：US4642810A
公开(公告)日：1987-02-10
申请号：US561848
申请日：1983-12-15
申请人： Jean-Louis Picard
发明人： Jean-Louis Picard
摘要： A data transmission system wherein data are entered upon activation of input points of an entry unit (1) of the keyboard type, including a sequence generation unit (5) generating a series of "maximum length" sequences on to a series-output (8) and a different binary pattern for each bit in the sequence on to a parallel-output (6). Such a binary pattern is compared in a coincidence circuit (7) with the binary representation of an activated point of the entry unit (1) so as to produce a bit "one" on line (9) which alters, through an X OR circuit (10), the corresponding bit in the sequence to be transmitted over the transmission line (11).
摘要翻译： 一种数据传输系统，其中在激活键盘类型的输入单元（1）的输入点时输入数据，该序列生成单元（5）产生一系列“最大长度”序列到串行输出（8 ）和序列中每个位到并行输出（6）的不同二进制模式。 这样的二进制模式在符合电路（7）中与入口单元（1）的激活点的二进制表示进行比较，以便在线路（9）上产生位“1”，其通过X或电路 （10），通过传输线（11）发送的序列中的相应位。
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4.发明授权
公开(公告)号：US5440874A
公开(公告)日：1995-08-15
申请号：US274709
申请日：1994-07-14
CPC分类号： F01D5/081 , F05D2240/81 , Y02T50/671 , Y02T50/676
摘要： A turbojet engine includes a combustion chamber located upstream of a turbine, the turbine having a rotor disk integrally bladed with vanes and including a channel blowing gas from a position outside a wall of the combustion chamber to a peripheral zone of the rotor disk adjacent to the vanes, a channel divided in front of a zone adjacent to the vanes into an internal channel and an external channel surrounding the internal channel, wherein the internal channel has a greater cross-section than the external channel and wherein the external channel converges upon approaching an outlet thereof so as to accelerate the gas flowing therethrough and prevent gas which passed through the internal channel from being dispersed.
摘要翻译： 涡轮喷气发动机包括位于涡轮机上游的燃烧室，涡轮机具有与叶片一体地叶片的转子盘，并且包括从燃烧室壁外的位置吹送气体的通道到与转子盘相邻的转子盘的周边区域 叶片，在与叶片相邻的区域的前面分成内部通道的通道和围绕内部通道的外部通道，其中内部通道具有比外部通道更大的横截面，并且其中外部通道在接近 出口，以加速流过其中的气体，并防止通过内部通道的气体分散。
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公开(公告)号：US4942572A
公开(公告)日：1990-07-17
申请号：US372146
申请日：1989-06-26
申请人： Jean-Louis Picard
发明人： Jean-Louis Picard
IPC分类号： H04L29/08 , G06F13/22 , H04L12/403
CPC分类号： G06F13/22 , H04L12/403 , H04L12/4013 , H04L12/413
摘要： A process is disclosed for efficiently polling low rate data terminals attached to communicate with a central station via a high speed channel. The process is based on the use of a dual rate polling mechanism involving first polling by using a high rate pseudo random sequence; monitoring the messages received back from the terminals; checking said messages for validity, and upon detecting an invalid message possibly indicating collision between terminal messages, then switching back into the first generated sequence at a lower conventional rate.
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6.发明授权公开(公告)号：US06474596B1
公开(公告)日：2002-11-05
申请号：US09678259
申请日：2000-10-03
IPC分类号： B64D2700
CPC分类号： B64D27/26 , B64D2027/266
摘要： A suspension system for an aircraft powerplant attached to an aircraft frame and having a housing. The suspension system includes a spindle mounted in a spindle support rigidly joined to the aircraft frame, a bearing cage affixed to the housing and having a bearing positioned therein, a pair of suspension arms connected to the spindle support, and a pair of lateral linkrods configured to link the housing and the suspension arms. The side surfaces of the bearing cage and the suspension arms define a clearance therebetween concentric to the Y-axis. The bearing cage is configurable along the spindle such that the bearing cage is limited to displacement relative to the longitude of the spindle while maintaining contact with the spindle.
摘要翻译： 一种用于飞机动力装置的悬挂系统，其连接到飞机框架并具有壳体。 悬挂系统包括安装在刚性地连接到飞行器机架的主轴支架中的主轴，固定到壳体并且具有定位在其中的轴承的轴承座，连接到主轴支撑件的一对悬架臂和配置成的一对横向连杆 以连接外壳和悬挂臂。 轴承保持架和悬挂臂的侧表面与Y轴同心地形成一个间隙。 轴承保持架可以沿主轴配置，使得轴承保持架被限制为相对于主轴经度的位移，同时保持与主轴的接触。
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7.发明授权Turbo aero engine provided with a device for heating turbine disks on revving up 失效涡轮增压涡轮发动机配有一个加热涡轮盘的装置
公开(公告)号：US5586860A
公开(公告)日：1996-12-24
申请号：US332101
申请日：1994-10-31
CPC分类号： F01D5/082 , Y02T50/676
摘要： Turbo aero engine including a heating arrangement for the internal portions (12) of turbine disks on revving up so as to reduce the temperature gradient in the disks. Heating gas passes through pipes (11) integral with the stator and reheats the disks by passing through a gasket (13) designed with the tongues (18) and orifices (20 and 22) which allow the gas to circulate towards the zones to be heated when the revving up has firstly heated the portions of the machine close to the pipes (11) and then makes it possible to interrupt the communication when the temperatures even out and the original heat expansions become uniform and offset the orifices (20 and 23).
摘要翻译： 涡轮增压器航空发动机包括用于涡轮盘的内部部分（12）的加热装置，用于减小涡轮盘中的温度梯度。 加热气体通过与定子成一体的管道（11），并通过设置有舌片（18）和孔口（20和22）的垫圈（13）再次加热盘片，该垫圈（13）和孔口（20和22）允许气体朝向待加热区域循环 当加速首先将机器的部分靠近管道（11）加热，然后当温度均匀并且原始热膨胀变得均匀并偏移孔口（20和23）时，可以中断连通。
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公开(公告)号：US06914344B2
公开(公告)日：2005-07-05
申请号：US10619076
申请日：2003-07-15
申请人： Michel Franchet , Jean-Louis Picard
发明人： Michel Franchet , Jean-Louis Picard
CPC分类号： H02K7/1823 , F01D15/10 , F02C7/268 , F02C7/32 , H02K7/14 , Y02T50/671
摘要： The invention relates to a turbomachine of axis X including a compressor and an integrated starter/generator. The field magnetic circuit of the starter/generator is mounted in the bore of at least one disk of the compressor and surrounds the secondary magnetic circuit which is secured to a cylindrical shroud provided on the support structure for the bearing of the compressor. The invention applies in particular to single-shaft or multi-shaft turbomachines.
摘要翻译： 本发明涉及一种包括压缩机和集成起动器/发电机的轴线X的涡轮机。 起动器/发电机的磁场磁路安装在压缩机的至少一个盘的孔中，并且包围固定到设置在用于压缩机的轴承的支撑结构上的圆柱形护罩上的次级磁路。 本发明特别适用于单轴或多轴涡轮机。
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公开(公告)号：US4964127A
公开(公告)日：1990-10-16
申请号：US266961
申请日：1988-11-03
CPC分类号： H03M13/091 , H04L1/0083
摘要： A data handling system wherein data are arranged into frames including an information data section and a frame check sequence (FCS) section, and wherein a stamp section has to be appended/deleted from said frame. The stamp appending is operated without any FCS updating being required by appending to each stamp, a so called precomputed and stored anti-stamp.
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10.发明授权Turboprop carrier structure and an assembly including such a carrier structure 有权涡轮螺旋桨飞机载体结构和包括这种载体结构的组件公开(公告)号：US07100869B2
公开(公告)日：2006-09-05
申请号：US10780639
申请日：2004-02-19
申请人： Jean-Louis Picard , Georges Mazeaud
发明人： Jean-Louis Picard , Georges Mazeaud
IPC分类号： B64D27/26
摘要： The carrier structure of the invention is used for carrying a turboprop and it is designed to be mounted beneath and/or in front of an airplane wing. In characteristic manner, the carrier structure comprises: a top portion comprising a front arch, a rear arch, and longitudinal beams; an upwardly-open removable bottom portion comprising at least two bottom arches and longerons; the bottom portion being demountably fixed to the top portion by centering and fixing devices, the bottom and top portions together defining a housing suitable for receiving said turboprop, and a suspension for carrying said turboprop.
摘要翻译： 本发明的承载结构用于承载涡轮螺旋桨飞机，并且其被设计成安装在飞机机翼的正下方和/或之前。 以特征方式，载体结构包括：顶部，其包括前拱，后拱和纵梁; 向上开放的可移除的底部部分，其包括至少两个底部拱形件和长形件; 底部可通过对中和固定装置可拆卸地固定到顶部，底部和顶部一起限定适于接收所述涡卷螺旋发生器的壳体，以及用于承载所述涡桨螺旋桨的悬架。
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