专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明专利

JP2014173597A Flow sleeve for controlling heat of double-wall turbine shell, and related method 审中-公开
标题翻译：用于控制双壁涡轮壳体热量的流量管道及相关方法
公开(公告)号：JP2014173597A
公开(公告)日：2014-09-22
申请号：JP2014043381
申请日：2014-03-06
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： RADU IOAN DANESCU , DAVID MARTIN JOHNSON , BLACK KENNETH DAMON , COX CHRISTOPHER PAUL , OZGUR BOZKURT
IPC分类号： F02C7/18 , F01D11/08 , F01D25/12 , F01D25/24 , F01D25/28 , F02C7/00
CPC分类号： F01D25/08 , F01D11/24 , F01D19/02 , F01D25/26 , F05D2220/32 , F05D2240/12 , F05D2240/14 , F05D2260/20
摘要： PROBLEM TO BE SOLVED: To hold a gap between rotary and stationary components minimum by a flow sleeve mounted to an external shell in a double shell gas turbine.SOLUTION: A turbine casing comprises: a shell 44 adapted to surround a turbine stage in a gas turbine engine; an air inlet 104 in the shell; and a flow sleeve fixed to an inner face of the shell and having two arc-like segments 54. Each arc-like segment 54 comprises an arc-like base part 58, and a pair of side walls 60, 62 extending from the base part outward in a radial direction, so as to form a flow channel defined by the base part, the side walls and the inner face and extending in a circumferential direction. The air inlet is aligned with the flow channel, and the sleeve is configured to distribute air flowing in the channel in a space immediately near the turbine stage, and in a circumferential direction, a radial direction and an axial direction including a direction along the inner face of the shell.
摘要翻译：要解决的问题：通过安装在双壳燃气轮机中的外壳的流动套筒来最小化旋转和静止部件之间的间隙。解决方案：涡轮机壳体包括：壳体44，其适于围绕气体中的涡轮机台架涡轮发动机; 外壳中的进气口104; 以及流动套筒，其固定到壳体的内表面并且具有两个弧形段54.每个弧形段54包括弧形基部58和从基部延伸的一对侧壁60,62 在径向方向外侧，以形成由基部，侧壁和内表面限定的并沿圆周方向延伸的流动通道。空气入口与流动通道对齐，并且套筒构造成将在通道内流动的空气分配在紧邻涡轮机台的空间中，并且沿圆周方向，沿径向和轴向方向包括沿着内侧的方向面壳的外壳。

2. 发明专利

JP2015036548A ガスターボ機械用の、ディフューザが一体化された内部筒部材审中-公开
标题翻译：内燃机会员与气体涡轮机的集成差速器
公开(公告)号：JP2015036548A
公开(公告)日：2015-02-23
申请号：JP2014160996
申请日：2014-08-07
申请人：ゼネラル・エレクトリック・カンパニイ , General Electric Co
发明人： CARL GERARD SCHOTT , BLACK KENNETH DAMON , CASAVANT MATTHEW STEPHEN
IPC分类号： F02C7/00 , F01D25/24
CPC分类号： F23R3/16 , F01D9/02 , F02C3/14
摘要：【課題】燃焼器の付近により有益な流れ場を形成し、燃焼力学を強化し、性能を改善し、排出物を低減するガスターボ機械用の、ディフューザが一体化された内部筒部材を提供する。【解決手段】ガスターボ機械用の内部筒部材35は、外面33と、内面42と、外面に設けられた1つ以上の半径流スプリッタ90とを有する本体64を含む。1つ以上の半径流スプリッタ90は、燃焼器中心線に沿って、燃焼流出口の、トランジションピース54の半径方向内側に配置されるように構成され、配されている。【選択図】図2
摘要翻译：要解决的问题：为了提供具有用于气体涡轮机的集成扩散器的内筒构件，其产生关于燃烧器的更有利的流场，增强燃烧动力学，改善性能并减少排放。解决方案：用于气体的内筒构件35 涡轮机械包括具有外表面33，内表面42和设置在外表面上的一个或多个径向分流器90的主体64。一个或多个径向流分流器90构造和设置成沿着燃烧器中心线布置在过渡件54径向内侧的燃烧流出口处。

3. 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。

4. 发明专利

JP2014084865A Gas turbine casing temperature control device 有权
标题翻译：气体涡轮机温度控制装置
公开(公告)号：JP2014084865A
公开(公告)日：2014-05-12
申请号：JP2013209765
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： F01D9/04 , F01D9/02 , F01D11/08 , F01D25/24 , F02C7/28
CPC分类号： F01D11/24 , F01D11/025 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20
摘要： PROBLEM TO BE SOLVED: To direct gas impingement to an inner casing of a gas turbine.SOLUTION: A plate configured for attachment to the outer surface of the inner casing has a first surface opposing the inner casing when the plate is attached to an area of the inner casing, and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged in the plate with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modification examples are possible. Related gas turbine assemblies are also disclosed.
摘要翻译：要解决的问题：将气体冲击引导到燃气轮机的内壳。解决方案：被配置为附接到内壳的外表面的板具有与内壳相对的第一表面，当板附接到所述内壳体和与所述第一表面相对的第二表面。板从第一表面到第二表面限定穿过板的多个孔。这些孔以对应于期望的优先冲击图案的预定的不均匀分布布置在板中，用于在燃气轮机的操作期间从区域提供不均匀的热传递，以便控制内壳跨过该区域的温度。各种选项和修改示例是可能的。还公开了相关的燃气轮机组件。

5. 发明专利

JP2014081076A Mechanical stop adjustment apparatus for jack 审中-公开
标题翻译：机械停止调整装置
公开(公告)号：JP2014081076A
公开(公告)日：2014-05-08
申请号：JP2013208696
申请日：2013-10-04
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
IPC分类号： F15B15/14
CPC分类号： G10L19/018
摘要： PROBLEM TO BE SOLVED: To provide adjustment and control of stop gaps in a hydraulic jack.SOLUTION: A first adjustable stop 230 on a jack member selectively adjusts an incline stop gap 239 while a second adjustable stop 250 on a support element 210 selectively adjusts a decline stop gap 259. Stop surfaces 235 on the first adjustable stop and the support element may define the incline stop gap, while stop surfaces on the second adjustable stop and the first adjustable stop may define the decline stop gap. The number of turns of a stop needed to effect a desired adjustment may be determined using a pitch, a lead and/or the number of starts of threads used to mount the stops.
摘要翻译：要解决的问题：提供液压千斤顶中止动间隙的调节和控制。解决方案：插座构件上的第一可调节止动件230选择性地调节倾斜止动间隙239，而支撑元件210上的第二可调节止动件250选择性地调节下降停止间隙259.第一可调节止动件和支撑元件上的止动表面235可以限定倾斜止挡间隙，而第二可调节止动件和第一可调节止动件上的止动表面可以限定下降停止间隙。可以使用螺距，导程和/或用于安装止挡件的螺纹的启动次数来确定实现所需调整所需的停止圈数。

6. 发明专利

JP2010174886A System and method of reducing heat loss from gas turbine during shutdown 有权
标题翻译：减速期间从燃气涡轮机损失的系统和方法
公开(公告)号：JP2010174886A
公开(公告)日：2010-08-12
申请号：JP2010013723
申请日：2010-01-26
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： BALLARD JR HENRY G , IAN DAVID WILSON , CHIECO STEPHEN CHRISTOPHER , KNEELAND ANDREW RAY , MILLER BRADLEY JAMES , BLACK KENNETH DAMON , GOETZE RAYMOND
IPC分类号： F01D25/10 , F01D25/14 , F02C7/18 , F02C9/20
CPC分类号： F01D21/06 , F01D11/24 , F01D21/12
摘要： PROBLEM TO BE SOLVED: To reduce a difference in a heat response between stator and rotor structural elements during the operation cycle of a gas turbine, particularly, during a shutdown cycle. SOLUTION: A method operates the gas turbine (200) that includes a compressor (202), a turbine (204) and an extraction cooling system (201). The method includes steps for monitoring an operation of the gas turbine (200), directing a cooling air flow through the extraction cooling system (201) from the compressor section (202) to the turbine section (204) according to the normal operation of the gas turbine (200), and directing a warming air flow through the extraction cooling system (201) to the compressor (202) and the turbine (204) according to the shutdown of the gas turbine (200). COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：为了减少在燃气轮机的操作循环期间，特别是在关闭循环期间定子和转子结构元件之间的热响应的差异。解决方案：一种方法操作包括压缩机（202），涡轮机（204）和抽取冷却系统（201）的燃气轮机（200）。该方法包括用于监测燃气轮机（200）的操作的步骤，根据所述燃气轮机（200）的正常操作，将冷却空气流通过所述抽出冷却系统（201）从所述压缩机部分（202）引导到所述涡轮机部分（204）燃气轮机（200），并且根据燃气轮机（200）的关闭，将加温空气流引导到提取冷却系统（201）到压缩机（202）和涡轮机（204）。版权所有（C）2010，JPO＆INPIT

7. 发明专利

JP2009150382A Thermally insulated flange bolt 审中-公开
标题翻译：热绝缘法兰螺栓
公开(公告)号：JP2009150382A
公开(公告)日：2009-07-09
申请号：JP2008311758
申请日：2008-12-08
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： MILLER BRADLEY JAMES , BLACK KENNETH DAMON , BALLARD HENRY GRADY JR , ADOOR RAKESH , YEOLE AJAY DIGAMBAR
IPC分类号： F01D25/24 , F02C7/00 , F02C7/24 , F04D29/52
CPC分类号： F01D25/243 , F16B33/004 , Y10T29/49766 , Y10T403/556
摘要： PROBLEM TO BE SOLVED: To provide turbine/compressor stator joints 300, 350, 400. SOLUTION: The turbine/compressor stator joints 300, 350, 400 may include a flange 210, an aperture 220 extending through the flange 210 and a bolt 230 extending through the aperture 220. The bolt 230 may include a shank part 240 and a shank thermal insulation layer 310 surrounding the shank part 240. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供涡轮/压缩机定子接头300,350,400。解决方案：涡轮/压缩机定子接头300,350,400可以包括凸缘210，延伸穿过凸缘的孔220 210和延伸穿过孔220的螺栓230.螺栓230可以包括柄部分240和围绕柄部分240的柄部隔热层310.版权所有（C）2009，JPO＆INPIT

8. 发明专利

JP2014095380A System for assembling and disassembling turbine section of gas turbine 有权
标题翻译：用于组装和拆卸涡轮机涡轮部分的系统
公开(公告)号：JP2014095380A
公开(公告)日：2014-05-22
申请号：JP2013228916
申请日：2013-11-05
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
IPC分类号： F02C7/00 , F01D25/00 , F01D25/28
CPC分类号： B23P11/00 , F01D21/045 , F01D25/28 , F01D25/285 , F05D2230/64 , F05D2230/68 , F16M13/00 , Y10T16/82 , Y10T29/49318 , Y10T29/49721 , Y10T29/53 , Y10T29/53687
摘要： PROBLEM TO BE SOLVED: To provide an improved system for installing and removing a lower portion of an inner turbine casing of a gas turbine engine.SOLUTION: A counter weight for installing and removing a lower portion of an inner casing of a turbine section generally comprises a semi-annular main body having a first radially extending mating surface and a second radially extending mating surface. A radial gear rack extends radially outward from the main body. The radial gear rack includes a primary segment that extends a first angular distance between the first radially extending mating surface and the second radially extending mating surface of the main body. A secondary segment of the radial gear rack extends to a second angular distance from the second radially extending mating surface of the main body. The secondary segment defines an at least partially linear inner surface and an outer arcuate surface.
摘要翻译：要解决的问题：提供一种用于安装和拆卸燃气涡轮发动机的内涡轮机壳体的下部的改进系统。解决方案：用于安装和移除涡轮机部分的内壳体的下部的配重通常包括半环形主体，其具有第一径向延伸的配合表面和第二径向延伸的配合表面。径向齿条从主体径向向外延伸。径向齿条包括主段，该主段在第一径向延伸的匹配表面和主体的第二径向延伸配合表面之间延伸第一角距离。径向齿条的次级段从主体的第二径向延伸配合表面延伸到第二角距离。次级段限定至少部分线性的内表面和外弧形表面。

9. 发明专利

JP2010270754A Low stress circumferential dovetail attaching device for rotor blade 有权
标题翻译：用于转子叶片的低应力圆周连接装置
公开(公告)号：JP2010270754A
公开(公告)日：2010-12-02
申请号：JP2010114854
申请日：2010-05-19
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 , BLACK KENNETH DAMON , CARTER BRADLEY SCOTT
IPC分类号： F01D5/30 , F01D5/02
CPC分类号： F01D5/3038 , F05D2260/941 , Y10T29/49321
摘要： PROBLEM TO BE SOLVED: To provide a retaining system for a circumferential entry type rotor dovetail, inserted into a dovetail slot in a rotor. SOLUTION: A plurality of rotor blade dovetails 118 are circumferentially slidable into and along the dovetail slot 110, with each rotor blade dovetail having a neck 120 and a pair of oppositely oriented lobes 122. A plurality of rail segments 126 are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops 106, 108. The rail segments define a first pressure face 138 that engages with an outward pressure face of the dovetail lobes, and a second pressure face 140 that engages with an inward pressure face of the respective disk hoop component. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种插入到转子中的燕尾槽中的圆周入口型转子燕尾榫的保持系统。解决方案：多个转子叶片燕尾形件118沿圆周方向滑动到燕尾槽110中并沿着燕尾槽110滑动，每个转子叶片燕尾形件具有颈部120和一对相对定向的叶片122.多个轨道段126周向滑动在燕尾形叶片和相应的盘箍106,108之间的燕尾槽中的通道中。轨道段限定了与燕尾形叶片的向外的压力面接合的第一压力面138和与第一压力面140接合的第二压力面140 相应的磁盘环组件的向内压力面。版权所有（C）2011，JPO＆INPIT

10. 发明专利

JP2009057973A Gas turbine rotor and stator support system 审中-公开
标题翻译：气体涡轮转子和定子支撑系统
公开(公告)号：JP2009057973A
公开(公告)日：2009-03-19
申请号：JP2008219111
申请日：2008-08-28
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： BLACK KENNETH DAMON , WILSON IAN DAVID , MILLER BRADLEY JAMES , BALLARD HENRY GRADY JR
IPC分类号： F01D25/00 , F01D25/24 , F02C7/20
CPC分类号： F02C7/20 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a system for supporting a stator and a rotor of a rotary machine disposed on a support base. SOLUTION: This system includes one or more support leg parts operably connecting the support base 13 and a bearing of the rotor 10, and one or more struts operably connecting one or more support legs and the stator 8. COPYRIGHT: (C)2009,JPO&INPIT

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式