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21. 发明专利

JP2014084866A Gas turbine thermal control device, and method thereof 有权
标题翻译：气体涡轮机热控制装置及其方法
公开(公告)号：JP2014084866A
公开(公告)日：2014-05-12
申请号：JP2013209768
申请日：2013-10-07
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： CASAVANT MATTHEW STEPHEN , BLACK KENNETH DAMON , JOHNSON DAVID MARTIN , RADU IOAN DANESCU
IPC分类号： F01D25/24 , F01D9/02 , F01D9/04 , F01D11/02 , F01D11/08 , F01D25/12 , F01D25/18 , F01D25/26
CPC分类号： F01D11/24 , F01D11/025 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20 , F01D25/14 , F01D25/26 , F02C7/12
摘要： PROBLEM TO BE SOLVED: To provide an improved gas turbine thermal control device, and a method thereof.SOLUTION: Thermal control is provided for a gas turbine casing by: supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired selective impingement pattern for enabling non-uniform heat transfer. A gas turbine thermal control assembly includes structure enabling selective heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.
摘要翻译：要解决的问题：提供一种改进的燃气轮机热控制装置及其方法。解决方案：通过以下方式为燃气轮机壳体提供热控制：将来自压缩机的热控制气体供应到外壳和内壳之间的空间并且通过经由附接到内壳的外表面的板限定的多个孔将热控制气体从该空间传递通过内壳中的开口。这些孔以对应于期望的选择性冲击图案的预定的不均匀分布布置，以实现不均匀的热传递。燃气轮机热控制组件包括能够通过从内壳的径向外侧到燃气轮机的内部的热控制气体流动路径在燃气涡轮机运行期间从内壳选择性地传热的结构。

22. 发明专利

JP2013221518A Stator seal for avoiding turbine friction 审中-公开
标题翻译：用于避免涡轮摩擦的定子密封
公开(公告)号：JP2013221518A
公开(公告)日：2013-10-28
申请号：JP2013085740
申请日：2013-04-16
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： WILLETT JR FRED THOMAS , MICHAEL EARL MONTGOMERY , EISENZOPF PETER JOHN , MILLER RICHARD JAMES
IPC分类号： F01D11/04 , F01D11/10 , F01D25/00 , F02C7/28 , F16J15/44 , F16J15/447
CPC分类号： F01D5/20 , F01D11/122 , F01D11/18 , Y10T29/49297
摘要： PROBLEM TO BE SOLVED: To provide a turbine assembly stationary seal that brings large clearance during transient operation and brings tighter clearance during steady operation.SOLUTION: A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady operation section that facilitates a tighter clearance.
摘要翻译：要解决的问题：提供一种涡轮机组件固定密封件，其在瞬时操作期间带来较大的间隙，并在稳定运行期间带来更紧密的间隙。解决方案：一种用于涡轮机组件的定子密封件，包括可固定到涡轮机定子的密封基座，表面和设置在环形内表面上的可磨损涂层。可磨损涂层和环形内表面具有预定的横截面轮廓，其包括有助于轴向膨胀的瞬时操作部分和促进更紧密间隙的稳定操作部分。

23. 发明专利

JP2013155741A Turbofan engine fan case cartridge, method and fixture of manufacturing the same 有权
标题翻译：涡轮发动机风扇箱，其制造方法及其制造方法
公开(公告)号：JP2013155741A
公开(公告)日：2013-08-15
申请号：JP2013042483
申请日：2013-03-05
申请人： United Technologies 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： ROBERTSON JR THOMAS J , COSTA MARK W , SANTANA JOHAN R
IPC分类号： F02C7/00 , F01D11/08 , F01D25/24 , F02C7/28
CPC分类号： F01D11/18 , F01D11/125 , F01D25/26 , F05D2220/36 , F05D2230/68 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/50212 , F05D2300/603 , Y02T50/672 , Y10T29/49323 , Y10T156/10 , Y10T156/17
摘要： PROBLEM TO BE SOLVED: To provide a turbofan engine fan case cartridge, in which reduction of engine efficiency accompanying a gap between a distal end part of a fan and a fan case is improved.SOLUTION: A turbofan engine fan case cartridge comprising a metallic member is included. A first honeycomb has an inner diameter (ID) liner and is encircled by a front part of the metallic member. A second honeycomb is encircled by a metallic member at the back of the first honeycomb. A wear strip is encircled by the second honeycomb.
摘要翻译：要解决的问题：提供一种涡轮风扇发动机风扇箱，其中伴随风扇的远端部分和风扇壳之间的间隙的发动机效率的降低得到改善。解决方案：一种涡轮风扇发动机风扇箱，包括金属构件已经包括了。第一蜂窝体具有内径（ID）衬里并且被金属构件的前部包围。第二蜂窝体由第一蜂窝体后部的金属构件环绕。磨损条被第二蜂窝包围。

24. 发明专利

JP2013064404A Self-adjusting device for controlling clearance, especially in radial direction, between rotating and stationary components of thermally loaded turbo machine 有权
标题翻译：用于控制间隙的自调整装置，特别是径向方向，热负荷涡轮机的旋转和静止部件
公开(公告)号：JP2013064404A
公开(公告)日：2013-04-11
申请号：JP2012206199
申请日：2012-09-19
申请人： Alstom Technology Ltd , アルストムテクノロジーリミテッドALSTOM Technology Ltd
发明人： SZWEDOWICZ JAROSLAW LESZEK , MOZHAROV ALEXEY , SCHIEDECK FLORIAN , BOETTCHER JONAS
IPC分类号： F01D11/08 , F02C7/28
CPC分类号： F01D11/00 , F01D11/18 , F03G7/065 , F05D2300/505 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a self-adjusting device for controlling the clearance, which is of simple construction and allows the safe control of clearances even in cases where the clearance becomes a minimum during transitional operation of the machine.SOLUTION: The self-adjusting device (25) for controlling the clearance (C), especially in the radial direction, between rotating and stationary components (21, 23) of a thermally loaded turbo machine, changes clearance (C) in a non-linear way during transition of the machine between standstill and steady-state operation. Simple and effective control can be achieved, even in the case of a nonlinear variation of the clearance during transitional operation, by the self-adjusting device (25) including at least two different driving elements (A, B) to move the rotating and fixed components (21, 23) relative to each other in order to change the clearance (C) between them, and by the different driving elements (A, B) being configured to be activated at different times during the transition of the machine.
摘要翻译：要解决的问题：提供一种用于控制间隙的自动调节装置，其结构简单，并且即使在机器的过渡操作期间间隙变得最小的情况下也允许间隙的安全控制。解决方案：用于控制热负荷涡轮增压机的旋转和静止部件（21,23）之间的间隙（C），特别是在径向方向上的自调节装置（25）将间隙（C）改变为在静止和稳态运行之间机器转换过程中的非线性方式。即使在过渡操作期间间隙的非线性变化的情况下，也可以通过包括至少两个不同的驱动元件（A，B）的自动调节装置（25）来实现简单有效的控制，以移动旋转和固定组件（21,23），以便改变它们之间的间隙（C），并且由不同的驱动元件（A，B）构造成在机器的转变期间的不同时间被激活。版权所有（C）2013，JPO＆INPIT

25. 发明专利

JP2012211582A Continuous ring composite turbine shroud 有权
标题翻译：连续式复合涡轮机
公开(公告)号：JP2012211582A
公开(公告)日：2012-11-01
申请号：JP2012072661
申请日：2012-03-28
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： SHAPIRO JASON DAVID , BUHLER JARED PETER , CORSETTI BRIAN KENNETH
IPC分类号： F01D25/28 , F01D11/08 , F01D25/00 , F01D25/24 , F02C7/18 , F02C7/28
CPC分类号： F01D11/08 , F01D9/04 , F01D11/18 , F01D25/246 , F05D2300/603
摘要： PROBLEM TO BE SOLVED: To reduce an amount of cooling air used in cooling a turbine shroud for maximizing the overall efficiency of a gas turbine engine.SOLUTION: A composite annular shroud 42 is supported by a support assembly including full 360 degree rings 50, 52, and 54 of integral structure and is disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement 80 with an inner flange 84 of the innermost ring. A three ring assembly includes the inner ring 50 disposed radially inwardly of a middle ring 52 disposed radially inwardly of an outer ring 54 and the shroud 42 at least partially disposed within the inner ring. Three clocking pins 74 extend radially inwardly from the middle ring through a slot 76 in the inner ring into notches 78 in the shroud. A mounting pin 104 is press fitted into a pin hole 106 in the middle ring 52 and extends radially outwardly from the middle ring 52 through a radial hole 107 in the outer ring 54.
摘要翻译：要解决的问题：为了减少用于冷却涡轮机罩的冷却空气量，以最大化燃气轮机的整体效率。解决方案：复合环形护罩42由包括整体结构的完整360度环50,52和54的支撑组件支撑并且设置在最内侧的一个环中。护罩偏置在最内圈的内凸缘84上并与其密封接合80。三环组件包括设置在设置在外环54的径向内侧的中间环52的径向内侧的内环50，以及至少部分地设置在内环内的护罩42。三个时钟销74从中间环径向向内延伸穿过内环中的狭槽76到护罩中的凹口78。安装销104压配合到中间环52中的销孔106中，并通过外环54中的径向孔107从中间环52径向向外延伸。（C）2013，JPO和INPIT

26. 发明专利

JP2010053863A Device, system, and method for thermally activated displacement 审中-公开
标题翻译：用于热启动位移的装置，系统和方法
公开(公告)号：JP2010053863A
公开(公告)日：2010-03-11
申请号：JP2009188801
申请日：2009-08-18
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： WILSON IAN DAVID , MILLER BRADLEY JAMES , BALLARD JR HENRY GRADY , SCICCHITANO ERIC
IPC分类号： F03G7/06 , F01D11/08 , F02C7/28
CPC分类号： F01D11/18 , F01D11/24 , F05D2240/11
摘要： PROBLEM TO BE SOLVED: To provide a method of controlling displacement of a thermally activated displacement device. SOLUTION: An actuation device 18 includes: at least one first elongated member 46 having a first coefficient of thermal expansion (CTE): and at least one second elongated member 48 having a second CTE different from the first CTE, the second elongated member 48 being nested within the first elongated member 46. The actuation device 18 is configured to displace a portion of the device by a predetermined distance along a major axis of the device based on a relation between the first CTE and the second CTE in response to a change in temperature. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种控制热激活位移装置的位移的方法。解决方案：致动装置18包括：具有第一热膨胀系数（CTE）的至少一个第一细长构件46和具有不同于第一CTE的第二CTE的至少一个第二细长构件48，第二细长构件构件48嵌套在第一细长构件46内。致动装置18构造成基于第一CTE和第二CTE之间的关系，响应于第一CTE而将设备的一部分沿设备的长轴移动预定距离温度变化版权所有（C）2010，JPO＆INPIT

27. 发明专利

JP2009144706A Turbomachine module having device for improving radial gap 有权
标题翻译：具有用于改善径向间隙的装置的涡轮机模块
公开(公告)号：JP2009144706A
公开(公告)日：2009-07-02
申请号：JP2008310568
申请日：2008-12-05
申请人： Snecma , スネクマ
发明人： BRUNET ANTOINE , CHOMEL CLAUDE , JUSTE SEBASTIEN , HOURADOU EMMANUEL , RAULIN DOMINIQUE , RENAULT FREDERIC , SEDLAK JULIEN
IPC分类号： F04D29/52 , F04D29/58
CPC分类号： F01D11/18 , F01D17/105 , F01D25/145 , F01D25/246 , F02C6/08 , F04D29/522 , Y02T50/671 , Y02T50/675
摘要： PROBLEM TO BE SOLVED: To provide a turbomachine module having a device for improving a radial gap.
SOLUTION: This turbomachine module comprises a device for improving a radial gap which includes an external casing 22, an internal casing 21, and at least one shock absorbing ring 5 for connecting the casings to each other. The module further comprises, on the downstream side of the ring 5, an annular hollow 43 in which a passage 42 is formed. An air flow 4 is extracted from a main flow Fp through the passage. According to this invention, the device for improving a radial gap comprises, on the downstream side of the shock absorbing ring 5, a thermal inertia control device for the shock absorbing ring attached to the shock absorbing ring. The device comprises at least one heat insulating cover 8, and at least partially defines the annular hollow 43 on the downstream side.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种具有用于改善径向间隙的装置的涡轮机模块。解决方案：该涡轮机模块包括用于改善径向间隙的装置，其包括外壳22，内壳21和用于将壳体彼此连接的至少一个减震环5。模块还包括在环5的下游侧的环形中空部43，其中形成有通道42。从主流Fp通过通道提取空气流4。根据本发明，用于改善径向间隙的装置在冲击吸收环5的下游侧包括一个安装在减震环上的用于冲击吸收环的热惯性控制装置。该装置包括至少一个绝热盖8，并且至少部分地限定下游侧的环形中空部43。版权所有（C）2009，JPO＆INPIT

28. 发明专利

JP2007538199A Reinforcement of the turbine case in a gas turbine jet engine 有权
公开(公告)号：JP2007538199A
公开(公告)日：2007-12-27
申请号：JP2007527324
申请日：2005-05-13
申请人：カルダレア、エル、ジェームス、ジュニア
发明人：カルダレア、エル、ジェームス、ジュニア
IPC分类号： F01D25/24 , F01D25/00 , F01D25/20 , F02C7/00
CPC分类号： F01D11/22 , F01D11/02 , F01D11/18 , F01D21/045 , F01D25/24 , F05B2260/301 , F05D2240/14 , F05D2240/55 , F05D2250/182 , F05D2250/292 , F05D2300/702 , Y02T50/672
摘要：一実施形態において、低圧または高圧のタービンケース２０４の外面が加工されて円周状の切り欠き３０２が形成される。この切り欠きは、例えば内面におけるブレード２０８のためのシール２１０の位置、またはあらかじめ確認された「ホットスポット」と一致する位置に存在する。リングとケースとの間に温度差が生じるようにすることによって、補強リング３０４が各切り欠き３０２に締りばめされつつ収縮する。各リングによって加わる径方向からの円周状圧縮力で低圧または高圧タービンケースの膨張が抑制され、この圧縮力がない状態では膨張が生じる。いくつかの用途において、補強リングによって、ブレード先端クリアランスの改善もしくは「ホットスポット」の相殺、ケースの強化、ケース冷却能の向上その他の便益が個々の用途に応じてもたらされる。実施形態によっては、切り欠きが設けられないものもある。別の実施形態では、Ｃ字形リングや多重分割式リングが油圧、電気その他の手段によって組み込まれて、コントローラの駆動により径方向の円周状圧縮力が調整可能に加わるようにされる。その他の実施形態が説明および権利請求される。
【選択図】図３

30. 发明专利

JP2005061418A Method and device for fabricating gas turbine engine 审中-公开
标题翻译：用于制造气体涡轮发动机的方法和装置
公开(公告)号：JP2005061418A
公开(公告)日：2005-03-10
申请号：JP2004236971
申请日：2004-08-17
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： MACLEAN THOMAS
IPC分类号： F01D11/18 , F01D25/24 , F02C7/00
CPC分类号： F01D25/24 , F01D11/18
摘要： PROBLEM TO BE SOLVED: To provide a method for fabricating a turbine casing 36 which includes a plurality of turbine shroud assemblies 42.
SOLUTION: The method includes providing a base casing 38 having a forward mounting flange 54 and an aft mounting flange 56 and at least one channel 52 defined therebetween, machining a rim 62 on the base casing proximate at least one channel 52, and coupling a ring member 64 to the base casing 38 with an interference fit such that the rim 62 is at least partially received within a groove 72 formed within the ring member 64.
COPYRIGHT: (C)2005,JPO&NCIPI

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