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1. 发明授权

US09616629B2 Blade having an integrated composite spar 有权
公开(公告)号：US09616629B2
公开(公告)日：2017-04-11
申请号：US13732884
申请日：2013-01-02
申请人： SNECMA
发明人： Adrien Jacques Philippe Fabre , Nicolas Horn , David Marsal , Jean-Marc Claude Perrollaz
IPC分类号： F01D5/28 , B64C11/26 , B29D99/00 , B29C70/22 , B29C70/24 , F04D29/02 , F04D29/32 , F04D29/38 , F01D5/14 , D03D25/00 , B64C27/473
CPC分类号： B29D99/0025 , B29C70/222 , B29C70/24 , B64C11/26 , B64C2027/4736 , D03D25/005 , F01D5/141 , F01D5/282 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2300/224 , F05D2300/6033 , F05D2300/6034 , F05D2300/702 , Y02T50/43 , Y02T50/672 , Y02T50/673
摘要： A blade including a structure with aerodynamic profile including two opposite skins obtained by three-dimensional weaving of a fibrous reinforcement densified by a matrix, and a longeron including a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, the longeron including a first part extending outside the structure with aerodynamic profile and designed to be connected to a drive hub in rotation of the blade and a second part arranged inside the structure with aerodynamic profile between the two skins. The second part of the longeron has a thickness substantially similar to that of the skins of the structure with aerodynamic profile. In addition, the fibrous reinforcement of the second part of the longeron has the same weaving armor as that of the reinforcement of the skins of the structure with aerodynamic profile.

2. 发明授权

US09435209B2 Turbomachine blade reinforcement 有权
标题翻译：涡轮机叶片加固
公开(公告)号：US09435209B2
公开(公告)日：2016-09-06
申请号：US13660989
申请日：2012-10-25
申请人： General Electric Company
发明人： Andres Jose Garcia Crespo
IPC分类号： F01D5/14 , F01D5/28
CPC分类号： F01D5/147 , F01D5/282 , F01D5/284 , F05D2260/941 , F05D2300/6033 , F05D2300/702 , Y02E20/16 , Y02T50/672 , Y10T29/49337
摘要： Embodiments of the present disclosure include a system having a turbomachine blade segment including a blade and a mounting segment coupled to the blade, wherein the mounting segment has a plurality of reinforcement pins laterally extending at least partially through a neck of the mounting segment.
摘要翻译：本公开的实施例包括具有涡轮机叶片段的系统，其包括叶片和联接到叶片的安装段，其中安装段具有至少部分地横向延伸穿过安装段的颈部的多个加强销。

3. 发明授权

US09409650B2 Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section 有权
标题翻译：推力反向器支撑结构包括复合增强件和具有未闭合截面的基座
公开(公告)号：US09409650B2
公开(公告)日：2016-08-09
申请号：US13516759
申请日：2010-12-09
申请人： Alexandre Bellanger , Florent Bouillon , Laurent Dubois
发明人： Alexandre Bellanger , Florent Bouillon , Laurent Dubois
IPC分类号： B64D29/06 , F02K1/72 , B64D27/18
CPC分类号： B64D29/06 , B64D27/18 , F02K1/72 , F05D2260/30 , F05D2300/603 , F05D2300/702 , Y02T50/672
摘要： An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.
摘要翻译：飞机机舱包括：具有可移动整流罩的推力反向装置和支撑推力反向装置的支撑结构。支撑结构包括：沿着机舱的纵向延伸并由复合材料制成的基体和基体的壁，其形成具有开口部分的未闭合的横截面以提供到支撑结构的内表面的通路以及多个由复合材料制成的增强件，并且沿纵向安装在内表面上。特别地，增强件集成在支撑结构的内表面中。

4. 发明申请

US20160177831A1 COOLING-AIR SUPPLY DEVICE FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮机的冷却空气供应装置
公开(公告)号：US20160177831A1
公开(公告)日：2016-06-23
申请号：US14972767
申请日：2015-12-17
申请人： MTU Aero Engines AG
发明人： Stefan Sasse , Erwin Bayer
IPC分类号： F02C7/18 , F01D25/24 , F01D5/02 , F02C3/04
CPC分类号： F02C7/18 , F01D5/02 , F01D5/082 , F01D25/24 , F02C3/04 , F05D2220/3213 , F05D2230/54 , F05D2240/35 , F05D2240/61 , F05D2260/14 , F05D2260/20 , F05D2260/201 , F05D2300/6033 , F05D2300/702 , Y02T50/672 , Y02T50/676
摘要： A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer.
摘要翻译：一种用于燃气轮机的冷却空气供应装置，特别是包括冷却空气室的飞机燃气轮机，其设置在燃气轮机的涡轮机轴周围，至少一个冷却空气入口，以及至少一个冷却出口孔; 所述冷却空气供应装置具有第一和第二轴向边界壁，以及连接两个轴向边界壁的周壁，所述两个轴向边界壁一起形成冷却空气室; 在轴向边界壁中的至少一个中，设置有多个冷却空气出口孔，其周向分布在涡轮轴上并且适于允许冷却空气基本上从单独的冷却空气出口孔排出燃气轮机的旋转方向。在轴向方向上，具有冷却空气出口孔的相应轴向边界壁具有层型结构; 所述冷却空气出口孔由至少一个第一冷却空气室侧层的变形和至少一个第二涡轮机侧层的变形形成。

5. 发明授权

US09199345B2 Method for producing a metal reinforcement for a turbine engine blade 有权
标题翻译：一种用于涡轮发动机叶片的金属加强件的制造方法
公开(公告)号：US09199345B2
公开(公告)日：2015-12-01
申请号：US13518179
申请日：2010-12-22
申请人： Thierry Jean Emile Flesch , Jean-Franøois Fromentin , Stéphane André Leveque , Laetitia Sanchez
发明人： Thierry Jean Emile Flesch , Jean-Franøois Fromentin , Stéphane André Leveque , Laetitia Sanchez
IPC分类号： B23P15/04 , B22F3/105 , B22F5/00 , B23K15/00 , B23K37/047 , C22C14/00 , F01D5/14 , F01D5/28 , F04D29/32 , B22F3/24 , B29C65/00 , B29L31/08 , B29C65/48
CPC分类号： B23P15/04 , B22F3/1055 , B22F5/009 , B22F2003/247 , B22F2003/248 , B22F2998/10 , B23K15/006 , B23K37/047 , B23K2101/001 , B29C65/48 , B29C65/483 , B29C65/484 , B29C66/12461 , B29C66/12463 , B29C66/301 , B29C66/53 , B29C66/721 , B29C66/742 , B29L2031/08 , B29L2031/082 , B33Y80/00 , C22C14/00 , F01D5/147 , F01D5/282 , F04D29/324 , F05D2230/234 , F05D2230/236 , F05D2240/121 , F05D2240/303 , F05D2300/702 , Y02P10/295 , Y10T29/49318 , Y10T29/49826 , Y10T29/4998 , B23K1/00 , B22F3/168 , B22F3/24
摘要： A method for creating a metal reinforcement for a leading or trailing edge of a turbine engine blade including a reinforcement foot and head, the method including: creating a plurality of V-shaped tapered elements that form different parts of the metal reinforcement so that the metal reinforcement is divided into a plurality of parts distributed between the foot and the head; positioning the parts on equipment that is shaped like the leading or trailing edge of the turbine engine blade; and rigidly connecting the different parts so as to form the complete profile of the one-piece metal reinforcement the by recombining the different parts.
摘要翻译：一种用于产生包括加强脚和头部的涡轮发动机叶片的前缘或后缘的金属加强件的方法，所述方法包括：形成多个V形锥形元件，其形成所述金属加强件的不同部分，使得所述金属加强件被分为在脚部和头部之间分布的多个部件; 将部件定位在类似于涡轮发动机叶片的前缘或后缘的设备上; 并刚性地连接不同的部件，以便通过重新组合不同的部件来形成一体式金属加强件的完整轮廓。

6. 发明授权

US09140131B2 Methods for controlling friction between heterogeneous contact surfaces 有权
标题翻译：控制非均匀接触表面摩擦的方法
公开(公告)号：US09140131B2
公开(公告)日：2015-09-22
申请号：US13445278
申请日：2012-04-12
申请人： Alison J McMillan
发明人： Alison J McMillan
IPC分类号： F01D5/30 , B23P9/00 , B24B19/14 , B24B15/08 , B24B19/06
CPC分类号： F01D5/3007 , B23P9/00 , B24B15/08 , B24B19/06 , B24B19/14 , F05D2230/90 , F05D2250/621 , F05D2260/941 , F05D2300/702 , Y10T29/49316 , Y10T29/49336
摘要： A method of conditioning a first, heterogeneous contact surface for operational engagement with a second contact surface, the method comprising: performing a smoothing operation on part or all of the first contact surface while subjecting said part or all of the first contact surface respectively to a contact pre-stress corresponding to a nominal operational contact stress between the first and second contact surfaces.
摘要翻译：一种调节第一非均匀接触表面以与第二接触表面操作接合的方法，所述方法包括：对所述第一接触表面的部分或全部进行平滑处理，同时将所述部分或全部所述第一接触表面分别接触对应于第一和第二接触表面之间的标称操作接触应力的预应力。

7. 发明申请

US20150198056A1 ABRADABLE SEAL HAVING NANOLAYER MATERIAL 审中-公开
标题翻译：具有纳米材质的不可剥离密封
公开(公告)号：US20150198056A1
公开(公告)日：2015-07-16
申请号：US14592196
申请日：2015-01-08
申请人： United Technologies Corporation
发明人： Shahram Amini , Christopher W. Strock
IPC分类号： F01D11/12 , C08K3/04
CPC分类号： F01D11/122 , C08K3/04 , F01D11/125 , F05D2220/36 , F05D2230/90 , F05D2300/224 , F05D2300/226 , F05D2300/43 , F05D2300/437 , F05D2300/5024 , F05D2300/702 , Y02T50/672
摘要： A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon. An abradable seal circumscribes the blades and includes a polymeric matrix with a dispersion of a nanolayer material.
摘要翻译：燃气涡轮发动机包括多个周向间隔开的叶片。叶片在其上具有聚合物涂层。可磨损的密封件围绕叶片并且包括具有纳米层材料的分散体的聚合物基质。

8. 发明申请

US20150175272A1 REINFORCED PRIMARY STRUCTURE FOR AN ATTACHMENT PYLON 有权
标题翻译：加固PYLON的主要结构
公开(公告)号：US20150175272A1
公开(公告)日：2015-06-25
申请号：US14573447
申请日：2014-12-17
申请人： Airbus Operations (S.A.S.)
发明人： Wolfgang Brochard , Sébastien Alby , David Ewens
IPC分类号： B64D45/00 , B64D27/26
CPC分类号： B64D45/00 , A62C2/065 , A62C3/08 , B64D27/26 , B64D2045/009 , F02C7/20 , F02C7/25 , F05D2300/702 , Y02T50/672
摘要： The disclosure herein relates to a structural element for an aircraft comprising a portion of an attachment pylon primary structure. According to the disclosure herein, the attachment pylon primary structure portion is at least partially covered by a protective assembly comprising a layer forming a firewall and a thermally insulating layer, thermally insulating layer being located between the layer forming a firewall and the attachment pylon primary structure portion.
摘要翻译：本文的公开内容涉及用于飞行器的结构元件，其包括附接塔一级结构的一部分。根据本文的公开内容，附接塔主结构部分至少部分地被包括形成防火墙的层和绝热层的保护组件覆盖，隔热层位于形成防火墙的层与附接塔一级结构之间一部分。

9. 发明授权

US08906181B2 Fan blade finishing 有权
标题翻译：风扇叶片整理
公开(公告)号：US08906181B2
公开(公告)日：2014-12-09
申请号：US13173738
申请日：2011-06-30
申请人： James O. Hansen, Sr. , Jesse Meyer , Christopher J. Hertel
发明人： James O. Hansen, Sr. , Jesse Meyer , Christopher J. Hertel
IPC分类号： B44C3/08 , B44C5/04 , B29C65/00 , B31B1/60 , B32B37/00 , B63H1/26 , B63H7/02 , B64C11/16 , B64C27/46 , F01D5/14 , F03B7/00 , F03D11/02 , F04D29/38 , B64C11/24 , F01D5/18 , F03B3/12 , B32B5/12 , B32B1/00 , B32B3/00 , B32B9/00 , B32B15/04 , B32B5/18 , B23P9/04 , F01D5/28 , F04D29/02 , F04D29/32
CPC分类号： F01D5/147 , B23P9/04 , C21D7/06 , C22F1/04 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2230/23 , F05D2230/90 , F05D2240/303 , F05D2300/702 , Y02T50/672 , Y10T156/10 , Y10T156/1002 , Y10T156/1039 , Y10T156/1041 , Y10T428/12479 , Y10T428/24124 , Y10T428/24628
摘要： A method of finishing a fan blade includes bonding a sheath and a cover to an aluminum fan blade with an airfoil, a root, a leading edge and a tip; imparting residual stresses onto the blade; coating the blade to protect exposed areas of the blade; and curing the blade in low-temperature cure cycles to preserve residual stresses imparted.
摘要翻译：一种完成风扇叶片的方法包括：用翼型件，根部，前缘和尖端将护套和盖子粘合到铝制风扇叶片上; 在刀片上施加残余应力; 涂覆刀片以保护刀片的暴露区域; 并在低温固化循环中固化刀片以保持施加的残余应力。

10. 发明授权

US08814528B2 Production method of leading edge reinforcement of fan blade 有权
标题翻译：风扇叶片前缘加固的生产方法
公开(公告)号：US08814528B2
公开(公告)日：2014-08-26
申请号：US13145350
申请日：2010-01-22
申请人： Takayuki Iwasaki
发明人： Takayuki Iwasaki
IPC分类号： B21D26/049 , B23P15/02
CPC分类号： B21D53/78 , B21D26/049 , B21D26/055 , B23P15/04 , F01D5/147 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2230/10 , F05D2230/23 , F05D2240/303 , F05D2300/702 , Y02T50/673 , Y10T29/49336 , Y10T29/49805
摘要： A production method enables use of ultrasonic forming but does not leave a bonding face in a final product.One cuts into a plate member having a first side face and a second side face from the first side face toward the second side face to form a slit that does not reach the second side face; seals lips of the slit to leave an opening; causes superplastic forming of the plate member by pressurizing the plate member in a mold with gas through the opening; and cuts out a portion including the sealed lips.
摘要翻译：一种制造方法能够使用超声波成形，但不会在最终产品中留下接合面。一个切割成具有从第一侧面朝向第二侧面的第一侧面和第二侧面的板构件，以形成不到达第二侧面的狭缝; 密封狭缝的嘴唇留下开口; 通过使气体通过开口对模具中的板构件加压来引起板构件的超塑性成形; 并切出包括密封唇部的部分。

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