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1. 发明授权

EP2182175B1 Casing structure for and method of improving a turbine's thermal response during transient and steady state operating conditions 失效
公开(公告)号：EP2182175B1
公开(公告)日：2018-10-03
申请号：EP09173963.1
申请日：2009-10-23
申请人： General Electric Company
发明人： Black, Kenneth Damon
IPC分类号： F01D11/24 , F01D25/14 , F01D25/26
CPC分类号： F01D11/24 , F01D25/14 , F01D25/26 , F05D2230/642 , F05D2240/14
摘要： A method is disclosed for improving a turbine's thermal response during transient and steady state operating conditions in which the flow of cooling fluid (25) in the turbine's casing (10) is caused to be asymmetrical relative to the horizontal and vertical symmetry planes (31, 33) of the casing (10) so that the turbine's cooling symmetry planes (30', 32') are rotated relative to its geometric symmetry planes (31, 33) and thereby the heat transfer at locations (27, 29) in the casing (10) with increased mass is increased.

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

EP2213843A2 Reducing heat loss from a gas turbine during shutdown 有权
标题翻译： Redizierung des Hitzeverlustes von einer Gasturbinewährendder Abschaltung
公开(公告)号：EP2213843A2
公开(公告)日：2010-08-04
申请号：EP10151736.5
申请日：2010-01-27
申请人： General Electric Company
发明人： Ballard, Henry G. Jr. , Wilson, Ian David , Chieco, Stephen Christopher , Kneeland, Andrew Ray , Miller, Bradley James , Black, Kenneth Damon , Goetze, Raymond
IPC分类号： F01D11/24
CPC分类号： F01D21/06 , F01D11/24 , F01D21/12
摘要： A method operates a gas turbine (200) that includes a compressor section (202), a turbine section (204) and an extraction cooling system (201). The method includes 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) in response to normal operation of the gas turbine (200), and directing a warming air flow through the extraction cooling system (201) to the compressor section and the turbine section (204) in response to shutdown of the gas turbine (200).
摘要翻译：一种方法操作包括压缩机部分（202），涡轮部分（204）和抽取冷却系统（201）的燃气轮机（200）。该方法包括监测燃气轮机（200）的操作，响应于燃气轮机（200）的正常运行，将冷却空气流通过提取冷却系统（201）从压缩机部分（202）引导到涡轮部分（204）（200），并且响应于燃气轮机（200）的关闭，将加温空气流引导到提取冷却系统（201）到压缩机部分和涡轮部分（204）。

4. 发明公开

EP2568125A3 Turbine casing assembly mounting pin 审中-公开
标题翻译：涡轮机壳体组件安装销
公开(公告)号：EP2568125A3
公开(公告)日：2017-09-20
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 , F01D25/26
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，描述了一种涡轮机壳体组件（10）和一种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。具有具有第一直径的第一部分和具有第二直径的第二部分的销（54）延伸穿过内部壳体（14）和外部壳体（12）并且相对于外部壳体（14）支撑内部壳体（14） 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。

5. 发明公开

EP2722490A3 Gas turbine thermal control and related method 有权转让
标题翻译：燃气轮机热控制及相关方法
公开(公告)号：EP2722490A3
公开(公告)日：2017-08-09
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
摘要： Thermal control is provided for a gas turbine (110) casing by supplying thermal control gas from a compressor (112) to a space between an outer casing (123) and an inner casing (121), and transferring the thermal control gas from the space through the opening in the inner casing (121) via a plurality of holes (144) defined through a plate (140) attached to an outer surface of the inner casing (121). The holes (144) are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing (121) during operation of the gas turbine (110) via a thermal control gas flow path (190) from radially outside of the inner casing into the interior of the gas turbine (110).
摘要翻译：通过从压缩机（112）供给热控制气体到外壳（123）和内壳（121）之间的空间并从该空间传送热控制气体，从而为燃气轮机（110）壳体提供热控制通过连接到内壳体（121）的外表面的板（140）限定的多个孔（144）穿过内壳体（121）中的开口。孔（144）以预定的非均匀分布布置，对应于期望的优先冲击模式以提供不均匀的热传递。燃气涡轮机热控制组件包括在燃气涡轮机（110）的操作期间经由热控制气体流动路径（190）从内壳体的径向外部进入内壳体（121）内部的优选传热燃气轮机（110）。

6. 发明公开

EP2730753A1 A system for assembling and disassembling a turbine section of a gas turbine 有权转让
标题翻译：系统zur蒙太奇和恶魔eines Turbinenabschnitts einer Gurburbine
公开(公告)号：EP2730753A1
公开(公告)日：2014-05-14
申请号：EP13191981.3
申请日：2013-11-07
申请人： General Electric Company
发明人： Casavant, Matthew Stephen , Black, Kenneth Damon
IPC分类号： F01D21/04 , 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： A counter weight (62) for installing and removing a lower portion of an inner casing of a turbine section generally includes a semi-annular main body (72) having a first radially extending mating surface (84) and a second radially extending mating surface (86). A radial gear rack (90) extends radially outward from the main body. The radial gear rack (90) includes a primary segment that extends a first angular distance between the first radially extending mating surface (84) and the second radially extending mating surface (86) of the main body (72). A secondary segment of the radial gear rack (90) extends a second angular distance from the second radially extending mating surface (86) of the main body (72). The secondary segment defines an at least partially linear inner surface and an outer arcuate surface.
摘要翻译：用于安装和移除涡轮机部分的内壳的下部的配重（62）通常包括具有第一径向延伸配合表面（84）和第二径向延伸配合表面（84）的半环形主体（72） 86）。径向齿条（90）从主体径向向外延伸。径向齿条（90）包括在第一径向延伸配合表面（84）和主体（72）的第二径向延伸配合表面（86）之间延伸第一角距离的主段。径向齿条（90）的次级段从主体（72）的第二径向延伸配合表面（86）延伸第二角距离。次级段限定至少部分线性的内表面和外弧形表面。

7. 发明公开

EP2690256A2 Method and system for assembling and disassembling shells of turbomachines 有权转让
标题翻译： Verfahren und System zur Montage und Demontage vonTurbomaschinengehäusen
公开(公告)号：EP2690256A2
公开(公告)日：2014-01-29
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： F01D9/04 , F01D25/28
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）的组件移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。该方法包括去除位于相对于多个环形壳体的组件的下壳体（16,20）的上部位置的上壳体（14,18），然后将配重（22）定位并固定在上部位置，并且将配重（22）固定到下壳体上，以代替上壳体的上部位置。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）处于先前被下壳体占据的下部位置。此后，下壳体（16,20）可以从组件移除。

8. 发明公开

EP2568126A2 Turbine casing assembly mounting pin 审中-公开
标题翻译： BefestigungsstiftfüreineTurbinengehäuseanordnung
公开(公告)号：EP2568126A2
公开(公告)日：2013-03-13
申请号：EP12182830.5
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 , Y10T29/49323
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) has a first outer casing section and a second outer casing section that join together along a flange (52). A bolt (50) extends through the flange (52) and joins together the first outer casing section and the second outer casing section. The turbine casing assembly (10) further includes a pin (54). The pin (54) has a segment defining an opening (66) therethrough. The pin (54) extends through the inner casing (14) and the outer casing (12) and supports the inner casing (14) relative to the outer casing (12). The bolt (50) passes through the opening (66) defined by the pin (54).
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）具有沿法兰（52）连接在一起的第一外壳部分和第二外壳部分。螺栓（50）延伸穿过凸缘（52）并将第一外壳部分和第二外壳部分连接在一起。涡轮机壳体组件（10）还包括销（54）。销（54）具有限定穿过其中的开口（66）的段。销（54）延伸穿过内壳（14）和外壳（12）并相对于外壳（12）支撑内壳体（14）。螺栓（50）穿过由销（54）限定的开口（66）。

9. 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。

10. 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。

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