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公开(公告)号：US10683759B2
公开(公告)日：2020-06-16
申请号：US15933582
申请日：2018-03-23
Applicant: General Electric Company
Inventor： William Scott Zemitis , Jacob Charles Perry, II , Melbourne James Myers , Ajay Gangadhar Patil , Richard Ryan Pilson
Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.
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公开(公告)号：US10378383B2
公开(公告)日：2019-08-13
申请号：US15416038
申请日：2017-01-26
Applicant: General Electric Company
Inventor： Martin James Jasper , Ajay Gangadhar Patil , Brad Wilson VanTassel
Abstract: Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.
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Patent Agency Ranking
公开(公告)号：US20140161596A1
公开(公告)日：2014-06-12
申请号：US13709620
申请日：2012-12-10
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D9/04 , F01D25/246 , F05D2230/60 , F05D2240/11 , Y10T29/49323
Abstract: According to one aspect of the invention a turbine shroud engagement arrangement includes an outer shroud and an inner shroud operably connectable to the outer shroud. The outer shroud has at least one of a channel formed in and a protruding member extending from an inner radial surface thereof. The inner shroud has at least one of a protruding member extending from an outer radial surface thereof that is complementary to the at least one channel of the outer shroud or a channel formed in the outer radial surface that is complementary to the at least one protruding member of the outer shroud. The turbine shroud engagement arrangement is primarily axially slidably engagable and configured to radially support the inner shroud relative to the outer shroud.
Abstract translation: 根据本发明的一个方面，涡轮机罩接合装置包括外护罩和可操作地连接到外护罩的内护罩。 外护罩具有形成在其中的通道和从其内径向表面延伸的突出构件中的至少一个。 内护罩具有从其外径向表面延伸的突出构件中的至少一个，其与外护罩的至少一个通道互补或形成在外径向表面中的与至少一个突出构件互补的通道 的外护罩。 涡轮机罩接合装置主要是轴向可滑动地接合并构造为相对于外护罩径向地支撑内罩。
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公开(公告)号：US10760451B2
公开(公告)日：2020-09-01
申请号：US15564809
申请日：2015-05-22
Applicant: General Electric Company
Inventor： Damian Wolff , Karol Filip Leszczynski , Ajay Gangadhar Patil , Michael Todd Summers , Brad Wilson Vantassel
Abstract: A flow mixing lobe for an exhaust diffuser includes a first flange member having a first leading end, a first trailing end, and an intermediate portion extending therebetween. A second flange member includes a second leading end, a second trailing end, and an intermediate section extending therebetween. A first leg portion includes a first end extending from the first flange member, and a second end. A second leg portion has a first end portion extending from the second flange member, and a second end portion. A wing member is arranged between the first and second leg portions at respective ones of the second end and second end portions. The wing member includes a flow conditioning surface having a non-linear profile extending between the second end and the second end portion.
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公开(公告)号：US20190292914A1
公开(公告)日：2019-09-26
申请号：US15933582
申请日：2018-03-23
Applicant: General Electric Company
Inventor： William Scott Zemitis , Jacob Charles Perry, II , Melbourne James Myers , Ajay Gangadhar Patil , Richard Ryan Pilson
Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.
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公开(公告)号：US20180209303A1
公开(公告)日：2018-07-26
申请号：US15416038
申请日：2017-01-26
Applicant: General Electric Company
Inventor： Martin James Jasper , Ajay Gangadhar Patil , Brad Wilson VanTassel
CPC classification number: F01D25/246 , F01D9/02 , F01D9/042 , F05D2220/31 , F05D2220/32 , F05D2220/76 , F05D2230/61 , F05D2250/292 , F05D2260/30 , Y02E20/16
Abstract: Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.
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公开(公告)号：US09863264B2
公开(公告)日：2018-01-09
申请号：US13709620
申请日：2012-12-10
Applicant: General Electric Company
CPC classification number: F01D11/08 , F01D9/04 , F01D25/246 , F05D2230/60 , F05D2240/11 , Y10T29/49323
Abstract: According to one aspect of the invention a turbine shroud engagement arrangement includes an outer shroud and an inner shroud operably connectable to the outer shroud. The outer shroud has at least one of a channel formed in and a protruding member extending from an inner radial surface thereof. The inner shroud has at least one of a protruding member extending from an outer radial surface thereof that is complementary to the at least one channel of the outer shroud or a channel formed in the outer radial surface that is complementary to the at least one protruding member of the outer shroud. The turbine shroud engagement arrangement is primarily axially slidably engagable and configured to radially support the inner shroud relative to the outer shroud.
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