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21. 发明申请

US20150000252A1 ROTATIONAL ANNULAR AIRSCREW WITH INTEGRATED ACOUSTIC ARRESTER 有权
标题翻译：具有集成声学ARRESTER的旋转环形空气
公开(公告)号：US20150000252A1
公开(公告)日：2015-01-01
申请号：US13674377
申请日：2012-11-12
申请人： Matthew D. Moore , Kelly L. Boren
发明人： Matthew D. Moore , Kelly L. Boren
IPC分类号： F02K5/00 , F02K1/44
CPC分类号： F02K5/00 , B64C11/001 , B64C11/18 , F01D1/24 , F01D5/03 , F01D5/225 , F02K1/44 , F02K1/827 , F02K3/062 , F02K3/072 , F04D29/326 , F05D2260/96 , Y02T50/672 , Y02T50/673 , Y10T137/0536
摘要： A propulsion system and methods are presented. A substantially tubular structure comprises a central axis through a longitudinal geometric center, and a first fan rotates around the central axis, and comprises a first fan hub and first fan blades. The fan hub is rotationally coupled to the substantially tubular structure, and the first fan blades are coupled to the first fan hub and increase in chord length with increasing distance from the first fan hub. A second fan is rotationally coupled to the substantially tubular structure and rotates around the central axis and contra-rotates relative to the first fan. Second fan blades are coupled to the second fan hub, and a nacelle circumscribing the first fan and the second fan is coupled to and rotates with the first fan.
摘要翻译：提出了推进系统和方法。基本上管状结构包括通过纵向几何中心的中心轴线，第一风扇围绕中心轴线旋转，并且包括第一风扇轮毂和第一风扇叶片。风扇轮毂旋转地联接到基本上管状的结构，并且第一风扇叶片联接到第一风扇轮毂并随着与第一风扇轮毂的距离增加而增加弦长。第二风扇旋转地联接到基本上管状的结构并围绕中心轴线旋转并相对于第一风扇反转。第二风扇叶片联接到第二风扇轮毂，并且包围第一风扇和第二风扇的机舱联接到第一风扇并与第一风扇一起旋转。

22. 发明申请

US20140105737A1 GAS TURBINE ENGINE COMPRISING THREE ROTARY BODIES 有权
标题翻译：包含三个旋转体的气体涡轮发动机
公开(公告)号：US20140105737A1
公开(公告)日：2014-04-17
申请号：US14122777
申请日：2012-05-31
申请人： Philippe Gerard Chanez , Lamine M'Bengue
发明人： Philippe Gerard Chanez , Lamine M'Bengue
IPC分类号： F02C7/04
CPC分类号： F02C7/04 , F02C3/067 , F02K3/06 , F02K3/072 , F05D2220/3213 , F05D2220/323 , Y02T50/671
摘要： A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade.
摘要翻译：一种用于推进飞机的燃气涡轮发动机，包括包括低压涡轮转子叶片的低压旋转体，包括中间涡轮转子叶片的中间旋转体，包括高压涡轮转子叶片的高压旋转体，流过发动机从上游到下游。所述至少一个中间涡轮机转子叶片直接通过低压涡轮转子叶片在下游，以便使由中间涡轮转子叶片偏转的空气流伸直。

23. 发明申请

US20140003916A1 TURBOMACHINE WITH FAN(S) FOR AIRCRAFT, WITH MOBILE JET NOZZLE 有权
标题翻译：具有风扇的涡轮机，用于具有移动喷嘴喷嘴的飞机
公开(公告)号：US20140003916A1
公开(公告)日：2014-01-02
申请号：US14004713
申请日：2012-03-14
申请人： Sebastien Dron , Nicolas Jerome Jean Tantot
发明人： Sebastien Dron , Nicolas Jerome Jean Tantot
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , B64D2027/005 , F02K1/09 , F02K1/763 , F02K3/025 , F02K3/072 , F02K3/075 , F05D2300/505 , Y02T50/66
摘要： A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.
摘要翻译：一种用于飞行器的涡轮机，包括至少一个涡轮机驱动风扇的旋转，以及喷射喷嘴，其同轴地延伸涡轮机并且产生具有终止涡轮机的出口锥体，用于通过涡轮机的燃烧气体的环形横截面通道。喷嘴可以安装成使得其可以在控制器的作用下的两个极限位置之间移动，气体通道的环形截面分别处于其最小或最大值，使得可以根据到飞机的运行阶段并在风扇和喷嘴之间分配推力。

24. 发明申请

US20130224003A1 GAS TURBINE ENGINE WITH FAN-TIED INDUCER SECTION 有权
标题翻译：具有风扇电感器部分的气体涡轮发动机
公开(公告)号：US20130224003A1
公开(公告)日：2013-08-29
申请号：US13406819
申请日：2012-02-28
申请人： Daniel Bernard Kupratis , Frederick M. Schwarz
发明人： Daniel Bernard Kupratis , Frederick M. Schwarz
IPC分类号： F01D1/04
CPC分类号： F01D15/12 , F02C7/047 , F02C7/36 , F02K3/072 , F05D2260/40311
摘要： A gas turbine engine includes a shaft, a speed change device driven by the shaft, and a fan including a fan rotor driven by the speed change device. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.
摘要翻译：燃气涡轮发动机包括轴，由轴驱动的变速装置和包括由变速装置驱动的风扇转子的风扇。至少一个诱导器台被定位在风扇的后面，并被联接成与风扇转子一起旋转。

25. 发明申请

US20130223993A1 COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 有权
标题翻译：带齿轮系统的逆转低压涡轮机安装在涡轮机排气箱
公开(公告)号：US20130223993A1
公开(公告)日：2013-08-29
申请号：US13408301
申请日：2012-02-29
申请人： Brian D. Merry , Gabriel L. Suciu
发明人： Brian D. Merry , Gabriel L. Suciu
IPC分类号： F01D25/00 , F01D25/24
CPC分类号： F01D15/12 , F01D1/24 , F01D25/162 , F01D25/30 , F02C3/107 , F02C7/32 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
摘要翻译：燃气涡轮发动机包括限定旋转轴线的轴。外转子直接驱动轴并且包括一组外部叶片。内转子具有与外组叶片交替散布的内组叶片。内转子构造成围绕与外转子的旋转轴线相反的方向旋转。齿轮系统将内转子连接到轴，并且构造成以比外部组叶片更快的速度旋转内组叶片。

26. 发明申请

US20130219908A1 GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY 审中-公开
标题翻译：用于改进扭矩密度的齿轮涡轮机结构
公开(公告)号：US20130219908A1
公开(公告)日：2013-08-29
申请号：US13483406
申请日：2012-05-30
申请人： Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu
发明人： Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu
IPC分类号： F02C3/10
CPC分类号： F01D25/162 , F02C3/107 , F02K3/072 , F05D2260/40311
摘要： A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.
摘要翻译：涡轮发动机包括风扇，具有低压压缩机部分和高压压缩机部分的压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。涡轮部分包括低压涡轮部分和高压涡轮部分。低压压缩机部分，低压涡轮部分和风扇沿第一方向旋转，而高压压缩机部分和高压涡轮部分沿与第一方向相反的第二方向旋转。

27. 发明申请

US20130192263A1 GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION 审中-公开
公开(公告)号：US20130192263A1
公开(公告)日：2013-08-01
申请号：US13410776
申请日：2012-03-02
申请人： Gabriel L. Suciu , Frederick M. Schwarz , William K. Ackermann , Daniel Bernard Kupratis
发明人： Gabriel L. Suciu , Frederick M. Schwarz , William K. Ackermann , Daniel Bernard Kupratis
IPC分类号： F02C3/06
CPC分类号： F02K3/072
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

28. 发明申请

US20130115083A1 TURBINE ENGINE HAVING TWO UNDUCTED PROPELLERS 审中-公开
标题翻译：具有两台发动机的涡轮发动机
公开(公告)号：US20130115083A1
公开(公告)日：2013-05-09
申请号：US13810833
申请日：2011-07-13
申请人： Alexandre Alfred, Gaston Vuillemin
发明人： Alexandre Alfred, Gaston Vuillemin
IPC分类号： F04D19/02
CPC分类号： F04D19/024 , B64C11/003 , B64C11/06 , B64C11/306 , B64C11/48 , B64D2027/026 , F02K3/072 , F04D29/324 , F04D29/362 , F04D29/666 , Y02T50/66
摘要： A turbine engine including two outer coaxial counter-rotating unducted propellers, of an upstream propeller and a downstream propeller, respectively. The blades of the downstream propeller are retractable in the lengthwise direction thereof so as to reduce the diameter of the propeller. The reduction in the diameter of the downstream propeller makes it possible to reduce noise caused by vortices generated by the upstream propeller.
摘要翻译：一种涡轮发动机，分别包括上游螺旋桨和下游螺旋桨的两个外部同轴反向旋转的未被牵引的螺旋桨。下游螺旋桨的叶片在其长度方向可缩回，以减小螺旋桨的直径。下游螺旋桨的直径的减小使得可以减少由上游螺旋桨产生的涡流引起的噪声。

29. 发明授权

US08375698B2 Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine 有权
标题翻译：一种用于降低涡轮发动机反转叶片盘的振动水平的方法
公开(公告)号：US08375698B2
公开(公告)日：2013-02-19
申请号：US12548040
申请日：2009-08-26
申请人： Jean-Pierre Francois Lombard , Jerome Talbotec
发明人： Jean-Pierre Francois Lombard , Jerome Talbotec
IPC分类号： F01D25/04 , F02K3/072 , B21K25/00
CPC分类号： F01D5/16 , F01D5/142 , F02K3/072 , F05D2200/20 , F05D2260/80 , F05D2260/96 , Y10T29/49321
摘要： A method for reducing the vibration levels likely to occur, in a turbine engine including a first and a second bladed disk forming a propfan of contrarotating disks, when the two disks are traversed by a gaseous fluid, because of the turbulence of aerodynamic origin generated by the second bladed disk on the first bladed disk is disclosed. The method includes defining an initial configuration of the blades, calculating the synchronous forced response on the first bladed disk as a function of the harmonic excitation force generated by the second bladed disk expressed as a linear function of the generalized aerodynamic force for the mode in question; for stacked sections of one of the two disks, determining a tangential geometric offset value θ of the individual aerodynamic profile to reduce the term corresponding to the generalized aerodynamic force; and applying a new configuration to the blades.
摘要翻译：一种用于减少可能发生的振动水平的方法，在涡轮发动机中，由于由气态流体产生的空气动力学原因的湍流，在涡轮发动机中，该涡轮发动机包括形成反转盘的螺旋桨的第一和第二叶片盘，披露了第一个刀片盘上的第二个刀片盘。该方法包括定义叶片的初始配置，根据第二叶片盘产生的谐波激励力计算第一叶片盘上的同步强制响应，其表示为所讨论模式的广义气动力的线性函数 ; 对于两个磁盘之一的堆叠部分，确定切向几何偏移值＆amp; 的个体空气动力学特性，以减少对应于广义气动力的术语; 并将新配置应用于刀片。

30. 发明申请

US20130028712A1 GAS TURBINE ENGINE SYSTEMS INVOLVING TIP FANS 有权
标题翻译：涉及风机的气体涡轮发动机系统
公开(公告)号：US20130028712A1
公开(公告)日：2013-01-31
申请号：US13452368
申请日：2012-04-20
申请人： Gary D. Roberge , Gabriel L. Suciu
发明人： Gary D. Roberge , Gabriel L. Suciu
IPC分类号： F01D15/12
CPC分类号： F02K3/077 , F02C7/36 , F02K3/072 , F05D2260/40311
摘要： Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades defining an inner fan and a tip fan and being located downstream of the first set of rotatable blades; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades.
摘要翻译：提供了涉及尖端风扇的燃气涡轮发动机系统。在这方面，代表性的燃气涡轮发动机系统包括：多级风扇，具有第一可转动的叶片组和第二可反向旋转的叶片组，第二可旋转叶片限定内部风扇和顶端风扇，位于第一组可旋转叶片的下游; 以及行星差速齿轮组件，其操作以接收扭矩输入并且差分地施加到第一组叶片和第二组叶片的扭矩输入。

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