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1. 发明授权

EP2587002B1 Turbomachine including an inner-to-outer turbine casing seal assembly and corresponding method of sealing 有权转让
公开(公告)号：EP2587002B1
公开(公告)日：2019-09-04
申请号：EP12189824.1
申请日：2012-10-24
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Johnson, David Martin
IPC分类号： F01D25/26 , F01D11/00

2. 发明公开

EP2722491A2 Gas turbine casing thermal control device 有权转让
标题翻译： Gasturbinengehäuse-Wärmesteuerungsvorrichtung
公开(公告)号：EP2722491A2
公开(公告)日：2014-04-23
申请号：EP13189103.8
申请日：2013-10-17
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Black, Kenneth Damon , Johnson, David Martin , Danescu, Radu Ioan
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F01D11/025 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20
摘要： A device (130) for directing gas impingement to an inner casing (121) of a gas turbine (110) may include a plate (140) configured for attachment to the outer surface of the inner casing. The plate has a first surface (146) opposing the inner casing when the plate is attached to an area of the inner casing and a second surface (148) opposite the first surface. The plate defines a plurality of holes (144) through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate 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 modifications are possible. Related gas turbine assemblies are also disclosed.
摘要翻译：用于将气体冲击引导到燃气涡轮机（110）的内壳体（121）的装置（130）可以包括被配置为附接到内壳体的外表面的板（140）。当板被附接到内壳体的一个区域和与第一表面相对的第二表面（148）时，板具有与内壳相对的第一表面（146）。板从第一表面到第二表面限定穿过板的多个孔（144）。这些孔以对应于期望的优先冲击图案的板中的预定的不均匀分布布置，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。可以进行各种选择和修改。还公开了相关的燃气轮机组件。

3. 发明公开

EP2587002A2 Turbomachine including an inner-to-outer turbine casing seal assembly and corresponding method of sealing 有权转让
标题翻译：涡轮机具有用于密封所述内涡轮机壳体的相对外涡轮机壳体和相关联的方法的装置
公开(公告)号：EP2587002A2
公开(公告)日：2013-05-01
申请号：EP12189824.1
申请日：2012-10-24
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Johnson, David Martin
IPC分类号： F01D25/26
CPC分类号： F01D25/26 , F01D11/005 , F05D2240/56 , F05D2240/59 , Y10T29/49229
摘要： A turbomachine includes an inner casing component (20) having a first end that extends to a second end and a seal member (58). An outer casing component (30) is coupled to the inner casing component (20). The annular outer casing component (30) includes a first end portion (71) that extends to a second end portion (72) and a seal element (78) that aligns with the seal member (58) of the annular inner casing component (20) to form a seal passage (86). A seal (36) is arranged in the seal passage (86). The seal (36) includes a first end section (94) that extends to a second end section (95) through an intermediate zone (96). The first end section (94) includes a recessed portion (99) and the second end section (95) includes a connecting portion (100). The connecting portion (100) is configured and disposed to nest within the recessed portion (99) to form a substantially continuous seal.
A corresponding method of sealing a turbomachine innner to outer casin interface.
摘要翻译：一种涡轮机，包括具有第一端部内壳部件（20）做了延伸到第二端部和密封构件（58）。外壳部件（30）被联接到内壳部件（20）。环形设计外壳体部件（30）包括（71）做了第一端部延伸到第二端部（72）和密封构件（78）没有与环形设计内壳体部件的密封构件（58）对齐（20 ），以形成一密封通道（86）。的密封件（36）在密封通道（86）被布置。所述密封件（36）包括第一端部（94）做了延伸通过到中间区（96）的第二端部（95）。第一端部段（94）包括凹部（99）和所述第二端部（95）包括连接部（100）。所述连接部（100）被配置和设置以嵌套凹部（99）内，以形成基本上连续的密封。密封的涡轮机中肠子到外酪接口的相应的方法。

4. 发明公开

EP2690256A3 Method and system for assembling and disassembling shells of turbomachines 有权转让
标题翻译：用于装配和拆卸涡轮机壳的方法和系统
公开(公告)号：EP2690256A3
公开(公告)日：2017-08-23
申请号：EP13177226.1
申请日：2013-07-19
申请人： General Electric Company
发明人： Holmes, James Bradford , Black, Kenneth Damon , Cox, Christopher Paul , Casavant, Matthew Stephen , Wilson, Bradley Edwin , Klinger, Brett Darrick
IPC分类号： F01D25/28 , B66F9/04 , F01D25/26 , F04D29/62
CPC分类号： F01D9/04 , B66F3/24 , F01D25/26 , F01D25/28 , F01D25/285 , F05D2230/60 , F05D2230/644 , F05D2230/70 , F05D2260/53 , F05D2260/57 , Y10T29/49238 , Y10T29/53
摘要： A method and system adapted for removing one or more shells from an assembly of multiple annular shells (14, 16, 18, 20), for example, turbine shells of a gas turbine engine (10). The method includes removing an upper shell (14, 18) positioned in an upper position relative to a lower shell (16, 20) of the assembly of multiple annular shells, and then positioning and securing a counterweight (22) in the upper position and securing the counterweight (22) to the lower shell as a replacement for the upper shell in the upper position. The counterweight (22) and the lower shell (16, 20) are then rotated in unison until the lower shell is in the upper position and the counterweight (22) is in a lower position previously occupied by the lower shell. Thereafter, the lower shell (16, 20) can be removed from the assembly.
摘要翻译：一种适于从多个环形壳体（14,16,18,20）的组件中去除一个或多个壳体的方法和系统，例如燃气涡轮发动机（10）的涡轮机壳体。该方法包括移除位于相对于多个环形壳组件的下部壳体（16,20）的上部位置中的上部壳体（14,18），然后将配重（22）定位和固定在上部位置并且将配重（22）固定在下部壳体上，作为上部位置的上部壳体的替代物。然后，配重（22）和下壳体（16,20）一致地旋转，直到下壳体处于上部位置并且配重（22）处于先前由下壳体占据的下部位置。此后，下壳（16,20）可以从组件中取出。

5. 发明公开

EP2722491A3 Gas turbine casing thermal control device 有权转让
标题翻译：燃气轮机机壳热控装置
公开(公告)号：EP2722491A3
公开(公告)日：2017-08-09
申请号：EP13189103.8
申请日：2013-10-17
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Black, Kenneth Damon , Johnson, David Martin , Danescu, Radu Ioan
IPC分类号： F01D11/24 , F01D11/02 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20
CPC分类号： F01D11/24 , F01D11/025 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20
摘要： A device (130) for directing gas impingement to an inner casing (121) of a gas turbine (110) may include a plate (140) configured for attachment to the outer surface of the inner casing. The plate has a first surface (146) opposing the inner casing when the plate is attached to an area of the inner casing and a second surface (148) opposite the first surface. The plate defines a plurality of holes (144) through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate 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 modifications are possible. Related gas turbine assemblies are also disclosed.
摘要翻译：用于引导气体冲击到燃气涡轮机（110）的内壳体（121）的装置（130）可以包括配置用于附接到内壳体的外表面的板（140）。当板连接到内壳的区域时，板具有与内壳相对的第一表面（146）和与第一表面相对的第二表面（148）。板限定从第一表面到第二表面穿过板的多个孔（144）。孔在板中以预定的不均匀分布布置，对应于期望的优先冲击模式，用于在燃气轮机运行期间从区域提供不均匀的热传递，从而控制横跨该区域的内壳的温度。各种选项和修改都是可能的。也公开了相关的燃气轮机组件。

6. 发明公开

EP2634379A1 Compression Sleeve Seal 有权
标题翻译： Kompressionshülsendichtung
公开(公告)号：EP2634379A1
公开(公告)日：2013-09-04
申请号：EP13157037.6
申请日：2013-02-27
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Klingler, Brett Darrick
IPC分类号： F01D25/24 , F16L23/16
CPC分类号： F01D25/243 , F05D2240/55 , F05D2260/31 , Y10T29/49863
摘要： A seal for a turbine casing (2) is provided. The turbine casing (2) includes a plurality of sections joined at flanges (4,6) provided on each section. Each flange (4,6) includes a bore and a counterbore. The seal comprises a compression sleeve seal (12) having a length that is greater than a counterbore (8) -to-counterbore length of two flanges (4,6) ; a fastener (16) configured to extend through the compression sleeve seal (12); and a nut (14) threadable on each end of the fastener (16). The compression sleeve seal (12) is compressible between each flange (4,6) and each nut (14) to create a first seal and is radially extensible to create a second seal against each bore (10).
摘要翻译：提供了一种用于涡轮机壳体（2）的密封件。涡轮壳体（2）包括在每个部分上设置的凸缘（4,6）处连接的多个部分。每个凸缘（4,6）包括孔和沉孔。密封件包括压缩套筒密封件（12），该密封件的长度大于两个凸缘（4,6）的沉孔（8）至沉孔长度; 构造成延伸穿过所述压缩套筒密封件（12）的紧固件（16）; 以及可在所述紧固件（16）的每一端上螺纹连接的螺母（14）。压缩套筒密封件（12）可在每个凸缘（4,6）和每个螺母（14）之间压缩以产生第一密封件并且可径向延伸以产生针对每个孔（10）的第二密封件。

7. 发明公开

EP2568125A2 Turbine casing assembly mounting pin 审中-公开
标题翻译： BefestigungsstiftfüreineTurbinengehäuseanordnung
公开(公告)号：EP2568125A2
公开(公告)日：2013-03-13
申请号：EP12182829.7
申请日：2012-09-03
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Black, Kenneth Damon
IPC分类号： F01D25/24
CPC分类号： F01D25/243 , F01D25/246 , F01D25/26 , F01D25/28 , F05D2230/644 , F05D2260/30 , Y10T29/4932
摘要： In certain embodiments of the present disclosure a turbine casing assembly (10) and a method for assembling a turbine casing are described. The turbine casing assembly (10) includes an inner casing (14) and an outer casing (12) surrounding the inner casing (14). The outer casing (12) includes a first outer casing section (125) and a second outer casing section (126) that join together along a flange (52). Two bolts (50) extend through the flange (52) and join together the first outer casing section (125) and the second outer casing section (126). A pin (54) having a first segment having a first diameter and a second segment having a second diameter extends through the inner casing (14) and the outer casing (12) and supports the inner casing (14) relative to the outer casing (12). The pin (54) has a first diameter that is greater than the second diameter and is located between the two bolts (50) along the axis of the flange (52).
摘要翻译：在本公开的某些实施例中，描述了涡轮机壳体组件（10）和用于组装涡轮机壳体的方法。涡轮机壳体组件（10）包括内壳体（14）和围绕内壳体（14）的外壳体（12）。外壳（12）包括沿凸缘（52）连接在一起的第一外壳部分（125）和第二外壳部分（126）。两个螺栓（50）延伸穿过凸缘（52）并将第一外壳部分（125）和第二外壳部分（126）连接在一起。具有第一直径的第一段和具有第二直径的第二段的销（54）延伸穿过内壳（14）和外壳（12），并相对于外壳（ 12）。销（54）具有大于第二直径的第一直径，并且沿着凸缘（52）的轴线位于两个螺栓（50）之间。

8. 发明授权

EP2722490B1 Gas turbine thermal control and related method 有权转让
公开(公告)号：EP2722490B1
公开(公告)日：2020-01-15
申请号：EP13187944.7
申请日：2013-10-09
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Black, Kenneth Damon , Johnson, David Martin , Danescu, Radu Ioan
IPC分类号： F01D11/24 , F01D25/12 , F02C7/12 , F01D11/20 , F01D11/18 , F01D11/16 , F01D11/14 , F01D11/02 , F01D25/26 , F01D25/14

9. 发明公开

EP2613020A3 Turbine casing 有权转让
标题翻译：涡轮机壳体
公开(公告)号：EP2613020A3
公开(公告)日：2017-05-17
申请号：EP12198420.7
申请日：2012-12-20
申请人： General Electric Company
发明人： Wilson, Bradley Edwin , Casavant, Matthew Stephen
IPC分类号： F01D25/24 , F01D25/26 , F02K3/06
CPC分类号： F01D25/243 , F01D25/26 , F02K3/06 , F05D2240/14
摘要： A turbine casing includes a plurality of arc-shaped segments (11) having a flange (36a,36b) at each side end (34,35) to connect to a flange of an adjacent arc-shaped segment. The flange extends outward from an outer surface of each arc-shaped segment and extends along the outer surface (31) in a front-to-rear direction. Each arc-shaped segment has a portion of the outer surface that is co-linear with the flange in a front-to-rear direction that does not include the flange.
摘要翻译：涡轮机壳体包括多个在每个侧端（34,35）处具有凸缘（36a，36b）以连接到相邻的弧形段的凸缘的弧形段（11）。凸缘从每个弧形段的外表面向外延伸并沿着外表面（31）在前后方向上延伸。每个弧形部分具有外表面的一部分，该部分外表面在不包括凸缘的前后方向上与凸缘共线。

10. 发明授权

EP2557277B1 Method and Apparatus to Facilitate Turbine Casing Assembly 有权转让
标题翻译：方法和装置以促进涡轮机壳体组件
公开(公告)号：EP2557277B1
公开(公告)日：2017-05-17
申请号：EP12179078.6
申请日：2012-08-02
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Wilson, Bradley Edwin
IPC分类号： F01D25/26 , F01D25/24 , F01D25/28
CPC分类号： F01D25/243 , F01D25/28 , F05D2230/644 , Y10T29/4932

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