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21. 发明专利

JP4625049B2 How to repair a part of the composite material, and components of the composite structure 有权
公开(公告)号：JP4625049B2
公开(公告)日：2011-02-02
申请号：JP2007156529
申请日：2007-06-13
申请人：ユナイテッドテクノロジーズコーポレイションUnited Technologies Corporation
发明人：ボーグウイリアム , ビー．リングラーリチャード
IPC分类号： F02C7/00 , B23P6/00 , F01D11/08 , F02C7/045 , F02C7/28
CPC分类号： B29C73/06 , B29C73/10 , B29L2031/608 , Y10T156/1056 , Y10T156/1082 , Y10T403/41 , Y10T403/66 , Y10T428/236 , Y10T428/24149 , Y10T428/24157
摘要： A method of restoring a section of a composite (20) includes the steps of removing an undesirable section (28) of a composite and securing a repair section (30) in the location of the removed undesirable section (28). One or more covers (32) are secured on at least a portion the repair section (30) to prevent or resist peeling of the repair section (30).

22. 发明专利

JP2010523878A Creating a system durability muffling structure, it due to durability mute structure and the coating material to take advantage of this kind of structure 有权
公开(公告)号：JP2010523878A
公开(公告)日：2010-07-15
申请号：JP2010501567
申请日：2008-03-28
申请人：エアバスフランス
发明人：マルクポイグノネック，ジーン , クリストフボシス，ジーン , メニエル，クリストフ , ララネ，ジャクエス
IPC分类号： F02C7/045 , B64D33/02 , F01D25/00 , F02C7/00 , F02C7/24 , G10K11/16
CPC分类号： G10K11/172 , F02C7/045 , F02C7/24 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T156/1056
摘要：【課題】本発明の目的は、消音処理のための被覆材を得るために蜂窩状構造体上に取り付けられる、耐久性消音構造体の作成方式であり、
【解決手段】同耐久性消音構造体が、接着によって結合された、少なくとも１つの多孔性層（３４）および補強用構造体（３６）を含んでおり、
― 少なくとも１つの同補強用構造体（３６）上に非晶質型接着剤を付着させ、
― 非晶質型接着剤の付着後、補強用構造体（３６）を穿孔または微細穿孔し、
― 非晶質型接着剤で被覆した補強用構造体（３６）の表面に、少なくとも１つの同多孔性層を付着させることを特徴とする。
【選択図】図６Ｃ

23. 发明专利

JP2009024697A Damping device for stator of turbo machine 有权
标题翻译：涡轮机定子的阻尼装置
公开(公告)号：JP2009024697A
公开(公告)日：2009-02-05
申请号：JP2008165446
申请日：2008-06-25
申请人： Snecma , スネクマ
发明人： BAUMHAUER STEPHANE JEAN JOSEPH , DUPEUX JEROME ALAIN , GARCIN FRANCOIS MAURICE , LOMBARD JEAN-PIERRE FRANCOIS
IPC分类号： F01D9/02 , F01D5/28 , F01D25/00 , F01D25/06 , F02C7/00 , F02C7/045 , F02C7/24 , F04D29/54 , F04D29/66
CPC分类号： F16F9/306 , F01D9/041 , F01D25/04 , F01D25/246 , F05D2260/96 , Y02T50/67 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To attenuate a dynamic response of a structure (regardless of whether it is pneumatics in origin or not) under synchronous stress or asynchronous stress by applying dynamic attenuation.
SOLUTION: This stator of a turbo machine forms a stator blade ring or an upstream-side guide blade member, and the stator blade ring is constituted by radially arranging a plurality of blades (43) between two concentric rings, namely a first inner ring (42) and a second outer ring (44). The second ring of the stator has a cylindrical outer surface (44e). At least one of vibration-damping layer bodies (30, 30') in which at least one layer (32) formed of a viscoelastic material is brought into contact with the surface (44e) and one counter layer (34) formed of a rigid material are attached to the outer surface (44e) of the stator.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：通过应用动态衰减，在同步应力或异步应力下，衰减结构的动态响应（无论是否为气源原理）。解决方案：涡轮机的该定子形成定子叶片环或上游侧引导叶片构件，并且定子叶片环通过在两个同心环之间径向布置多个叶片（43）而构成，即第一内环（42）和第二外环（44）。定子的第二环具有圆柱形外表面（44e）。至少一个振动阻尼层体（30,30'），其中由粘弹性材料形成的至少一层（32）与表面（44e）接触，并且一个反应层（34）由刚性材料附接到定子的外表面（44e）。版权所有（C）2009，JPO＆INPIT

24. 发明专利

JP2008121682A Turbofan engine cowl assembly and thrust reverser assembly 有权
标题翻译：涡轮发动机组件和扭矩组件
公开(公告)号：JP2008121682A
公开(公告)日：2008-05-29
申请号：JP2007290253
申请日：2007-11-08
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SEDA JORGE FRANCISCO , MONIZ THOMAS ORY , ORLANDO ROBERT JOSEPH , STUART ALAN ROY , SCHEFFEL KENNETH S
IPC分类号： F02K1/70 , F02C7/045 , F02C7/24 , F02K1/44 , F02K3/06
CPC分类号： F02K1/72
摘要： PROBLEM TO BE SOLVED: To provide a thrust reserver assembly (100) for a turbofan engine assembly (10).
SOLUTION: The engine assembly (10) includes a core gas turbine engine (20), a core cowl (22) which circumscribes the core gas turbine engine (20), a nacelle (24) positioned radially outward from the core cowl (22), a fan nozzle duct (26) having an area defined between the core cowl (22) and a portion of the nacelle (24), and the thrust reverser assembly (100) positioned within a portion of the nacelle (24). The thrust reverser assembly (100) includes a first cowl (104), a second cowl (102) repositionable with respect to the first cowl (104) for varying the area of the fan nozzle duct (26), and at least one flow directing member (133, 137) coupled to the second cowl (102) to selectively impede airflow from flowing through a cavity defined between the first cowl (104) and the second cowl (102).
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于涡轮风扇发动机组件（10）的推力保持器组件（100）。解决方案：发动机组件（10）包括核心燃气涡轮发动机（20），围绕核心燃气涡轮发动机（20）的核心整流罩（22），从核心整流罩径向向外定位的机舱（22），具有限定在所述核心整流罩（22）和所述机舱（24）的一部分之间的区域的风扇喷嘴管道（26）和位于所述机舱（24）的一部分内的推力反向器组件（100）。推力反向器组件（100）包括第一整流罩（104），相对于第一整流罩（104）可重新定位的第二整流罩（102），用于改变风扇喷嘴管道（26）的面积，以及至少一个导流联接到第二整流罩（102）的构件（133,137）以选择性地阻止气流流过限定在第一整流罩（104）和第二整流罩（102）之间的空腔。版权所有（C）2008，JPO＆INPIT

25. 发明专利

JP2008121670A Swept turbomachine blade 有权
标题翻译： SWEPT涡轮叶片
公开(公告)号：JP2008121670A
公开(公告)日：2008-05-29
申请号：JP2007287122
申请日：2007-11-05
申请人： Snecma , スネクマ
发明人： BOIS BEATRICE , MADEC ALAIN , M BENGUE AMADOU
IPC分类号： F04D29/38 , F02C7/00 , F02C7/045
CPC分类号： F04D29/384 , F01D5/141 , F04D29/324 , F04D29/681 , F05D2240/301 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To mitigate conventional drawbacks of a turbomachine blade equipped with a plurality of blade sections (22) stacked along a radial axis (Z-Z). SOLUTION: The projection of a line (28a) interconnecting the leading edges of the blade sections (22) of a bottom stack (28) onto a mid-plane presents a first longitudinal angle (α) of inclination towards a leading edge (24) that lies in the range 10 to 25°, the projection of a line (30a) interconnecting the leading edges of the blade sections (22) of an intermediate stack (30) presents a second longitudinal angle (β) of inclination towards the trailing edge lying in the range 10 to 25°, the projection of a line (32a) interconnecting the leading edges of the blade sections (22) of a top stack (32) presents a third longitudinal angle (γ) of inclination towards the trailing edge lying in the range 20 to 50°, and a bottom limit (34) of the intermediate stack (30) of the blade sections (22) lies in the range 30 to 40% of the total radial height of the stack of blade sections (22). COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：为了减轻配备有沿着径向轴线（Z-Z）堆叠的多个叶片部分（22）的涡轮机叶片的常规缺点。解决方案：将底部堆叠（28）的叶片部分（22）的前缘互连到中间平面上的线（28a）的突出部朝向前边缘呈现倾斜的第一纵向角度（α）（24），其位于10至25°的范围内，与中间堆叠（30）的叶片部分（22）的前缘相互连接的线（30a）的突起呈倾斜的第二纵向角（β）后缘位于10至25°的范围内，与顶部叠层（32）的叶片部分（22）的前缘相互连接的线（32a）的突出部呈现向第三纵向角度（γ）后缘位于20至50°的范围内，叶片部分（22）的中间叠层（30）的下限（34）位于叶片堆叠的总径向高度的30％至40％的范围内部分（22）。版权所有（C）2008，JPO＆INPIT

26. 发明专利

JP2007315386A Method for manufacturing noise attenuation liner, method for manufacturing perforated face sheet for noise attenuation liner and noise attenuation liner assembly 审中-公开
标题翻译：制造噪声衰减线路的方法，制造噪声衰减线路和噪声衰减线路总成的执行表面的方法
公开(公告)号：JP2007315386A
公开(公告)日：2007-12-06
申请号：JP2007134861
申请日：2007-05-22
申请人： United Technol Corp , ユナイテッドテクノロジーズコーポレイションUnited Technologies Corporation
发明人： MORIN BRUCE L , KSIAZKIEWICZ RUDOLPH A JR , CICON DENNIS
IPC分类号： F02C7/24 , F01D25/30 , F02C7/045
CPC分类号： G10K11/172 , F02C7/045 , F02K1/827 , F05D2250/283 , F05D2260/96 , Y02T50/672 , Y10T428/24149
摘要： PROBLEM TO BE SOLVED: To provide a noise attenuation liner capable of providing desired durability, reducing resistance, and extending frequency attenuation range, and a method for manufacturing the noise attenuation liner. SOLUTION: An example liner assembly 22 includes a backing plate 24 that supports a cellular structure 26 covered by a perforated face sheet 28 including a plurality of openings 32. Each of the plurality of openings 32 is of a size determined to provide desired acoustic performance. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供能够提供期望的耐久性，降低电阻和扩大频率衰减范围的噪声衰减衬垫，以及用于制造噪声衰减衬垫的方法。示例性衬套组件22包括支撑由包括多个开口32的穿孔面板28覆盖的多孔结构26的背板24.多个开口32中的每一个具有确定为提供期望的尺寸声学性能。版权所有（C）2008，JPO＆INPIT

27. 发明专利

JP2007218253A Aircraft auxiliary gas turbine engine 有权
标题翻译：飞机辅助气体涡轮发动机
公开(公告)号：JP2007218253A
公开(公告)日：2007-08-30
申请号：JP2007022796
申请日：2007-02-01
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： BALAN CHELLAPPA , SHELDON KARL EDWARD
IPC分类号： F02C6/00 , B64D41/00 , F01D17/00 , F02C6/08 , F02C7/04 , F02C7/045 , F02C7/24
CPC分类号： B64D41/00 , B64D2013/0611 , B64D2041/002 , F02C7/32 , F05D2220/50
摘要： PROBLEM TO BE SOLVED: To provide an aircraft auxiliary gas turbine for an aircraft which is improved and not for propulsion, and an improved method for operating this kind of engine.
SOLUTION: The aircraft auxiliary gas turbine engine (10) is not for propulsion and is attachable to an aircraft (12) having a cabin (16) suitable for being pressurized. The auxiliary gas turbine engine (10) includes an auxiliary gas turbine engine compressor (18) having an intake port (20), and the intake port (20) is suitable for receiving compressed air (22) from the cabin (16).
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：提供一种改进而不是推进的飞机的飞机辅助燃气轮机，以及用于操作这种发动机的改进方法。解决方案：飞机辅助燃气涡轮发动机（10）不用于推进，并且可附接到具有适于被加压的舱室（16）的飞机（12）。辅助燃气涡轮发动机（10）包括具有进气口（20）的辅助燃气涡轮发动机压缩机（18），并且进气口（20）适于从舱室（16）接收压缩空气（22）。版权所有（C）2007，JPO＆INPIT

28. 发明专利

JP2006300062A Splice, and liner assembly and fan case assembly equipped therewith 审中-公开
标题翻译： SPLICE和LINER ASSEMBLY和风扇组件
公开(公告)号：JP2006300062A
公开(公告)日：2006-11-02
申请号：JP2006113977
申请日：2006-04-18
申请人： United Technol Corp , ユナイテッドテクノロジーズコーポレイションUnited Technologies Corporation
发明人： COSTA MARK W , BROWN CHARLES W , FREILER CHRIS
IPC分类号： F02C7/045 , F02C7/24 , F02K99/00 , F04D29/54 , F04D29/66
CPC分类号： F02C7/045 , F02K1/827 , F04D29/664 , F05D2250/11 , F05D2250/12 , Y02T50/672
摘要： PROBLEM TO BE SOLVED: To provide an acoustically advantageous splice for an acoustic liner.
SOLUTION: This duct liner assembly 12 includes a noise decay layer 18 covered with a surface sheet 22 for absorbing noise energy. The surface sheet 22 includes a seam 26 covered with the acoustically advantageous splice 30. The acoustically advantageous splice 30 includes a plurality of acoustic regions 32 for transmitting acoustic energy to the noise decay layer 18 to minimize the occurrence of acoustically disadvantageous regions.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：为声学衬垫提供声学上有利的接头。解决方案：该管道衬套组件12包括覆盖有用于吸收噪声能量的表面片22的噪声衰减层18。表面片22包括用声学上有利的接头30覆盖的接缝26.声学上有利的接头30包括用于将声能传递到噪声衰减层18的多个声学区域32，以使声学上不利的区域的发生最小化。版权所有（C）2007，JPO＆INPIT

29. 发明专利

JP2006226286A ACOUSTIC LINER HAVING BACK WALL OF NONUNIFORM DEPTH 审中-公开
公开(公告)号：JP2006226286A
公开(公告)日：2006-08-31
申请号：JP2006025299
申请日：2006-02-02
申请人： UNITED TECHNOLOGIES CORP
发明人： PATRICK WILLIAM P
IPC分类号： F02C7/045 , F01D25/30 , F02C7/00 , F02K1/44 , F02K99/00 , F04D29/54 , F04D29/66
摘要： PROBLEM TO BE SOLVED: To change the direction of noise reflected in a duct, without exposing aerodynamic performance of the duct to a danger, without adding inconvenient weight, cost and complexity. SOLUTION: A fluid processing duct such as an intake duct 20 of a turbine engine, has a face sheet 34 and an acoustic liner 32 having a back wall 38 separate in the horizontal direction from the face sheet. The back wall is offset from the face sheet in the nonuniform depth D to turn a sound wave incident there in the predetermined direction to the face sheet. In one embodiment, the back wall is composed of a lamp. In another embodiment, the back wall is composed of a series of stages offset from the face sheet in the different depth. The nonuniform depth of the back wall can be adapted to adjust the direction of a noise signal reflected from there, and can thereby reduce noise propagating to a surrounding environment from the duct. COPYRIGHT: (C)2006,JPO&NCIPI

30. 发明专利

JP3789129B2 Fan blade condition assembly 失效
公开(公告)号：JP3789129B2
公开(公告)日：2006-06-21
申请号：JP52831495
申请日：1995-04-24
申请人：ユナイテッドテクノロジーズコーポレイション
发明人：アール．ペンダ，アレン
IPC分类号： F02C7/00 , F01D21/04 , F02C7/045 , F02K3/06
CPC分类号： F01D21/045 , F02C7/045 , Y02T50/671

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