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81.发明申请Method for providing turbulation on the inner surface of holes in an article, and related articles 审中-公开在物品的孔的内表面上提供紊流的方法及相关物品公开(公告)号：US20060138195A1
公开(公告)日：2006-06-29
申请号：US11054635
申请日：2005-02-08
申请人： Wayne Hasz , Nesim Abuaf , Robert Johnson , Ching-Pang Lee
发明人： Wayne Hasz , Nesim Abuaf , Robert Johnson , Ching-Pang Lee
IPC分类号： A47J36/02
CPC分类号： F28F13/18 , B23K35/30 , F01D5/147 , F01D5/186 , F05C2201/0463 , F05C2201/0466 , F05D2230/10 , F05D2230/21 , F05D2230/22 , F05D2230/23 , F05D2230/40 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F05D2300/132 , F05D2300/172 , F05D2300/222 , Y02T50/67 , Y02T50/676 , Y10T428/12993
摘要： A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.
摘要翻译： 描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。 首先将该紊乱施加到最终可以插入通道孔中的基底。 基板通常是由牺牲材料形成的棒或管。 在对基板施加了混浊之后，将基板插入到通孔中。 然后使用常规的加热技术将紊乱材料熔合到内表面。 然后可以通过各种技术从孔中去除牺牲衬底。 还描述了相关文章。
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公开(公告)号：US06981841B2
公开(公告)日：2006-01-03
申请号：US10718149
申请日：2003-11-20
IPC分类号： F03D11/00
CPC分类号： F01D25/12 , F01D5/082 , F01D5/084 , F01D5/085 , F02C7/18 , Y02T50/673 , Y02T50/676
摘要： A turbofan engine includes in serial flow communication a first fan, second fan, multistage compressor, combustor, first turbine, second turbine, and third turbine. The first turbine is joined to the compressor by a first shaft. The second turbine is joined to the second fan by a second shaft. And, the third turbine is joined to the first fan by a third shaft. First, second, and third cooling circuits are joined to different stages of the compressor for cooling the forward and aft sides and center bore of the first turbine with different pressure air.
摘要翻译： 涡轮风扇发动机包括串联流动连通的第一风扇，第二风扇，多级压缩机，燃烧器，第一涡轮机，第二涡轮机和第三涡轮机。 第一涡轮机通过第一轴连接到压缩机。 第二涡轮机通过第二轴连接到第二风扇。 并且，第三涡轮机通过第三轴接合到第一风扇。 第一，第二和第三冷却回路连接到压缩机的不同阶段，用不同的压力空气冷却第一涡轮机的前后侧和中心孔。
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公开(公告)号：US06919121B2
公开(公告)日：2005-07-19
申请号：US10153929
申请日：2002-05-23
申请人： William R. Stowell , Robert A. Johnson , Andrew J. Skoog , Joseph Thomas Begovich , Thomas Walter Rentz , Jane Ann Murphy , Ching-Pang Lee , Dainel P. Ivkovich, Jr.
发明人： William R. Stowell , Robert A. Johnson , Andrew J. Skoog , Joseph Thomas Begovich , Thomas Walter Rentz , Jane Ann Murphy , Ching-Pang Lee , Dainel P. Ivkovich, Jr.
IPC分类号： F01D5/28 , C23C4/10 , C23C18/06 , C23C18/12 , C23C24/08 , C23C26/00 , C23C28/00 , F02C7/00 , B32B35/00
CPC分类号： C23C24/08 , Y02T50/67 , Y10T428/20 , Y10T428/24479 , Y10T428/24521 , Y10T428/25 , Y10T428/252
摘要： A method of repairing a thermal barrier coating (16) on a component (10) designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating (16) on a component (10) that has suffered localized spallation (20) of the thermal barrier coating (16). After cleaning the surface area (22) of the component (10) exposed by the localized spallation (20), a ceramic paste (24) comprising a ceramic powder in a binder is applied to the surface area (22) of the component (10). The binder is then reacted to yield a ceramic-containing repair coating (26) that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating (26) has a ceramic matrix. The repair method can be performed while the component (10) remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.
摘要翻译： 修复设计用于恶劣热环境的部件（10）上的热障涂层（16）的方法，所述部件（10）用于燃气涡轮发动机的涡轮机，燃烧器和增压器部件。 该方法更具体地涉及修复已经遭受热隔离涂层（16）的局部剥落（20）的部件（10）上的热障涂层（16）。 在清洁通过局部剥离（20）暴露的组分（10）的表面积（22）之后，将包含粘合剂中的陶瓷粉末的陶瓷浆料（24）施加到组分（10）的表面区域（22） ）。 然后使粘合剂反应以产生覆盖部件的表面积的含陶瓷的修补涂层（26），并且将包含在粘合剂反应时形成的材料的基质中的陶瓷粉末。 粘合剂优选是陶瓷前体材料，其可以立即转化为陶瓷或随时间而热分解形成陶瓷，使得修补涂层（26）具有陶瓷基体。 可以在组件（10）保持安装（例如，在燃气涡轮发动机中）的情况下执行修理方法。 在反应步骤之后，燃气涡轮发动机可以立即恢复操作，在此期间粘合剂进一步反应/转化，并且修复涂层的强度增加。
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84.发明授权Method for providing turbulation on the inner surface of holes in an article, and related articles 有权在物品的孔的内表面上提供紊流的方法及相关物品公开(公告)号：US06910620B2
公开(公告)日：2005-06-28
申请号：US10271098
申请日：2002-10-15
IPC分类号： F01D5/08 , B23K35/30 , C22C19/05 , C22C19/07 , C22C38/00 , F01D5/14 , F01D5/18 , F01D5/28 , F02C7/00 , F28F13/18 , B23K35/12 , B05D3/02 , B23K31/00
CPC分类号： F28F13/18 , B23K35/30 , F01D5/147 , F01D5/186 , F05C2201/0463 , F05C2201/0466 , F05D2230/10 , F05D2230/21 , F05D2230/22 , F05D2230/23 , F05D2230/40 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F05D2300/132 , F05D2300/172 , F05D2300/222 , Y02T50/67 , Y02T50/676 , Y10T428/12993
摘要： A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.
摘要翻译： 描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。 首先将该紊乱施加到最终可以插入通道孔中的基底。 基板通常是由牺牲材料形成的棒或管。 在对基板施加了混浊之后，将基板插入到通孔中。 然后使用常规的加热技术将紊乱材料熔合到内表面。 然后可以通过各种技术从孔中去除牺牲衬底。 还描述了相关文章。
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公开(公告)号：US20050118023A1
公开(公告)日：2005-06-02
申请号：US10881506
申请日：2004-06-29
申请人： Ronald Bunker , Ching-Pang Lee
发明人： Ronald Bunker , Ching-Pang Lee
CPC分类号： F28F13/12 , F01D5/187 , F05D2230/90 , F05D2250/28 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F28F3/022 , F28F3/044 , Y02T50/67 , Y02T50/671 , Y02T50/676 , Y10T29/4932
摘要： A component includes at least one wall having an inner portion and an outer portion. A number of pins extend between the inner and outer portions. The pins define a mesh cooling arrangement with a number of flow channels. The inner portion of the wall defines a number of dimples. A method for forming a number of cooling holes in a component is described. The component has at least one wall with inner and outer portions. The inner portion defines a number of dimples. The method includes centering a drilling tool on a dimple, drilling at least one impingement cooling hole through the inner portion of the wall at the dimple using the drilling tool, and repeating the centering and drilling steps for a number of dimples to drill a number of impingement cooling holes in the inner portion of the wall.
摘要翻译： 一个部件包括至少一个具有内部部分和外部部分的壁。 多个销在内部和外部之间延伸。 销钉定义了具有多个流动通道的网状冷却装置。 壁的内部部分限定了多个凹坑。 描述了在部件中形成多个冷却孔的方法。 该部件具有至少一个具有内部和外部部分的壁。 内部部分限定了一些凹坑。 该方法包括将钻孔工具定中在凹坑上，使用钻孔工具在凹坑处穿过壁的内部部分的至少一个冲击冷却孔钻孔，并重复多个凹坑的定中心和钻孔步骤以钻出若干个 在壁的内部的冲击冷却孔。
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公开(公告)号：US20050058534A1
公开(公告)日：2005-03-17
申请号：US10664192
申请日：2003-09-17
申请人： Ching-Pang Lee , Ramgopal Darolia
发明人： Ching-Pang Lee , Ramgopal Darolia
CPC分类号： F01D11/24 , F01D5/288 , F01D25/12 , F05D2260/204 , Y02T50/67 , Y02T50/676
摘要： A turbine wall includes a metal substrate having front and back surfaces. A thermal barrier coating is bonded atop the front surface. A network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.
摘要翻译： 涡轮壁包括具有前表面和后表面的金属基底。 隔热涂层粘结在前表面顶部。 流动通道网络层压在基板和涂层之间，用于在其间承载空气冷却剂以冷却隔热涂层。
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公开(公告)号：US20050028531A1
公开(公告)日：2005-02-10
申请号：US10422314
申请日：2003-04-24
摘要： A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where a plurality of spaced detonation passages are disposed therethrough. Each detonation passage includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the aft surface of the cylindrical member to create a torque which causes the cylindrical member to rotate. Each detonation passage further includes a first end located adjacent the forward surface of the cylindrical member and a second end located adjacent the aft surface of the cylindrical member.
摘要翻译： 用于具有延伸穿过其中的纵向中心线轴的燃气涡轮发动机的脉冲爆震系统包括具有前表面，后表面和外周表面的可旋转圆柱形构件，其中多个间隔开的爆震通道穿过其中。 每个爆震通道包括至少一个具有延伸穿过的纵向轴线的部分，该纵向轴线以与纵向中心线轴线成圆周方向定位。 脉冲爆震系统还包括可旋转地连接到圆柱形构件的轴和定子，其与圆柱形构件的前表面和轴的一部分间隔开地配置。 定子具有至少一组端口，当圆柱形构件旋转时，该组端口可与引爆通道对准。 以这种方式，在引爆通道中进行爆震循环，使得燃烧气体离开圆柱形构件的后表面以产生使圆柱形构件旋转的扭矩。 每个引爆通道还包括位于圆柱形构件的前表面附近的第一端和位于圆柱形构件的后表面附近的第二端。
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公开(公告)号：US06838190B2
公开(公告)日：2005-01-04
申请号：US10028109
申请日：2001-12-20
申请人： Ching-Pang Lee , Melvin Robert Jackson , Stephen Joseph Ferrigno , Gary Edward Trewiler , Mark Daniel Gorman
发明人： Ching-Pang Lee , Melvin Robert Jackson , Stephen Joseph Ferrigno , Gary Edward Trewiler , Mark Daniel Gorman
CPC分类号： B32B15/018 , C22C5/04 , C22C27/06 , Y10T428/1275 , Y10T428/12847 , Y10T428/12868 , Y10T428/12875 , Y10T428/12944
摘要： A protected article includes a nickel-base superalloy substrate, an interlayer overlying the substrate, and a protective layer overlying the interlayer. The protective layer has a composition comprising at least one of rhodium, platinum, palladium, and ruthenium. In one composition, palladium is present in an amount of from about 1 to about 41 atomic percent; platinum is present in an amount of about (40+atomic percent palladium) atomic percent for palladium ranging from about 1 atomic percent to about 14 atomic percent and up to about 54 atomic percent for palladium ranging from about 15 atomic percent up to about 41 atomic percent; rhodium is present in an amount of at least about 24 atomic percent; zirconium, hafnium, titanium, and mixtures thereof are present in an amount of from zero up to about 5 atomic percent; and ruthenium is present in an amount of from zero up to about 5 atomic percent, balance impurities. The interlayer has a coefficient of thermal expansion intermediate between that of the substrate and that of the protective layer. The protected article is fabricated by furnishing the substrate, applying the interlayer over the substrate, and applying the protective layer over the interlayer. The application of the protective layer may be, for example, by welding or attachment of a solid piece.
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公开(公告)号：US06832889B1
公开(公告)日：2004-12-21
申请号：US10616023
申请日：2003-07-09
IPC分类号： F03D1100
CPC分类号： F01D5/20 , F01D5/184 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall of the airfoil short of the airfoil trailing edge. A third bridge has opposite ends joined to the pressure sidewall and the second bridge to define with the first bridge a supply channel for the leading edge channel, and defines with the second bridge a louver channel extending aft along the second bridge to its distal end at the pressure sidewall.
摘要翻译： 涡轮机叶片包括与燕尾形整体连接的中空翼片。 翼型件包括限定在翼型件前缘后面的流动通道的穿孔第一桥。 第二桥隔开在第一桥后面并且从机翼后缘的翼型的压力侧壁延伸出来。 第三桥具有连接到压力侧壁和第二桥的相对端，第一桥与第一桥形成用于前缘通道的供应通道，并且与第二桥一起限定沿着第二桥向后延伸到其远端的百叶窗通道 压力侧壁。
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公开(公告)号：US06761956B2
公开(公告)日：2004-07-13
申请号：US10028108
申请日：2001-12-20
IPC分类号： B32B310
CPC分类号： C23C28/321 , C23C28/3455 , F01D5/288 , F05D2230/90 , F05D2260/20 , F23R3/002 , F23R3/06 , Y02T50/67 , Y02T50/673 , Y02T50/676 , Y10T428/12361 , Y10T428/12479 , Y10T428/12611 , Y10T428/24273 , Y10T428/24322 , Y10T428/26
摘要： A gas turbine engine component includes a perforate metal wall having pores extending therethrough. The wall has a first surface covered by a thermal barrier coating. The pores have first ends which are covered by the thermal barrier coating, and the pores are ventilated from an opposite second surface of the wall for cooling the thermal barrier coating.
摘要翻译： 燃气涡轮发动机部件包括具有贯穿其中延伸的孔的穿孔金属壁。 该壁具有由热障涂层覆盖的第一表面。 孔具有由热障涂层覆盖的第一端，并且孔从壁的相对的第二表面通风以冷却热障涂层。
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