公开(公告)号：US20220145765A1

公开(公告)日：2022-05-12

申请号：US17438489

申请日：2019-03-29

申请人： Siemens Energy, Inc.

发明人： Atul L. Navale ,  James A. Yarbrough ,  Somesh J. Ghunakikar ,  Ivan F. Oliver Vargas

IPC分类号： F01D5/20 ,  B23P6/00

摘要： A method for repairing a tip portion of a turbine component having a structural defect is provided. The method includes removing a damaged section in turbine component with a structural defect in a tip portion of the turbine component. A pre-sintered preform is provided including a first portion having a first composition and a second portion having a second composition. The pre-sintered preform is configured to mate with an upper surface of a remaining portion of the turbine component. The method also includes applying the pre-sintered preform to the upper surface, wherein the PSP comprises a superalloy material and a braze material. The PSP and the remaining portion of the turbine component are subjected to a brazing process to melt the braze material and fill in the structural defect.

公开(公告)号：US10392938B1

公开(公告)日：2019-08-27

申请号：US16059490

申请日：2018-08-09

申请人： Siemens Energy, Inc.

发明人： Somesh J. Ghunakikar ,  James A. Yarbrough ,  Mark A. Garcia

IPC分类号： B23K1/00 ,  F01D5/00 ,  B23P6/00 ,  B23K31/02

摘要： A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

公开(公告)号：US09611741B2

公开(公告)日：2017-04-04

申请号：US14070664

申请日：2013-11-04

申请人： Siemens Energy, Inc.

发明人： Petya M. Georgieva ,  James A. Yarbrough

IPC分类号： F01D5/00 ,  B23K1/00 ,  B23K35/30 ,  F01D5/12 ,  F01D9/02 ,  B23P6/00 ,  B23K35/02 ,  C22C19/05 ,  B23K101/00

CPC分类号： B23P6/045 ,  B23K1/0018 ,  B23K35/025 ,  B23K35/3033 ,  B23K35/304 ,  B23K35/3046 ,  B23K2101/001 ,  B23P6/002 ,  C22C19/055 ,  C22C19/056 ,  C22C19/057 ,  C22C19/058 ,  C22C19/07 ,  F01D5/005 ,  F01D5/12 ,  F01D5/28 ,  F01D9/02 ,  F05D2220/30 ,  F05D2230/237 ,  F05D2230/40 ,  F05D2230/80 ,  F05D2300/175 ,  F05D2300/177 ,  Y10T403/479

摘要： A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects.

公开(公告)号：US20200049012A1

公开(公告)日：2020-02-13

申请号：US16512433

申请日：2019-07-16

申请人： Siemens Energy, Inc.

发明人： Somesh J. Ghunakikar ,  James A. Yarbrough ,  Mark A. Garcia

IPC分类号： F01D5/00 ,  B23K1/00 ,  B23P6/00 ,  B23K31/02

摘要： A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

公开(公告)号：US09664049B2

公开(公告)日：2017-05-30

申请号：US14070626

申请日：2013-11-04

申请人： Siemens Energy, Inc.

发明人： Petya M. Georgieva ,  James A. Yarbrough

IPC分类号： F01D5/00 ,  B23K35/30 ,  B23K1/00 ,  F01D5/12 ,  B23P6/04 ,  B23K35/02 ,  F01D9/02 ,  C22C19/05 ,  C22C19/07 ,  B23K101/00

CPC分类号： F01D5/005 ,  B23K1/0018 ,  B23K35/025 ,  B23K35/3033 ,  B23K35/3046 ,  B23K2101/001 ,  B23P6/045 ,  C22C19/057 ,  C22C19/07 ,  F01D5/12 ,  F01D9/02 ,  F05D2230/237 ,  F05D2230/80 ,  F05D2300/175 ,  F05D2300/177 ,  Y10T403/479

摘要： A multi-component braze filler alloy comprising at least 70% by weight MarM509A superalloy with the remainder MarM509B superalloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. It is shown that generally higher braze temperatures lead to improved results including the possibility of re-welding such a brazed component, resulting in a re-repaired brazed component capable of continued commercial service.

公开(公告)号：US10760422B2

公开(公告)日：2020-09-01

申请号：US16512433

申请日：2019-07-16

申请人： Siemens Energy, Inc.

发明人： Somesh J. Ghunakikar ,  James A. Yarbrough ,  Mark A. Garcia

IPC分类号： B23K1/00 ,  F01D5/00 ,  B23P6/00 ,  B23K31/02 ,  B23K35/30 ,  B23K103/18 ,  B23K101/00

摘要： A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

公开(公告)号：US20170157721A1

公开(公告)日：2017-06-08

申请号：US15433597

申请日：2017-02-15

申请人： Siemens Energy, Inc.

发明人： Petya M. Georgieva Fernlund ,  James A. Yarbrough

IPC分类号： B23P6/04 ,  B23K35/30 ,  F01D9/02 ,  C22C19/05 ,  F01D5/28 ,  F01D5/00 ,  B23P6/00 ,  C22C19/07

CPC分类号： B23P6/045 ,  B23K1/0018 ,  B23K35/025 ,  B23K35/3033 ,  B23K35/304 ,  B23K35/3046 ,  B23K2101/001 ,  B23P6/002 ,  C22C19/055 ,  C22C19/056 ,  C22C19/057 ,  C22C19/058 ,  C22C19/07 ,  F01D5/005 ,  F01D5/12 ,  F01D5/28 ,  F01D9/02 ,  F05D2220/30 ,  F05D2230/237 ,  F05D2230/40 ,  F05D2230/80 ,  F05D2300/175 ,  F05D2300/177 ,  Y10T403/479

摘要： A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects.

公开(公告)号：US20160199930A1

公开(公告)日：2016-07-14

申请号：US14596250

申请日：2015-01-14

申请人： Siemens Energy, Inc.

发明人： James A. Yarbrough

IPC分类号： B23K1/00 ,  C22C30/00 ,  B23K1/20

CPC分类号： B23K1/0018 ,  B23K1/20 ,  B23K2101/001 ,  B23K2103/26 ,  B23P6/005 ,  C22C30/00 ,  F01D5/005 ,  F01D11/122 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  F05D2240/11

摘要： A method disclosed herein involves disposing (125) a pre-sintered preform (50) onto a machined component surface (44) to form a pre-braze assembly. The pre-braze assembly is then heated (130) in order the melt the preform at a temperature less than a liquidus temperature of the component surface to form a multi-layer component (52) having a protective surface (56). The preform may be formed by sintering a first powder including a protective alloy and a second powder including a composition of the protective alloy that is supplemented with an additional element such that a solidus temperature of the second powder is lower than a solidus temperature of the first powder. The method allows a service run gas turbine ring segment (30) to be repaired without chemical stripping or welding.

摘要翻译： 本文公开的方法涉及将预烧结的预成型件（50）布置（125）到加工的部件表面（44）上以形成预钎焊组件。 然后将预钎焊组件加热（130），以使预成型体在低于部件表面的液相线温度的温度下熔化，以形成具有保护表面（56）的多层部件（52）。 预成型体可以通过烧结包括保护合金的第一粉末和包含补充有附加元素的保护合金的组合物的第二粉末形成，使得第二粉末的固相线温度低于第一粉末的固相线温度 粉末。 该方法允许在没有化学剥离或焊接的情况下修理服务运行燃气涡轮环段（30）。