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    • 4. 发明公开
    • Verfahren zur Herstellung einer Turbinenschaufel
    • EP2127781A1
    • 2009-12-02
    • EP08009847.8
    • 2008-05-29
    • SIEMENS AKTIENGESELLSCHAFT
    • Ahmad, Fathi
    • B22D19/08B22D19/10
    • B22D19/08B22D19/10
    • Die Erfindung betrifft ein Verfahren zur Herstellung einer Turbinenschaufel (2, 5), bei dem zunächst eine innere Struktur (1, 6) der Turbinenschaufel (2, 5) gefertigt und dann die innere Struktur (1, 6) mit einer Umhüllung (4, 10) unter Bildung einer äußeren Form der Turbinenschaufel (2, 5) umgossen wird.
    • 该方法包括制造涡轮铲(5)的内部结构(6),然后在形成涡轮铲的外部形式的情况下用盖(10)重新铸造。 内部结构和盖由不同的金属和/或合金制成。 内部结构由具有高抗蠕变性的材料制成,并且该盖由具有高氧化稳定性的材料制成。 冷却通道(7)在内部结构的制造期间形成,其在冷却流体被冷却通道引导的再烧制期间被冷却。 该方法包括制造涡轮铲(5)的内部结构(6),然后在形成涡轮铲的外部形式的情况下用盖(10)重新铸造。 内部结构和盖由不同的金属和/或合金制成。 内部结构由具有高抗蠕变性的材料制成,并且该盖由具有高氧化稳定性的材料制成。 冷却通道(7)在内部结构的制造期间形成,其在冷却流体被冷却通道引导的再烧制期间被冷却。 陶瓷掩蔽元件在重新雕刻内部结构之前固定在内部结构上,以便重新加盖盖中的通道。 通道(9)在盖子上形成有遮蔽元件并与内部结构中的冷却通道连通。 通道在盖中形成有扩散开口。 内部结构被模制。 包括用于涡轮铲的修理过程的独立权利要求。
    • 7. 发明授权
    • Method for forming an article extension by melting of a mandrel in a ceramic mold
    • 一种用于通过在一个陶瓷铸型熔化心轴产生附着过程
    • EP0815991B1
    • 2001-01-31
    • EP97304565.1
    • 1997-06-26
    • GENERAL ELECTRIC COMPANY
    • Bewlay, Bernard PatrickJackson, Melvin RobertRitter, Ann Melinda
    • B22D27/04B22D19/10C30B11/00C30B29/52
    • B22D23/06B22D19/10B23P6/007C30B11/00C30B29/52Y10T29/49318
    • A method for providing an integral extension on an article comprises selecting an article (100) comprising an extension end, an extension bonding surface and an outer surface defined by the cross sectional shape. The extension end also has a superalloy composition and a directionally oriented crystal structure. A mandrel (200) is attached to the extension bonding surface. The mandrel has a cross sectional shape that is compatible with the cross sectional shape of the extension end and an outer surface that communicates with the outer surface of the extension end. The mandrel also has an alloy composition that is compatible with the superalloy composition. A ceramic mould (300) is formed over the outer surface of the mandrel and a portion of the outer surface of the extension end. The mould has a cavity with a shape that is defined by the mandrel and defines the shape of the integral extension. The mandrel is melted under controlled conditions by application of an external heating means, the article, mandrel and mould being oriented either prior to or during the melting so that the molten mandrel contacts the extension bonding surface, for a time sufficient to permit the extension bonding surface to be heated by and interact with the molten mandrel as a microstructure growth seed. The extension end (700) is cooled under controlled thermal conditions so as to cause the molten mandrel to solidify on the growth seed, at an interface between them that moves from the extension bonding surface into the molten mandrel, as an integral extension that conforms to the shape of the mould cavity and has a microstructure that is compatible with the microstructure of the extension end. The controlled thermal conditions comprise maintaining a temperature gradient within the article such that the temperature is highest at the interface and decreases within the article as a function of increasing distance from the interface. Also claimed is a second method for providing an integral extension on an article.
    • 10. 发明公开
    • SYSTEM AND METHOD FOR PERFORMING AN IN SITU REPAIR OF AN INTERNAL COMPONENT OF A GAS TURBINE ENGINE
    • 系统和方法用于执行原位修复的燃气涡轮发动机的内部部件
    • EP3176365A1
    • 2017-06-07
    • EP16199947.9
    • 2016-11-22
    • General Electric Company
    • DIWINSKY, David ScottROBERTS, Herbert Chidsey
    • F01D5/00B22D19/10B22F7/06B23P6/00B23P6/04G02B23/24
    • B23P6/007B22D19/10B22D25/02B22F5/009B22F5/04B22F7/062B22F2007/068B23P6/045F01D5/005F01D25/24F05D2220/32F05D2230/80F05D2260/02G02B23/24
    • In one aspect, a method (200, 400) for performing in situ repairs of internal components of a gas turbine engine (10) may generally include inserting a repair tool (102, 302) through an access port (62) of the gas turbine engine (10) such that the repair tool (102, 302) includes a tip end (112, 312) positioned within the gas turbine engine (10) and a material supply end (114, 314) positioned outside the gas turbine engine (10). The method may also include positioning the tip end (112, 312) of the repair tool (102, 302) adjacent to a defect (106) of an internal component (104) of the gas turbine engine (10), wherein the defect (106) defines a fillable volume (108) along a portion of the internal component (104). In addition, the method (200, 400) may include supplying a filler material to the tip end (112, 312) of the repair tool (102, 302) and expelling the filler material from the tip end (112, 312) of the repair tool (102, 302) such that the fillable volume (108) is at least partially filled with the filler material. The filler material may be liquid metal or solid powder material. A corresponding system for performing in situ repair of internal components of a gas turbine engine is also provided.
    • 在一个方面,用于执行原位的燃气涡轮发动机(10)的内部部件的维修的方法(200,400)可以一般地包括在燃气涡轮机的进入口(62)插入通过一个修复工具(102,302) 测试发动机(10)所做的修复工具(102,302)包括一个前端的燃气涡轮发动机外侧的位置(112,312)的燃气涡轮发动机(10)和一个材料供给端(114,314)内的定位(10 )。 因此,该方法可以包括定位修复工具(102,302)相邻的燃气涡轮发动机(10)的内部部件(104)的缺陷(106)的前端(112,312),其中所述缺陷( 106)定义沿内部部件(104)的至少一部分可填充体积(108)。 此外,该方法(200,400)可包括供应的填充材料到修理工具(102,302)的前端(112,312),并从前端排出的填充材料(112,312) 修复工具(102,302)检测没有可填充体积(108)至少部分地填充有填充材料。 填充材料可以是液体金属或固体粉末材料。 因此,用于执行在燃气涡轮发动机的内部部件的原位修复的相应系统设置。