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公开(公告)号：US20150345314A1
公开(公告)日：2015-12-03
申请号：US14290164
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dwight Eric DAVIDSON , Herbert Chidsey ROBERTS, III , John McConnell DELVAUX , Brian Denver POTTER , Stephen Paul WASSYNGER
IPC: F01D5/30
CPC classification number: F01D5/30 , F01D5/282 , F01D5/284 , F01D5/3007 , F01D5/3084 , F05D2240/80 , F05D2300/175 , F05D2300/6033
Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a non-segmented airfoil having a root section and a tip section integral with the root section, the tip section having a tip end with a second axial length, the second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The turbine wheel includes a turbine wheel material and the single-lobe joint and the non-segmented airfoil include a turbine bucket material, the turbine bucket material having a higher heat resistance and a lower thermal expansion than the turbine wheel material.
Abstract translation: 公开了一种涡轮机桶组件和涡轮机系统。 涡轮叶片组件包括具有整体平台的单瓣接头，该接头具有第一轴向长度; 一个非分段翼型件，其具有根部和与该根部一体的尖端部分，该末端部分具有一个具有第二轴向长度的末端，该第二轴向长度小于该第一轴向长度; 以及涡轮机轮，具有具有对应于单瓣接头的几何形状并且联接到单瓣接头的插座。 涡轮机叶轮包括涡轮叶轮材料，单瓣接头和非分段翼型件包括涡轮机叶片材料，涡轮机叶片材料具有比涡轮机轮材料更高的耐热性和更低的热膨胀性。
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公开(公告)号：US20180230822A1
公开(公告)日：2018-08-16
申请号：US15432398
申请日：2017-02-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephen Joseph BALSONE , Dwight Eric DAVIDSON , Michael Francis Xavier GIGLIOTTI, JR. , Pazhayannur Ramanathan SUBRAMANIAN , Akane SUZUKI
CPC classification number: F01D5/28 , C22C14/00 , F01D5/02 , F05D2300/174
Abstract: In some embodiments, a gamma titanium aluminide alloy consists essentially of, in atomic percent, about 38 to about 50% aluminum, about 6% niobium, about 0.25 to about 2% tungsten, optionally up to about 1.5% boron, about 0.01 to about 1.0% carbon, optionally up to about 2% chromium, optionally up to about 2% vanadium, optionally up to about 2% manganese, and the balance titanium and incidental impurities. In some embodiments, the gamma titanium aluminide alloy forms at least a portion of a gas turbine component. In some embodiments, a gamma titanium aluminide alloy, consisting essentially of, in atomic percent, about 40 to about 50% aluminum, about 3 to about 5% niobium, about 0.5 to about 1.5% tungsten, about 0.01 to about 1.5% boron, about 0.01 to about 1.0% carbon, optionally up to about 2% chromium, optionally up to about 2% vanadium, optionally up to about 2% manganese, and the balance titanium and incidental impurities.
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Patent Agency Ranking
公开(公告)号：US20150345307A1
公开(公告)日：2015-12-03
申请号：US14290237
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dwight Eric DAVIDSON , Stephen Joseph BALSONE , Brian Denver POTTER
IPC: F01D5/22
CPC classification number: F01D5/225 , C22C14/00 , C22C19/055 , C22C19/07 , C22C21/00 , F01D5/10 , F01D5/147 , F01D5/28 , F01D5/282 , F01D5/284 , F01D5/288 , F01D5/3007 , F05C2251/046 , F05D2300/174 , F05D2300/175 , F05D2300/176 , F05D2300/5021 , F05D2300/522
Abstract: A turbine bucket assembly and turbine system are disclosed. The assembly includes a multi-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the multi-lobe joint and being coupled to the multi-lobe joint. A tip segment material, a root segment material, and a turbine wheel material are selected, such that the turbine wheel material and the root segment material have a lower heat resistance and a higher thermal expansion than the tip segment material.
Abstract translation: 公开了一种涡轮机桶组件和涡轮机系统。 组件包括具有整体平台的多叶节接头，该接头具有第一轴向长度; 具有从所述平台径向向外延伸的根部段的分段翼型件和联接到根部段的尖端段，所述尖端段具有小于所述第一轴向长度的第二轴向长度; 以及涡轮机叶轮，其限定具有对应于所述多叶节接头的几何形状并且连接到所述多叶节接头的容器。 选择尖端段材料，根部段材料和涡轮机叶轮材料，使得涡轮机叶轮材料和根部材料具有比尖端段材料更低的耐热性和更高的热膨胀。
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公开(公告)号：US20150345296A1
公开(公告)日：2015-12-03
申请号：US14290076
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dwight Eric DAVIDSON , Michael David McDUFFORD , Brian Denver POTTER , Stephen Joseph BALSONE , Stephen Paul WASSYNGER
IPC: F01D5/14
CPC classification number: F01D5/14 , F01D5/16 , F01D5/225 , F01D5/28 , F01D5/3007 , F05D2230/642
Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length, which is less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material, the root segment material and the turbine wheel material having a lower heat resistance and a higher thermal expansion than the tip segment material.
Abstract translation: 公开了一种涡轮机桶组件和涡轮机系统。 涡轮叶片组件包括具有整体平台的单瓣接头，该接头具有第一轴向长度; 具有从所述平台径向向外延伸的根部段的分段翼型件和联接到所述根部段的尖端段，所述尖端段具有小于所述第一轴向长度的第二轴向长度; 以及涡轮机叶轮，其限定具有对应于单瓣接头的几何形状并且联接到单瓣接头的插座。 尖端部分包括尖端部分材料，根部部分包括根部部分材料，并且涡轮机叶轮包括涡轮叶轮材料，根部部分材料和涡轮机叶轮材料具有比尖端更低的耐热性和更高的热膨胀 段材料
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公开(公告)号：US20180230576A1
公开(公告)日：2018-08-16
申请号：US15432513
申请日：2017-02-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephen Joseph BALSONE , Dwight Eric DAVIDSON , Michael Francis Xavier GIGLIOTTI, JR. , Pazhayannur Ramanathan SUBRAMANIAN , Akane SUZUKI
CPC classification number: C22C14/00 , C22F1/183 , F01D5/02 , F01D5/28 , F05D2220/30 , F05D2300/174
Abstract: In some embodiments, a gamma titanium aluminide alloy consists essentially of, in atomic percent, 38 to about 50% aluminum, 1 to about 6% niobium, 0.25 to about 2% tungsten, 0.01 to about 1.5% boron, up to about 1% carbon, optionally up to about 2% chromium, optionally up to about 2% vanadium, up to about 2% manganese, and the balance titanium and incidental impurities. In some embodiments, the gamma titanium aluminide alloy forms at least a portion of a gas turbine component. In some embodiments, a gamma titanium aluminide alloy, consists essentially of, in atomic percent, about 40 to about 50% aluminum, about 1 to about 5% niobium, about 0.3 to about 1% tungsten, about 0.1 to about 0.3% boron, up to about 0.1% carbon, up to about 2% chromium, up to about 2% vanadium, up to about 2% manganese, up to about 1% molybdenum, and the balance titanium and incidental impurities.
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公开(公告)号：US20150345310A1
公开(公告)日：2015-12-03
申请号：US14290352
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dwight Eric DAVIDSON , Stephen Joseph BALSONE , Brian Denver POTTER
CPC classification number: F01D5/28 , F01D5/225 , F01D5/3007 , F05D2230/642
Abstract: A turbine bucket assembly and turbine system are disclosed. The assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a non-segmented airfoil extending radially outward from the integral platform and having a tip end with a second axial length, the second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The joint and the non-segmented airfoil include a turbine bucket material, and the turbine wheel includes a turbine wheel material, the turbine wheel material having a lower heat resistance and a higher thermal expansion than the turbine bucket material.
Abstract translation: 公开了一种涡轮机桶组件和涡轮机系统。 组件包括具有整体平台的单瓣接头，该接头具有第一轴向长度; 所述非分段翼型件从所述整体平台径向向外延伸并且具有具有第二轴向长度的末端，所述第二轴向长度小于所述第一轴向长度; 以及涡轮机轮，具有具有对应于单瓣接头的几何形状并且联接到单瓣接头的插座。 接头和非分段翼型件包括涡轮机叶片材料，涡轮机叶轮包括涡轮机叶轮材料，涡轮机叶轮材料具有比涡轮机叶片材料更低的耐热性和更高的热膨胀率。
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公开(公告)号：US20150345309A1
公开(公告)日：2015-12-03
申请号：US14290295
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dwight Eric DAVIDSON , Brian Denver POTTER , Stephen Joseph BALSONE
CPC classification number: F01D5/28 , F01D5/141 , F01D5/16 , F01D5/225 , F01D5/3007 , F05D2230/642
Abstract: A turbine bucket assembly and turbine system are disclosed. The assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material having a lower heat resistance and a higher thermal expansion than the root segment material and the tip segment material.
Abstract translation: 公开了一种涡轮机桶组件和涡轮机系统。 组件包括具有整体平台的单瓣接头，该接头具有第一轴向长度; 具有从所述平台径向向外延伸的根部段的分段翼型件和联接到所述根部段的尖端段，所述尖端段具有小于所述第一轴向长度的第二轴向长度; 以及涡轮机轮，具有具有对应于单瓣接头的几何形状并且联接到单瓣接头的插座。 尖端段包括尖端段材料，根段包括根段材料，并且涡轮机叶轮包括具有比根段材料和尖端段材料更低的耐热性和更高的热膨胀的涡轮机叶轮材料。
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