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11. 发明申请

US20170138308A1 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
公开(公告)号：US20170138308A1
公开(公告)日：2017-05-18
申请号：US15420155
申请日：2017-01-31
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
IPC分类号： F02K3/06 , F02C3/04
CPC分类号： F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
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.

12. 发明申请

US20170002688A1 UNDUCTED PROPELLER TURBOSHAFT ENGINE PROVIDED WITH A REINFORCING SHELL INTEGRATING PIPE SEGMENTS 审中-公开
标题翻译：提升螺旋桨涡轮发动机提供加固壳体集成管段
公开(公告)号：US20170002688A1
公开(公告)日：2017-01-05
申请号：US15113683
申请日：2015-01-14
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Bruno Albert BEUTIN , Nuria LLAMAS CASTRO , Maria NATAL , Bruna RAMOS
IPC分类号： F01D25/26 , B64D27/16 , F01D25/12 , F02K3/072 , F02C7/20
CPC分类号： F01D25/26 , B64D27/16 , B64D2027/005 , F01D25/12 , F01D25/24 , F02C7/20 , F02K3/072 , F05D2220/323 , F05D2240/14 , F05D2240/30 , Y02T50/672
摘要： An airplane unducted propeller turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator, a reinforcing shell presenting a first attachment zone mounted on the first casing second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing, wherein the reinforcing shell further includes at least one pipe segment integrated in the wall.
摘要翻译：一种具有气体发生器和接收器的飞机未驱动的螺旋桨涡轮轴发动机，所述接收器包括承载最少一个螺旋桨的推进组件，所述发动机包括第一壳体，第二壳体和第三壳体，所述第三壳体设置在所述第一和第二壳体之间，围绕所述气体发生器的至少一部分，加强壳，其具有安装在安装在所述第二壳体上的所述第一壳体第二附接区域上的第一附接区域和设置在所述第一和第二附接区域之间并围绕所述第三壳体的壁，其中加强壳还包括集成在壁中的至少一个管段。

13. 发明申请

US20160341217A1 GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20160341217A1
公开(公告)日：2016-11-24
申请号：US15114503
申请日：2015-02-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
IPC分类号： F04D29/54 , F02C7/36 , F04D29/32
CPC分类号： F04D29/544 , F01D5/141 , F02C7/36 , F02K3/072 , F04D29/324 , F05D2220/3217 , F05D2240/122 , F05D2240/304 , F05D2260/40311 , Y02T50/672 , Y02T50/673
摘要： A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
摘要翻译：具有齿轮架构的涡轮发动机的压缩机翼型包括压力和吸力侧面，并且在径向方向上从0％跨度位置延伸到100％跨度位置。翼型件具有后缘角度和跨度位置之间的关系，其限定了对应于不减小的后缘角度的0％跨度至20％跨度的非负斜率的曲线。

14. 发明申请

US20160333709A1 RADIAL CONTROL SHAFT FOR A DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBINE ENGINE HAVING AN UNDUCTED FAN, AND A METHOD OF MOUNTING SUCH A SHAFT 审中-公开
标题翻译：用于控制具有风扇的涡轮发动机风扇叶片的设备的径向控制轴以及安装这种轴的方法
公开(公告)号：US20160333709A1
公开(公告)日：2016-11-17
申请号：US15150832
申请日：2016-05-10
申请人： SNECMA
发明人： Olivier BELMONTE , Emmanuel Pierre Dimitri Patsouris , Thomas Julien Nguyen Van
IPC分类号： F01D7/00 , F16C3/02
CPC分类号： F01D7/00 , B64C11/306 , B64D2027/005 , F02K3/072 , F04D29/323 , F05D2220/32 , F05D2260/74 , F16C3/02
摘要： The invention relates to a radial control shaft (48) for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, the shaft comprising an external portion (52) that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade (26) in order to adjust its pitch, and an internal portion (50), independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing (40) in order to pivot the shaft about a radial axis (Z-Z), and to close an oil enclosure in which said bearing is housed, the external and internal portions of the shaft being coupled to each other. The invention also relates to a method of mounting such a shaft and to a control device including such a shaft.
摘要翻译：本发明涉及一种用于控制具有未被引导的风扇的涡轮发动机的风扇叶片间距的装置的径向控制轴（48），该轴包括设计成安装在控制装置中的外部部分（52）其外部并且耦合到至少一个风扇叶片（26）以调节其间距，以及独立于外部部分设计成从控制装置的内部安装的内部部分（50）连接到负载传递轴承（40），以便使轴围绕径向轴线（ZZ）枢转，并且关闭容纳所述轴承的油封壳，所述轴的外部和内部部分与每个轴承其他。本发明还涉及将这种轴安装到包括这种轴的控制装置的方法。

15. 发明申请

US20160305281A1 GAS TURBOMACHINE INCLUDING A COUNTER-FLOW COOLING SYSTEM AND METHOD 审中-公开
标题翻译：燃气涡轮机，包括一个反流冷却系统和方法
公开(公告)号：US20160305281A1
公开(公告)日：2016-10-20
申请号：US15175576
申请日：2016-06-07
申请人： General Electric Company
发明人： Henry Grady Ballard, JR. , Kenneth Damon Black , John David Memmer
IPC分类号： F01D25/14 , F01D25/12 , F01D9/02 , F04D29/58 , F04D29/52 , F02C3/04 , F01D25/24
CPC分类号： F01D25/14 , F01D25/12 , F01D25/24 , F02C3/04 , F02C3/067 , F02C7/12 , F02C7/16 , F02K3/072 , F04D29/522 , F04D29/5826 , F05D2210/44 , F05D2250/44
摘要： A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine. The casing assembly includes an inner casing portion defining a casing volume VC and a counter-flow cooling system arranged within the inner casing portion. The counter-flow cooling system includes a plurality of ducts that collectively define a channel volume Vch. The plurality of ducts is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction. The casing volume and the channel volume define a volume ratio of about 0.0002
摘要翻译：气体涡轮机包括围绕气体涡轮机的一部分的壳体组件。壳体组件包括限定壳体体积VC的内壳部分和布置在内壳部分内的逆流冷却系统。逆流冷却系统包括共同限定通道容积Vch的多个管道。多个管道被构造和设置成沿着第一轴向方向引导冷却流体通过壳体组件，并且在与第一轴向方向相反的第二轴向方向上使冷却流体通过壳体组件返回。套管体积和通道体积定义体积比为约0.0002

16. 发明授权

US09145776B2 Retention device for a rotating blade 有权
标题翻译：旋转叶片保持装置
公开(公告)号：US09145776B2
公开(公告)日：2015-09-29
申请号：US13483460
申请日：2012-05-30
申请人： Kenneth J Mackie , David M Beaven
发明人： Kenneth J Mackie , David M Beaven
IPC分类号： F01D5/30 , F01D7/00 , F01D21/04 , F02K3/072 , B64C11/06 , F02C6/20 , B64D27/00
CPC分类号： F01D5/30 , B64C11/06 , B64D2027/005 , F01D7/00 , F01D21/045 , F02C6/206 , F02K3/072 , F05D2260/36 , Y02T50/66 , Y02T50/672 , Y02T50/673 , Y10T29/49321
摘要： A blade assembly including: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device having a root part and a hub part, the root part being located radially inwards of the hub part in a retention cavity in use, wherein at least a portion of the root part enters the retention cavity via an interlock which prevents radial separation of the root and hub in the event of a primary retention device failure.
摘要翻译：一种刀片组件，包括：可围绕轴线旋转的轮毂; 至少一个叶片具有机翼部分和根部，其中所述根部使用主保持装置联接到所述轮毂，所述主保持装置在正常使用中防止所述根部和轮毂的径向分离; 以及具有根部和轮毂部分的次要保持装置，所述根部在使用中位于保持腔中的所述轮毂部分的径向内侧，其中所述根部的至少一部分经由互锁件进入所述保持腔在主保持装置发生故障的情况下防止根部和集线器的径向分离。

17. 发明申请

US20150219014A1 DEVICE FOR THE TRANSFER OF HEAT BETWEEN A LUBRICATION PIPE AND A TURBOMACHINE BLADE PITCH ACTUATOR CONTROL HYDRAULIC PIPE 审中-公开
标题翻译：润滑管和涡轮叶片转子之间的转移装置叶片调节器控制液压管
公开(公告)号：US20150219014A1
公开(公告)日：2015-08-06
申请号：US14414343
申请日：2013-07-18
申请人： SNECMA
发明人： Olivier Belmonte , Augustin Curlier
IPC分类号： F02C7/24 , F02C9/16 , F02C7/06 , F02C3/10 , F02C3/067
CPC分类号： F02C7/24 , B64C11/306 , B64C11/308 , B64D2027/005 , F01D17/26 , F01D25/18 , F02C3/067 , F02C3/10 , F02C7/06 , F02C7/14 , F02C7/36 , F02C9/16 , F02K3/072 , F05D2210/12 , F05D2220/323 , F05D2260/213 , F05D2260/2214 , F05D2260/22141 , F05D2260/74 , F05D2270/20 , F05D2270/64 , F05D2300/172 , Y02T50/66 , Y02T50/676
摘要： An aircraft turbomachine including a lubricant circulation pipe and a hydraulic pipe for controlling an actuator for changing a pitch of blades of a propeller of the turbomachine. The assembly, integrated to a receiver of the turbomachine, further includes a mechanism forming a thermal bridge between the lubricant circulation pipe and the hydraulic pipe.
摘要翻译：一种飞机涡轮机，包括润滑剂循环管和用于控制用于改变涡轮机的螺旋桨的桨叶的桨距的致动器的液压管。集成到涡轮机的接收器的组件还包括在润滑剂循环管和液压管之间形成热桥的机构。

18. 发明申请

US20150089958A1 GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION 有权
标题翻译：具有高速低压涡轮部分的气体涡轮发动机
公开(公告)号：US20150089958A1
公开(公告)日：2015-04-02
申请号：US14568167
申请日：2014-12-12
申请人： United Technologies Corporation
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： F02C3/06 , F02C3/04 , F02C7/36 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/072 , F05D2220/3215
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.
摘要翻译：燃气涡轮发动机包括非常高速的低压涡轮机，使得由低压涡轮机的出口面积所规定的数量乘以低压涡轮转速的平方，与高压涡轮机的相同参数相比是在在约0.5和约1.5之间。

19. 发明授权

US08985946B2 Mounting system 有权
标题翻译：安装系统
公开(公告)号：US08985946B2
公开(公告)日：2015-03-24
申请号：US13483461
申请日：2012-05-30
申请人： Kenneth F. Udall , Alexander V. Lavrenko
发明人： Kenneth F. Udall , Alexander V. Lavrenko
IPC分类号： F01D7/00 , F01D21/00 , F01D5/30 , F02K3/072 , B64C11/30 , B64D27/00
CPC分类号： F01D5/30 , B64C11/306 , B64D2027/005 , F01D7/00 , F02C6/206 , F02K3/072 , Y02T50/66
摘要： A mounting system for mounting a blade to a rotor body includes a pitch control mechanism including an anchor and a pitch change rod extending radially outwardly from the anchor to join to a base of the blade. The anchor and the rod are rotatable about the longitudinal axis of the rod to vary the blade pitch. The pitch control mechanism further includes a torque-transmitting formation between the blade and the anchor such that pitch-varying torque can be transmitted to the blade through the torque-transmitting formation while allowing relative radial movement between the blade and the anchor. The system includes a primary bearing formation, which transmits blade centrifugal loads to the rotor body while accommodating variation of the blade pitch, and secondary bearing formation, which transmits pitch change mechanism centrifugal loads to the rotor body while accommodating rotation of the anchor and the rod during variation of the blade pitch.
摘要翻译：用于将叶片安装到转子主体的安装系统包括俯仰控制机构，其包括锚固件和从锚固件径向向外延伸以连接到叶片的基部的变桨杆。锚杆和杆可围绕杆的纵向轴线旋转以改变叶片间距。俯仰控制机构还包括在叶片和锚之间的转矩传递结构，使得桨距变化转矩可以通过扭矩传递构件传递到叶片，同时允许叶片和锚之间的相对径向移动。该系统包括主轴承结构，其将叶片离心载荷传递到转子本体同时容纳叶片间距的变化，以及次级轴承形成，其将桨距变化机构的离心载荷传递到转子本体，同时容纳锚和杆的旋转在叶片间距的变化期间。

20. 发明授权

US08984891B2 Flade discharge in 2-D exhaust nozzle 有权
标题翻译：二维排气喷嘴中的闪光放电
公开(公告)号：US08984891B2
公开(公告)日：2015-03-24
申请号：US12982265
申请日：2010-12-30
申请人： Erin Lee Lariviere , Stephen Michael Ettorre
发明人： Erin Lee Lariviere , Stephen Michael Ettorre
IPC分类号： F02K1/00 , F02K1/82 , F02C9/20 , F02K1/08 , F02K1/10 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/10 , F02K7/16
CPC分类号： F02K1/82 , F02C9/20 , F02K1/06 , F02K1/08 , F02K1/09 , F02K1/10 , F02K1/30 , F02K3/062 , F02K3/065 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/08 , F02K3/10 , F02K7/16
摘要： An aircraft gas turbine engine has a row of FLADE fan blades disposed radially outwardly of and drivingly connected to a fan in the engine's fan section. The FLADE fan blades extend across a FLADE duct circumscribing the fan section. A two dimensional air discharge passage is in fluid flow communication with the FLADE duct and with FLADE air upstream and downstream discharge slots in a divergent flap of a two dimensional exhaust nozzle. A valve fully closes the upstream slot when the downstream slot is fully opened and fully opens the upstream slot when the downstream slot is fully closed. The upstream and downstream slots may be located upstream and downstream respectfully of a nozzle discharge area in the nozzle. A sliding deck slides aft or down to open upstream slot and close downstream slot and slides forward or up to close upstream slot and open downstream slot.
摘要翻译：飞机燃气涡轮发动机具有一排FLADE风扇叶片，其设置在发动机风扇部分中的径向向外并与风扇连接。 FLADE风扇叶片延伸穿过限制风扇部分的FLADE风管。二维空气排放通道与FLADE管道流体流动连通，并且具有FLADE空气上游和下游排放槽，位于二维排气喷嘴的发散阀瓣中。当下游槽完全打开时，阀完全关闭上游槽，当下游槽完全关闭时，阀完全打开上游槽。上游和下游槽可以相对于喷嘴中的喷嘴排放区域位于上游和下游。滑动台面向下滑动以打开上游槽，并关闭下游槽，向前或向上滑动以关闭上游槽并打开下游槽。

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