专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20180022649A1 COATED MEMBER, COATING MATERIAL, AND METHOD OF MANUFACTURING COATED MEMBER 审中-公开
公开(公告)号：US20180022649A1
公开(公告)日：2018-01-25
申请号：US15549516
申请日：2016-02-09
申请人： MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.
发明人： Mineaki MATSUMOTO , Takayuki KURIMURA , Kosuke NISHIKAWA , Tadayuki HANADA
IPC分类号： C04B35/48 , C04B35/486
CPC分类号： C04B35/481 , C04B35/10 , C04B35/16 , C04B35/486 , C04B35/488 , C04B35/565 , C04B35/62675 , C04B35/653 , C04B35/803 , C04B35/806 , C04B41/009 , C04B41/5024 , C04B41/85 , C04B2235/3224 , C04B2235/3225 , C04B2235/3246 , C04B2235/5224 , C04B2235/5244 , C04B2235/5436 , C04B2235/5445 , C04B2235/5454 , C04B2235/76 , C04B2235/9607 , C23C4/11 , C23C28/042 , C23C28/044 , F01D5/288 , F05D2300/15 , F05D2300/211 , F23R3/42 , Y02T50/672 , Y02T50/6765 , C04B41/4527 , C04B41/5042 , C04B2103/0021
摘要： A coated member includes a heat-shielding coating layer made of a zirconia-dispersed silicate in which ytterbia-stabilized zirconia is precipitated as a dispersed phase in a matrix phase which is any one of a rare earth disilicate, a rare earth monosilicate, and a mixed phase of the rare earth disilicate and the rare earth monosilicate. The rare earth disilicate is a (Y1-a[Ln1]a)2Si2O7 solid solution wherein Ln1 is any one of Sc, Yb, and Lu, or a (Y1-c[Ln2]c)2Si2O7 solid solution wherein Ln2 is any one of Nd, Sm, Eu, and Gd. The rare earth monosilicate is Y2SiO5, [Ln1′]2SiO5, a (Y1-b[Ln1′]b)2SiO5 solid solution wherein Ln1′ is any one of Sc, Yb, and Lu, or a (Y1-d[Ln2′]d)2SiO5 solid solution wherein Ln2′ is any one of Nd, Sm, Eu, and Gd.

2. 发明申请

US20170370235A1 TRANSITION PIECE, COMBUSTOR PROVIDED WITH SAME, AND GAS TURBINE PROVIDED WITH COMBUSTOR 审中-公开
公开(公告)号：US20170370235A1
公开(公告)日：2017-12-28
申请号：US15544384
申请日：2016-01-25
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Tetsu KONISHI , Hiroaki KISHIDA , Kentaro TOKUYAMA , Hiroki SHIBATA , Akihiro MURAKAMI
IPC分类号： F01D9/02 , F02C7/18 , F02C3/04 , F01D25/24 , F01D5/08 , F23R3/28 , F01D25/12
CPC分类号： F01D9/023 , F01D5/082 , F01D25/12 , F01D25/24 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23R3/06 , F23R3/28 , F23R3/42
摘要： A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

3. 发明申请

US20170363004A1 COMBUSTOR COMPONENT HAVING ENHANCED COOLING 审中-公开
公开(公告)号：US20170363004A1
公开(公告)日：2017-12-21
申请号：US15187149
申请日：2016-06-20
申请人： United Technologies Corporation
发明人： JinQuan Xu
IPC分类号： F02C7/12 , F23R3/42 , F23R3/30 , F02C7/22 , F02C7/224 , F23R3/34
CPC分类号： F02C7/12 , F02C7/14 , F02C7/222 , F02C7/224 , F05D2220/32 , F05D2240/35 , F05D2260/208 , F23D11/36 , F23D2214/00 , F23R3/283 , F23R3/30 , F23R3/346 , F23R3/42 , F28D15/02 , F28D15/04 , F28D2021/0024 , F28D2021/0026
摘要： Fuel injectors for gas turbine engines are provided herein. The fuel injectors include a nozzle configured to dispense fuel into a combustor of a gas turbine engine, a fuel conduit fluidly connecting a fuel source to the nozzle, and a heat pipe having a vaporization section and a condensation section, wherein the vaporization section is in thermal communication with the nozzle and the condensation section is in thermal communication with a cooling source of the gas turbine engine.

4. 发明申请

US20170343217A1 DUCTING ARRANGEMENT WITH INJECTOR ASSEMBLIES ARRANGED IN AN EXPANDING CROSS-SECTIONAL AREA OF A DOWNSTREAM COMBUSTION STAGE IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170343217A1
公开(公告)日：2017-11-30
申请号：US15165195
申请日：2016-05-26
申请人： Siemens Energy, Inc.
发明人： Yuntao Chen , Juan Enrique Portillo Bilbao , Andrew J. North , Lucky Tran , Joseph Meadows , Walter Ray Laster
IPC分类号： F23R3/34 , F23R3/28 , F23R3/10
CPC分类号： F23R3/346 , F01D9/023 , F02C6/003 , F02C7/222 , F05D2240/35 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/16 , F23R3/18 , F23R3/20 , F23R3/286 , F23R3/34 , F23R3/42 , F23R2900/03341
摘要： A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

5. 发明授权

US09709279B2 System and method for control of combustion dynamics in combustion system 有权
公开(公告)号：US09709279B2
公开(公告)日：2017-07-18
申请号：US14192687
申请日：2014-02-27
申请人： General Electric Company
发明人： Sarah Lori Crothers , Lucas John Stoia , William Francis Carnell, Jr.
IPC分类号： F23R3/46 , F23R3/42 , F23R3/04 , F23R3/16 , F23R3/26
CPC分类号： F23R3/42 , F23R3/04 , F23R3/16 , F23R3/26 , F23R3/46 , F23R2900/00014 , Y02T50/675
摘要： A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path. The second combustor includes a second oxidant flow path and a second perforated structure comprising a second plurality of oxidant ports. The second perforated structure is disposed in the second oxidant flow path and the first perforated structure has at least one difference relative to the second perforated structure.

6. 发明授权

US09618333B2 Clearance measurement device and clearance measurement method for combustor 有权
公开(公告)号：US09618333B2
公开(公告)日：2017-04-11
申请号：US14418228
申请日：2013-09-06
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Yugo Tokunaga , Kenta Taniguchi
IPC分类号： G01C3/08 , G01B11/14 , F23R3/10 , F23R3/46 , F23R3/42 , F02C7/00 , F23R3/28
CPC分类号： G01B11/14 , F02C7/00 , F05D2260/80 , F05D2260/83 , F23R3/10 , F23R3/283 , F23R3/42 , F23R3/46 , F23R2900/00017 , F23R2900/00019
摘要： A clearance measurement device for a combustor includes: a rod part with the hollow base end side which is mounted on a first flange of the combustor while being inserted in the combustor; a support part which is mounted at the leading end of the rod part so as to be rotatable around an axis perpendicular to the axial direction of the rod part; an imaging element which is supported by the support part and images an annular clearance; an operation lever which penetrates the inside of the rod part and extends toward the support part; and a link mechanism which is provided between the operation lever and the support part and converts a forward/backward motion of the operation lever into a rotary motion of the support part around the axis.

7. 发明申请

US20170081964A1 TREATMENT PROCESS, OXIDE-FORMING TREATMENT COMPOSITION, AND TREATED COMPONENT 有权
公开(公告)号：US20170081964A1
公开(公告)日：2017-03-23
申请号：US14857912
申请日：2015-09-18
申请人： GENERAL ELECTRIC COMPANY
发明人： Richard Todd EVERHART
IPC分类号： F01D5/28 , F23R3/42 , F23R3/00 , C09D5/08 , F01D9/04
CPC分类号： F01D5/288 , C09D5/084 , C23C8/42 , C23C8/80 , C23C24/08 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D9/041 , F05D2220/32 , F05D2230/31 , F05D2230/90 , F05D2240/128 , F05D2240/30 , F05D2240/35 , F05D2300/21 , F05D2300/611 , F23R3/002 , F23R3/42
摘要： A treatment process for a gas turbine component comprising a bond coating and a ceramic coating, an oxide-forming treatment composition, and a treated component are disclosed. The ceramic coating is contacted with a treatment composition. The treatment composition includes a carrier and a particulate oxide-forming material suspended within the carrier. The particulate oxide-forming material is one or more of yttria oxide, antimony, or tin oxide. The treatment composition is heated to form an oxide overlay coating on the ceramic coating. The treated component includes a ceramic coating and one or both of a corrosion inhibitor and an oxide formed by an oxide-forming treatment composition having the corrosion inhibitor.

8. 发明申请

US20170058779A1 ENGINE LUBRICATION SYSTEM USING DE-OXYGENATED FUEL 审中-公开
标题翻译：使用脱氧燃料的发动机润滑系统
公开(公告)号：US20170058779A1
公开(公告)日：2017-03-02
申请号：US15139839
申请日：2016-04-27
申请人： ROLLS-ROYCE plc
发明人： Giles E. HARVEY , Martyn RICHARDS
IPC分类号： F02C7/224 , F23R3/42 , F02C7/12 , F23R3/34
CPC分类号： F02C7/224 , F01D25/20 , F02C7/12 , F02C7/16 , F05D2220/32 , F05D2240/50 , F05D2260/205 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F23R3/34 , F23R3/42 , Y02T50/675
摘要： A thermal management system for a gas turbine engine comprises a plurality of first heat generating sub-systems arranged in operable communication with the engine, a fuel supply sub-system, a fuel circulation sub-system, and one or more combustors. The fuel supply sub-system is adapted to supply a de-oxygenated fuel to the fuel circulation sub-system, and the fuel circulation sub-system is adapted to circulate the de-oxygenated fuel to lubricate and cool each of the plurality of first heat generating sub-systems, and then to combust the de-oxygenated fuel in the or each combustor.
摘要翻译：燃气涡轮发动机的热管理系统包括布置成与发动机可操作地连通的多个第一发热子系统，燃料供应子系统，燃料循环子系统和一个或多个燃烧器。燃料供应子系统适于向燃料循环子系统供应脱氧燃料，并且燃料循环子系统适于使脱氧燃料循环以润滑和冷却多个第一热量产生子系统，然后燃烧该或每个燃烧器中的脱氧燃料。

9. 发明授权

US09395082B2 Combustor resonator section with an internal thermal barrier coating and method of fabricating the same 有权
标题翻译：具有内部热障涂层的燃烧器谐振器部分及其制造方法
公开(公告)号：US09395082B2
公开(公告)日：2016-07-19
申请号：US13622452
申请日：2012-09-19
申请人： Siemens Energy, Inc.
发明人： Abhijeet Tiwary , Stephen A. Ramier , Timothy A. Fox , James Bertoncello , Steven Williams
IPC分类号： F02C7/24 , F23R3/00 , F23R3/06 , F23M5/00 , F01N1/02 , F23R3/42 , F23M20/00
CPC分类号： F23M5/00 , F01N1/023 , F02C7/24 , F05D2260/963 , F23M20/005 , F23M2900/05004 , F23R3/002 , F23R3/06 , F23R3/42 , F23R2900/00014 , F23R2900/00017 , F23R2900/00018 , F23R2900/03042 , F23R2900/03044 , Y10T29/49323
摘要： A combustor (100) for a gas turbine engine (30) has a circumferentially extending liner (109) defining at least a portion of an interior combustion chamber (107) and a hot gas path (115). The liner includes a resonator section (112) including at least one resonator (116A, 116B) having a resonator chamber (125A, 125B) formed on an exterior of the liner. A thermal barrier coating (118) is disposed along an inner surface of the liner including an inner surface (130) of the resonator section. The resonator further includes a plurality of apertures (117) and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.
摘要翻译：用于燃气涡轮发动机（30）的燃烧器（100）具有限定内部燃烧室（107）和热气体路径（115）的至少一部分的周向延伸的衬套（109）。衬套包括谐振器部分（112），该谐振器部分包括至少一个谐振器（116A，116B），该谐振器具有形成在衬套的外部上的谐振腔（125A，125B）。隔热层涂层（118）沿着衬套的内表面设置，包括谐振器部分的内表面（130）。谐振器还包括多个孔（117），并且每个孔在谐振器段处延伸穿过衬垫和热障涂层，并且在燃烧室和谐振腔之间存在流体流动连通。

10. 发明授权

US09366444B2 Flexible component providing sealing connection 有权
标题翻译：柔性部件提供密封连接
公开(公告)号：US09366444B2
公开(公告)日：2016-06-14
申请号：US14077594
申请日：2013-11-12
申请人： Anil L. Salunkhe , Dustin C. Boudin
发明人： Anil L. Salunkhe , Dustin C. Boudin
IPC分类号： F23R3/42 , F01D9/02
CPC分类号： F23R3/42 , F01D9/023 , F05D2240/55 , F05D2240/57 , F23R2900/00012
摘要： A sealing component (61) for a turbine (15) positionable at an interface between a transition section (21) for carrying exhaust gas and a turbine inlet section (32). A U-shaped section (45) includes first and second legs (67, 69). When the sealing component is positioned at the interface, the legs extend about the turbine axis. A seal flange (75) connects to the U-shaped section. The positioned sealing component extends about the axis and in a direction away from the first leg. The seal flange faces the inner surface (76) of the flange. A flexible strip (79), positioned radially outward with respect to the seal flange, extends about the axis and extends along the axis between the U-shaped section and the flange. The flexible strip acts as a spring member pressing against the outer surface (96) of the flange.
摘要翻译：一种用于涡轮机（15）的密封部件（61），其位于用于承载废气的过渡部分（21）和涡轮机入口部分（32）之间的界面处。 U形部分（45）包括第一和第二腿部（67,69）。当密封部件位于界面处时，腿部绕涡轮机轴线延伸。密封法兰（75）连接到U形部分。定位的密封部件围绕轴线和远离第一腿部的方向延伸。密封凸缘面对凸缘的内表面（76）。相对于密封凸缘径向向外定位的柔性条（79）围绕该轴线延伸并沿着U形截面和凸缘之间的轴线延伸。柔性带作为压靠凸缘的外表面（96）的弹簧构件。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式