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公开(公告)号：US10035185B2
公开(公告)日：2018-07-31
申请号：US14651911
申请日：2013-12-13
发明人： Dilip M. Shah , Alan D. Cetel
CPC分类号： B22D25/02 , B22D19/16 , B22D21/025 , B22D21/06 , B22D27/045 , C22C19/057 , F01D5/14 , F01D5/147 , F01D5/28 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/17 , F05D2300/606 , F05D2300/609 , Y10T403/478
摘要： A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation.
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公开(公告)号：US10005125B2
公开(公告)日：2018-06-26
申请号：US14106007
申请日：2013-12-13
发明人： Dilip M. Shah , Alan D. Cetel
CPC分类号： B22D25/02 , B22D19/16 , B22D21/025 , B22D21/06 , B22D27/045 , C22C19/057 , F01D5/14 , F01D5/147 , F01D5/28 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/17 , F05D2300/606 , F05D2300/609 , Y10T403/478
摘要： A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method includes introducing a molten alloy into a mold. A composition of the introduced alloy is varied during the introduction so as to produce a compositional variation.
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公开(公告)号：US09988913B2
公开(公告)日：2018-06-05
申请号：US14738001
申请日：2015-06-12
发明人： Brandon W. Spangler
CPC分类号： F01D5/188 , B23P15/02 , F01D5/282 , F01D5/284 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/232 , F05D2230/60 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2260/201 , F05D2260/221 , F05D2260/2212 , F05D2300/131 , F05D2300/20 , F05D2300/6033 , Y02T50/672 , Y02T50/676
摘要： A method for forming a gas turbine engine component comprises the steps of forming a block of a high temperature alloy material. An external surface of the block is machined to form an external surface of a gas turbine engine component. At least one cooling passage within the component that is open to at least one end of the component is machined. At least one insert with a heat transfer feature is formed. The insert is installed within the at least one cooling passage. A component for a gas turbine engine is also disclosed.
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公开(公告)号：US09896752B2
公开(公告)日：2018-02-20
申请号：US14447754
申请日：2014-07-31
发明人： Pavan Chintalapati , Marc Wilson , Rayad Benchiheub , Philippe Renaud , Gary Agnew , Nicolas Devulder
IPC分类号： C22C38/44 , C22C38/48 , C22C38/58 , C22C38/00 , F01D25/24 , F02C6/12 , C22C38/02 , C22C38/04 , C22C38/34 , F01D25/00 , F01N13/16
CPC分类号： C22C38/58 , C22C38/001 , C22C38/02 , C22C38/04 , C22C38/34 , C22C38/44 , C22C38/48 , F01D25/005 , F01D25/24 , F01N13/16 , F02C6/12 , F05D2220/40 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/161 , F05D2300/171
摘要： Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.5% to about 1.5% tungsten, about 0.2% to about 0.8% molybdenum, about 0.2% to about 0.8% niobium, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% nitrogen, and a balance of iron. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 1020° C.
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5.发明申请公开(公告)号：US20170241271A1
公开(公告)日：2017-08-24
申请号：US15431925
申请日：2017-02-14
申请人： MTU Aero Engines AG
IPC分类号： F01D5/28 , C22C30/00 , C23C14/16 , F01D9/02 , C23C14/58 , C23C16/42 , C23C16/38 , C23C16/56 , C22C27/04 , C23C14/34
CPC分类号： F01D5/28 , C22C27/04 , C22C30/00 , C23C10/04 , C23C10/28 , C23C14/165 , C23C14/34 , C23C14/5806 , C23C14/5853 , C23C16/38 , C23C16/42 , C23C16/56 , C23C28/321 , C23C28/322 , C23C28/34 , C23C28/345 , C23C28/36 , F01D9/02 , F05D2220/323 , F05D2230/313 , F05D2230/314 , F05D2230/40 , F05D2300/131 , Y02T50/6765
摘要： Disclosed is a method for improving the high-temperature stability of a component, in particular a blade of a turbomachine, formed at least partially from a molybdenum alloy that, besides molybdenum, silicon, boron and titanium, comprises iron and/or yttrium. The method comprises depositing a diffusion barrier layer formed from technically pure molybdenum or tungsten or being an alloy based on molybdenum and/or tungsten at least on an outer surface, which comprises the molybdenum alloy, of the component, and depositing silicon on the diffusion barrier layer to form molybdenum silicides and/or tungsten silicides.
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公开(公告)号：US20170211392A1
公开(公告)日：2017-07-27
申请号：US15005327
申请日：2016-01-25
发明人： Paul M. Lutjen , Gary L. Grogg
CPC分类号： F01D5/18 , B22C7/02 , B22C9/04 , B22C9/10 , B22C9/103 , B22C9/108 , B22F3/1055 , B22F5/009 , B22F5/04 , B22F2005/103 , B33Y80/00 , F01D5/187 , F01D9/065 , F05D2230/21 , F05D2230/22 , F05D2230/31 , F05D2240/11 , F05D2240/81 , F05D2250/20 , F05D2250/231 , F05D2250/24 , F05D2250/241 , F05D2250/27 , F05D2250/293 , F05D2250/313 , F05D2250/75 , F05D2260/20 , F05D2260/204 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F05D2300/131
摘要： According to one embodiment of this disclosure a core includes a first end and a second end spaced generally opposite from the first end. The core further includes a stacking axis defined between the first end and second end and a first toroidal structure located between the first end and the second end. The first toroidal structure includes a first passage extending through the first toroidal structure in a first direction that is perpendicular to and passes through the stacking axis. The core also includes a second toroidal structure located between the first toroidal structure and the second end. The second toroidal structure includes a second passage extending through the second toroidal structure in a second direction. The first direction and the second direction are oriented along the stacking axis at a non-zero degree angle with respect to each other.
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公开(公告)号：US20170152751A1
公开(公告)日：2017-06-01
申请号：US14955167
申请日：2015-12-01
发明人： Brandon W. Spangler , Atul Kohli
CPC分类号： F01D5/187 , F01D5/147 , F01D5/284 , F01D9/02 , F01D11/08 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/35 , F05D2250/14 , F05D2250/185 , F05D2250/71 , F05D2260/22141 , F05D2300/131 , F05D2300/6033 , Y02T50/672 , Y02T50/676
摘要： A gas path component for a gas turbine engine includes an element configured to be exposed to a gas path. The element includes a plurality of internal cooling passages. At least one of the internal cooling passages includes a cross section having a plurality of asymmetrical filleted corners.
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公开(公告)号：US09429029B2
公开(公告)日：2016-08-30
申请号：US13189043
申请日：2011-07-22
申请人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
发明人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
CPC分类号： F01D5/3092 , F01D5/005 , F01D5/28 , F05B2230/90 , F05D2220/32 , F05D2230/80 , F05D2230/90 , F05D2260/94 , F05D2300/11 , F05D2300/121 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/134 , F05D2300/143 , F05D2300/16 , F05D2300/1614 , F05D2300/1616 , F05D2300/609
摘要： An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.
摘要翻译： 燃气涡轮发动机的翼型叶片包括配置成与配合的转子毂配合连接的根部以及远离根部延伸的翼型件。 根由第一金属组成，并且在其至少一部分上具有由第二金属组成的纳米晶体金属涂层。 还公开了通过将纳米晶体金属涂层施加到叶片根部的一部分来保护这种叶片的方法。
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公开(公告)号：US20140322479A1
公开(公告)日：2014-10-30
申请号：US14343635
申请日：2012-09-07
申请人： Cedric Plaindoux , Simon Schers , Benjamin Moura
发明人： Cedric Plaindoux , Simon Schers , Benjamin Moura
CPC分类号： F02C7/25 , B64C7/02 , F05D2300/131 , F05D2300/30 , F05D2300/5024 , F05D2300/522 , F05D2300/603 , Y10T428/24008 , Y10T428/266
摘要： A flame resistant shield includes two opposing walls between which are positioned at least: a first insulating layer, the first layer being capable of distributing heat in the plane formed by the first layer and being insulating across its thickness, a second insulating layer, one of the opposing walls which covers the first layer being produced from a refractory antioxidant material or having at least the surface intended to be exposed to flames covered with a material preventing this surface from being oxidised, the other wall being a support.
摘要翻译： 阻燃屏蔽包括两个相对的壁，它们之间至少位于第一绝缘层上，第一层能够在由第一层形成的平面中分布热量并在其厚度上绝缘;第二绝缘层， 覆盖第一层的相对壁由难熔抗氧化材料制成或至少具有暴露于火焰的表面覆盖的材料，防止该表面被氧化，另一壁是支撑体。
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公开(公告)号：US08523519B2
公开(公告)日：2013-09-03
申请号：US12565813
申请日：2009-09-24
IPC分类号： F03D11/00 , F01D25/00 , F03B11/00 , F04D29/04 , C22C38/22 , C22C38/08 , C22C38/00 , C22C38/12 , C22C38/44
CPC分类号： C22C38/44 , B21K1/06 , C21D1/20 , C21D1/28 , C21D6/004 , C21D7/13 , C21D8/005 , C21D9/28 , C21D2211/002 , C22C38/04 , C22C38/46 , C22C38/50 , C22C38/54 , F01D5/02 , F05C2201/0466 , F05D2230/25 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/161
摘要： An alloy suitable for use in a rotor, such as one or more regions of a steam turbine rotor, as well as a forged rotor formed with the alloy. The alloy consists of, by weight, 0.20 to 0.30% carbon, 0.80 to 1.5% chromium, 0.80 to 1.5% molybdenum, 0.50 to 0.90% vanadium, 0.30 to 0.80% nickel, 0.05 to 0.15% titanium, 0.20 to 1.0% manganese, and 0.005 to 0.012% boron, the balance iron, optionally low levels of other alloying constituents, and incidental impurities.
摘要翻译： 适合用于转子的合金，例如蒸汽轮机转子的一个或多个区域，以及由合金形成的锻造转子。 该合金按重量计含有0.20-0.30％的碳，0.80到1.5％的铬，0.80到1.5％的钼，0.50到0.90％的钒，0.30到0.80％的镍，0.05到0.15％的钛，0.20到1.0％的锰， 和0.005至0.012％的硼，余量为铁，任选低含量的其它合金成分和附带杂质。
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