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1. 发明专利

JP2007031836A Powder metal rotating components for turbine engines and process therefor 审中-公开
标题翻译：用于涡轮发动机的粉末金属旋转部件及其过程
公开(公告)号：JP2007031836A
公开(公告)日：2007-02-08
申请号：JP2006198882
申请日：2006-07-21
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： JACKSON JOSEPH J , SCHAEFFER JON C
IPC分类号： C22C1/04 , B22F3/17 , C22C19/05 , F01D5/06 , F01D5/28 , F02C7/00
CPC分类号： B22F3/14 , B22F5/009 , B22F2998/00 , B22F2998/10 , B23P15/006 , C22C19/055 , B22F3/15 , B22F3/20 , B22F9/08 , B22F1/0003 , B22F3/17 , B22F1/0085
摘要： PROBLEM TO BE SOLVED: To provide a process for producing turbine rotors and other large rotating components of power-generating gas turbine engines using powder metallurgy techniques.
SOLUTION: The process involves forming a powder of a gamma prime or gamma double prime precipitation-strengthened nickel-based superalloy whose particles are about 0.100 mm in diameter or smaller. The powder is placed in a can and consolidated to produce an essentially fully dense consolidation, which is then hot worked to produce a billet of a size sufficient to form a forging of at least 2300 kg. The billet is forged at a temperature and strain rate to produce a forging with a uniform fine grain of ASTM 10 or finer. Thereafter, the forging may undergo a heat treatment to achieve a desired balance of mechanical properties while retaining a uniform grain size of ASTM 10 or finer.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：提供使用粉末冶金技术来生产发电燃气轮机的涡轮转子和其它大的旋转部件的方法。解决方案：该方法包括形成粒径为约0.1mm或更小的γ'或γ双键沉淀强化的镍基超级合金的粉末。将粉末放置在罐中并固化以产生基本上完全致密的固结，然后将其热加工以产生足以形成至少2300kg的锻造的坯料。坯料以温度和应变速率锻造，以产生具有ASTM 10均匀细粒度或更细的锻件。此后，锻造可以进行热处理，以达到所需的机械性能平衡，同时保持ASTM 10的均匀晶粒尺寸或更细。版权所有（C）2007，JPO＆INPIT

2. 发明专利

JP2010180477A High corrosion resistance precipitation hardened martensitic stainless steel 有权
标题翻译：高耐腐蚀降解硬化马氏体不锈钢
公开(公告)号：JP2010180477A
公开(公告)日：2010-08-19
申请号：JP2010020823
申请日：2010-02-02
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： CHEN JIANQIANG , MOORS THOMAS MICHAEL , SCHAEFFER JON C
IPC分类号： C22C38/00 , C21D6/00 , C22C38/48 , C22C38/60 , F04D29/02 , F04D29/32 , F04D29/54
CPC分类号： C22C38/20 , C21D8/005 , C22C38/42
摘要： PROBLEM TO BE SOLVED: To provide a precipitation hardened martensitic stainless steel which is suitable for a turbine rotary component.
SOLUTION: The precipitation-hardened stainless steel alloy comprises, by weight: about 14.0 to about 16.0% chromium; about 6.0 to about 7.0% nickel; about 1.25 to about 1.75% copper; about 0.5 to about 2.0% molybdenum; about 0.025 to about 0.05% carbon; niobium in an amount greater than about twenty times to about twenty-five times that of carbon; and the balance iron and incidental impurities. The alloy has an aged microstructure and ultimate tensile strength of at least about 1,100 MPa and Charpy V-notch toughness of at least about 69 J. The aged microstructure includes martensite and not more than about 10% reverse-transformed austenite and is useful for making turbine airfoils.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供适用于涡轮机旋转部件的沉淀硬化马氏体不锈钢。解决方案：沉淀硬化的不锈钢合金包含重量：约14.0至约16.0％的铬; 约6.0至约7.0％的镍; 约1.25至约1.75％的铜; 约0.5至约2.0％的钼; 约0.025至约0.05％的碳; 铌的量大于碳的二十倍至二十五倍; 余铁和附带杂质。该合金具有至少约1100MPa的老化组织和极限拉伸强度以及至少约69J的夏比V-缺口韧性。老化的微结构包括马氏体和不超过约10％的反向转变奥氏体，并且可用于制备涡轮机翼型。版权所有（C）2010，JPO＆INPIT

3. 发明专利

JP2004003470A Method for manufacturing insert for component of steam-cooling type high-temperature gas flow passage 审中-公开
公开(公告)号：JP2004003470A
公开(公告)日：2004-01-08
申请号：JP2003119168
申请日：2003-04-24
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： DEVINE ROBERT H , PLACKO JAMES M , DOWNS JUSTIN W , SCHAEFFER JON C , PETERSON LANCE G
IPC分类号： F01D5/18 , B22C9/04 , B22C9/24 , B22D13/06 , B22D18/02 , B22D21/00 , B22D29/00 , F01D5/28 , F01D9/02 , F02C7/00
CPC分类号： B22D29/002 , B22C9/04
摘要： PROBLEM TO BE SOLVED: To provide a method for forming an insert for a component of a steam-cooling type high-temperature gas flow passage.
SOLUTION: This method includes a step of casting an insert (10), and a step of laser-drilling the cast insert (10) while a ceramic core (12) is still in a predetermined position. Thereafter, the ceramic core (12) is removed by using an exudate. By performing the laser-drilling (14) of a hole (16) while the ceramic core (12) is still in the predetermined position, the ceramic core (12) works as a backing supporter during the laser-drilling (14), which brings the drilling of the insert (10) with high accuracy and the shortening of the working time.
COPYRIGHT: (C)2004,JPO

4. 发明专利

JP2010038156A Compressor blade leading edge shim and related method 审中-公开
标题翻译：压缩机叶片前沿叶片及相关方法
公开(公告)号：JP2010038156A
公开(公告)日：2010-02-18
申请号：JP2009172612
申请日：2009-07-24
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SCHAEFFER JON C , PABLA SURINDER S , HELMICK DAVID A , ROBERTS JEFFREY
IPC分类号： F04D29/38 , F04D29/02
CPC分类号： F04D29/023 , F01D5/005 , F01D5/28 , F04D29/324 , F05D2230/23 , F05D2230/80 , F05D2240/303 , F05D2260/95 , F05D2300/2284 , Y10T29/49337
摘要： PROBLEM TO BE SOLVED: To reduce damage to the leading edge of a compressor blade resulting from erosion and/or corrosion. SOLUTION: This method of improving an erosion and/or corrosion resistance at the leading edge of a compressor blade airfoil includes: (a) preparing a leading edge portion of the compressor blade airfoil; and (b) attaching one or more shims to the leading edge portion. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：减少由于腐蚀和/或腐蚀而导致的压缩机叶片前缘的损坏。解决方案：提高压缩机叶片翼型的前缘处的侵蚀和/或耐腐蚀性的方法包括：（a）制备压缩机叶片翼型件的前缘部分; 和（b）将一个或多个垫片附接到前缘部分。版权所有（C）2010，JPO＆INPIT

5. 发明专利

JP2007283405A Method for welding nickel base superalloy 审中-公开
标题翻译：焊接镍基焊接方法
公开(公告)号：JP2007283405A
公开(公告)日：2007-11-01
申请号：JP2007103590
申请日：2007-04-11
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： ARNETT MICHAEL D , NOWAK DANIEL A , SCHAEFFER JON C
IPC分类号： B23K31/00 , B23K1/19 , B23K9/23 , B23K31/02
CPC分类号： B23K9/02 , B23K1/0018 , B23K31/02 , B23K2201/001 , B23P6/007 , B23P6/045 , F01D5/005 , F05D2230/237 , F05D2230/40
摘要： PROBLEM TO BE SOLVED: To provide a new welding method to solve such problems that a nickel base superalloy containing a high content of γ' phase develops cracks very easily when it is welded or when it is heat-treated after welding and also characteristics of the basic material may be substantially deteriorated by the application of the conventional welding method.
SOLUTION: This method is a welding method for welding superalloy members (10) and (12), and comprises (a) the step wherein a groove for welding (14) is formed at the contact surface between the members, (b) the step wherein the members are weld by using filler metal (16) at ambient temperature, (c) the step wherein a brazing paste (18) is applied between the filler metal and the members on the adjoining surfaces and (d) the step of heat-treatment of the members including a stress relieving cycle and a brazing cycle. The same method can be applied to repair cracks in a member made of the nickel base superalloy.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：为了解决这样的问题，提供一种新的焊接方法，即当焊接时或者焊接后进行热处理时，含有高γ含量的镍基超合金会非常容易地产生裂纹通过使用常规的焊接方法，基本材料的特性可能会显着劣化。解决方案：该方法是用于焊接超合金构件（10）和（12）的焊接方法，并且包括（a）在构件之间的接触表面处形成用于焊接的沟槽（14）的步骤，（b ）其中通过在环境温度下使用填充金属（16）对构件进行焊接的步骤，（c）在填充金属和邻接表面上的构件之间施加钎焊膏（18）的步骤，以及（d）步骤包括应力消除循环和钎焊循环的构件的热处理。可以应用相同的方法来修复由镍基超级合金制成的构件中的裂纹。版权所有（C）2008，JPO＆INPIT

6. 发明专利

JP2010075999A Unidirectionally-solidification process and casting formed thereby 审中-公开
标题翻译：非常方便的固化工艺和铸造成型
公开(公告)号：JP2010075999A
公开(公告)日：2010-04-08
申请号：JP2009218349
申请日：2009-09-24
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SCHAEFFER JON C , BALSONE STEPHEN JOSEPH , ELLIOTT ANDREW J
IPC分类号： B22D27/04 , B22C9/22 , B22D21/00
CPC分类号： B22D27/045 , C30B11/003 , C30B29/52 , F05B2230/21 , F05C2253/083
摘要： PROBLEM TO BE SOLVED: To provide a process capable of producing large metallic castings having lengths of one hundred centimeters or more and a unidirectional crystal structure substantially free of freckle defects. SOLUTION: The process includes pouring a molten metal alloy into a preheated mold within a heating zone, withdrawing the mold from the heating zone, through a heat shield, and into a cooling zone to directionally solidify the molten metal alloy, and then cooling the mold to produce the casting and the unidirectional crystal structure thereof. The heat shield operates as a barrier to thermal radiation between the heating zone and the cooling zone, and the mold is withdrawn at a rate that, in combination with the heat shield, maintains a thermal gradient to solidify the molten metal alloy and form primary dendrite arms having an average spacing therebetween of about 150 to about 500 μm. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够生产长度为100厘米或更大的大型金属铸件和基本上不含雀斑缺陷的单向晶体结构的方法。解决方案：该方法包括将熔融金属合金浇注到加热区域内的预热模具中，通过隔热罩将模具从加热区域中取出，并进入冷却区域以使熔融金属合金定向凝固，然后冷却模具以生产铸件及其单向晶体结构。隔热罩作为加热区域和冷却区域之间的热辐射的屏障，并以与隔热层结合的温度保持热梯度以固化熔融金属合金并形成初级枝晶的速率取出模具具有约150至约500μm的平均间隔的臂。版权所有（C）2010，JPO＆INPIT

7. 发明专利

JP2009161859A Erosion and corrosion-resistant coating system and process therefor 审中-公开
标题翻译：耐腐蚀和耐腐蚀涂料体系及其工艺
公开(公告)号：JP2009161859A
公开(公告)日：2009-07-23
申请号：JP2009000530
申请日：2009-01-06
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： PABLA SURINDER SINGH , SCHAEFFER JON C , PAREEK VINOD KUMAR , BUCCI DAVID VINCENT , MOORS THOMAS , LIPKIN JANE MARIE
IPC分类号： C23C28/00 , F01D25/00 , F02C7/00 , F04D29/38
CPC分类号： F01D5/288 , C23C4/02 , C23C4/11 , C23C4/18 , C23C28/00 , C23C28/321 , C23C28/322 , C23C28/3225 , C23C28/345 , C23C28/3455 , C23C28/347 , C23C30/00 , F05D2260/95 , F05D2300/21 , Y10T428/31678
摘要： PROBLEM TO BE SOLVED: To provide a coating system and process capable of providing erosion and corrosion-resistance to a component, particularly a steel compressor blade of an industrial gas turbine. SOLUTION: The coating system includes a metallic sacrificial undercoat 12 on a surface of the component substrate, and a ceramic topcoat 14 deposited by thermal spray on the undercoat 12. The undercoat 12 contains a metal or metal alloy that is more active in the galvanic series than iron, and electrically contacts the surface of the substrate. The ceramic topcoat 14 consists essentially of a ceramic material chosen from the group consisting of mixtures of alumina and titania, mixtures of chromia and silica, mixtures of chromia and titania, mixtures of chromia, silica, and titania, and mixtures of zirconia, titania, and yttria. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供能够对工业燃气轮机的部件，特别是钢制压缩机叶片提供侵蚀和耐腐蚀性的涂覆系统和工艺。解决方案：涂层系统包括在组件衬底的表面上的金属牺牲底涂层12和通过热喷涂沉积在底涂层12上的陶瓷顶涂层14.底涂层12含有更有活性的金属或金属合金电流系列比铁，并且电接触衬底的表面。陶瓷面漆14基本上由选自氧化铝和二氧化钛的混合物，氧化铬和二氧化硅的混合物，氧化铬和二氧化钛的混合物，氧化铬，二氧化硅和二氧化钛的混合物以及氧化锆，二氧化钛，和氧化钇。版权所有（C）2009，JPO＆INPIT

8. 发明专利

JP2009013452A Machine component and manufacturing method 审中-公开
标题翻译：机器组件和制造方法
公开(公告)号：JP2009013452A
公开(公告)日：2009-01-22
申请号：JP2007174784
申请日：2007-07-03
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： FENG GANJIANG , DIMASCIO PAUL S , SCHAEFFER JON C
IPC分类号： C23C4/06 , C23C4/10 , C23C28/00 , F01D5/28 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a thermal barrier coating (TBC) system (110). SOLUTION: The system has at least one thermal barrier coating (TBC) bond coat layer (112) formed on the surface region (108) of a substrate. The TBC bond coat layer contains at least one TBC bond coat material. The TBC bond coat material is a nickel-chromium-aluminum-yttrium (NiCrAlY) composition containing silicon (Si), hafnium (Hf) and also COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种隔热涂层（TBC）系统（110）。解决方案：该系统具有形成在基板的表面区域（108）上的至少一个热障涂层（TBC）粘合涂层（112）。 TBC粘合涂层含有至少一种TBC粘结涂层材料。 TBC粘合涂层材料是含有硅（Si），铪（Hf）以及<10wt。％钴的镍铬 - 铝 - 钇（NiCrAlY）组合物。 TBS系统还具有形成在TBC粘结涂层上的至少一个顶涂层（120）。版权所有（C）2009，JPO＆INPIT

9. 发明专利

JP2010209913A Erosion and corrosion resistant turbine compressor airfoil and method of making the same 审中-公开
标题翻译：耐腐蚀和耐腐蚀涡轮压缩机气动及其制造方法
公开(公告)号：JP2010209913A
公开(公告)日：2010-09-24
申请号：JP2010047302
申请日：2010-03-04
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： LIPKIN JANE MARIE , ANAND KRISHNAMURTHY , BUCCI DAVID VINCENT , LAU YUK-CHIU , PABLA SURINDER , PAREEK VINOD KUMAR , SCHAEFFER JON C , SUNDARARAJAN GURUPRASAD
IPC分类号： F04D29/38 , F04D29/02
CPC分类号： C23C30/00 , C23C4/06 , C23C28/00 , C23C28/042 , C23C28/321 , C23C28/322 , C23C28/3225 , C23C28/324 , C23C28/34 , C23C28/341 , C23C28/345 , C23C28/3455 , C23C28/42 , F04D29/023 , F04D29/324 , F05D2230/31 , F05D2260/95 , F05D2300/611
摘要： PROBLEM TO BE SOLVED: To provide a stainless steel turbine compressor airfoil having improved resistance to both erosion and corrosion. SOLUTION: An erosion-resistant and sacrificial turbine compressor airfoil has a modified airfoil surface 32. The airfoil surface 32 has an airfoil coating which includes a sacrificial coating 62 including a layer of Al, Cr, Zn, an Ni-Al alloy, an Al-Si alloy, an Al-based alloy, a Cr-based alloy, a Zn-based alloy, an Al polymer composite, or a combination thereof, or a layer of a conductive undercoat 70 and an overcoat 72 which is disposed on the undercoat 70 and has a plurality of ceramic particles and conductive particles embedded in an inorganic matrix binder. One of the sacrificial coating 62 or an erosion-resistant coating 64 is disposed on the airfoil surface 32, and the other of a corrosion-resistant coating or the erosion-resistant coating 64 is disposed on the one, and the sacrificial coating 62 is more anodic than the airfoil surface 32 or the erosion-resistant coating 64. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供具有改善的抵抗侵蚀和腐蚀的不锈钢涡轮压缩机翼型。解决方案：抗侵蚀和牺牲的涡轮压缩机翼型件具有改进的翼型表面32.翼型件表面32具有翼型涂层，其包括牺牲涂层62，牺牲涂层62包括Al，Cr，Zn，Ni-Al合金层，Al-Si合金，Al系合金，Cr系合金，Zn系合金，Al聚合物复合体或其组合，或配置在导电性底涂层70和外涂层72上的层在底涂层70上具有多个陶瓷颗粒和嵌入无机基质粘合剂中的导电颗粒。牺牲涂层62或抗侵蚀涂层64之一设置在翼型表面32上，并且耐腐蚀涂层或抗侵蚀涂层64中的另一个设置在一个上，并且牺牲涂层62更多阳极比翼型表面32或抗侵蚀涂层64.版权所有（C）2010，JPO＆INPIT

10. 发明专利

JP2013139633A Processes for coating turbine rotor and article thereof 审中-公开
标题翻译：用于涂覆涡轮转子及其制品的方法
公开(公告)号：JP2013139633A
公开(公告)日：2013-07-18
申请号：JP2012275233
申请日：2012-12-18
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： AMANCHERLA SUNDAR , ANAND KRICHNAMURTHY , CALLA EKLAVYA , SCHAEFFER JON C , HARIHARAN S
IPC分类号： C23C28/00 , B24C1/10 , C23C24/04 , F01D5/02 , F01D25/00 , F02C7/00 , F02C7/28
CPC分类号： C23C4/02 , C23C4/06 , C23C4/08 , C23C4/18 , C23C24/04 , C23C28/022 , C23C28/027
摘要： PROBLEM TO BE SOLVED: To provide a coating on a surface of a turbine rotor configured to reduce the wear of brush seals in a turbine engine.SOLUTION: A process for applying a hard coating to the turbine rotor includes steps of: providing a turbine rotor having at least one surface; applying a first coating to the at least one surface, the first coating being cold sprayed onto the at least one surface; applying a second coating onto the first coating to form the hard coating. The hard coating is configured to substantially resist wear of the brush seal in physical communication with the turbine rotor.
摘要翻译：要解决的问题：在涡轮转子的表面上提供涂层，其构造成减少涡轮发动机中的电刷密封件的磨损。解决方案：将硬涂层施加到涡轮转子的方法包括以下步骤：提供涡轮转子具有至少一个表面; 将第一涂层施加到所述至少一个表面，所述第一涂层被冷喷涂到所述至少一个表面上; 将第二涂层施加到第一涂层上以形成硬涂层。硬涂层构造成基本上抵抗与涡轮转子物理连通的刷密封件的磨损。

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