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151. 发明申请

US20170312867A1 METHOD FOR REPAIRING A COMPONENT 审中-公开
公开(公告)号：US20170312867A1
公开(公告)日：2017-11-02
申请号：US15531845
申请日：2015-11-03
申请人： Siemens Aktiengesellschaft
发明人： Matthias Kuhlee , Britta Laux
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23K35/0222 , B23K35/0255 , B23K35/30 , B23K35/3033 , B23K35/304 , F01D5/005 , F05D2230/238 , F05D2300/131
摘要： A method for repairing a component is provided, including the following steps: introducing a recess into the component, via which recess a damaged region in the component is removed; positioning a filler body in the recess; and fixedly, i.e. non-detachably, connecting the filler body to the component, wherein the filler body is provisionally secured to the component prior to establishing the fixed connection to the component, in that a securing element is placed over the filler body and the securing element is attached to the component, wherein the securing element is removed again after the establishing of the fixed connection between the filler body and the component.

152. 发明申请

US20170175528A1 SURFACE TREATMENT OF TURBOMACHINERY 有权
公开(公告)号：US20170175528A1
公开(公告)日：2017-06-22
申请号：US14977365
申请日：2015-12-21
申请人： General Electric Company
发明人： Andrew Joseph Colletti , Bruce John Badding , Bryan Edward Williams
IPC分类号： F01D5/02 , B24B19/26 , B23P15/00
CPC分类号： F01D5/025 , B23C3/00 , B23D45/00 , B23D45/003 , B23D45/046 , B23P15/006 , B24B7/04 , B24B7/16 , B24B19/26 , B24B27/0038 , B24B27/0092 , B24B39/06 , B24B41/061 , B24B41/067 , B24C1/00 , B26D3/00 , B27C1/00 , B27C7/00 , B27C7/04 , F01D5/02 , F01D7/00 , F01D25/285 , F05D2230/10 , F05D2230/90 , F05D2240/20 , F05D2240/24 , F05D2300/13 , F05D2300/131 , F05D2300/132
摘要： Embodiments of the present disclosure provide surface treatment tools, methodologies, and/or treated turbomachine components. A surface treatment tool according to the present disclosure can include a lathe assembly having a lathe chuck for receiving a component thereon, wherein the lathe chuck rotates the component about a first axis of rotation, and wherein the component includes an exposed axial target surface; and a sander or burnishing tool coupled to the lathe assembly and including a sanding or burnishing surface thereon, coupled to a drive system, wherein the sanding or burnishing surface is oriented along a second axis substantially non-parallel with the first axis of rotation, such that the sanding or burnishing surface selectively contacts the target surface of the component to yield a polished target surface.

153. 发明申请

US20170167279A1 Abradable Compositions and Methods for CMC Shrouds 审中-公开
公开(公告)号：US20170167279A1
公开(公告)日：2017-06-15
申请号：US14963448
申请日：2015-12-09
申请人： General Electric Company
发明人： Glen Harold Kirby , Paul Stephen Manicke
IPC分类号： F01D9/04 , C04B41/50 , C04B41/89
CPC分类号： F01D9/04 , C04B35/495 , C04B35/565 , C04B35/806 , C04B41/009 , C04B41/5072 , C04B41/52 , C04B41/89 , C04B2111/00405 , C04B2235/3224 , C04B2235/3225 , C04B2235/3227 , C04B2235/3229 , C04B2235/3232 , C04B2235/3287 , C04B2235/3418 , F01D5/288 , F01D11/001 , F01D11/122 , F05D2220/32 , F05D2230/90 , F05D2300/13 , F05D2300/131 , F05D2300/15 , F05D2300/17 , F05D2300/6033 , F05D2300/611 , C04B41/5096 , C04B41/5024 , C04B2103/0021 , C04B2103/001 , C04B41/524 , C04B41/526 , C04B41/5027
摘要： Coating systems on a surface of a CMC component, such as a CMC shroud, are provided. The coating system can include an environmental barrier coating on the surface of the CMC component and an abradable coating on the environmental barrier coating and defining an external surface opposite of the environmental barrier coating. The abradable coating includes a compound having the formula: Ln2ABO8, where Ln comprises scandium, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, or mixtures thereof; A comprises Si, Ti, Ge, or a combination thereof; and B comprises Mo, W, or a combination thereof. In one embodiment, the abradable coating has a first coefficient of thermal expansion at an interface with the environmental barrier coating that changes to a second coefficient of thermal expansion at its external surface. Methods are also provided for applying an abradable coating onto a CMC component.

154. 发明申请

US20170089444A1 PROCESS FOR MAINTAINING A TURBOMACHINE ACCESSORY GEARBOX HOUSING ELEMENT 审中-公开
公开(公告)号：US20170089444A1
公开(公告)日：2017-03-30
申请号：US15315714
申请日：2015-06-05
申请人： SAFRAN TRANSMISSION SYSTEMS
发明人： Philippe MEUNIER , Laurent HENRY , Frederique HUSTACHE
IPC分类号： F16H57/032 , F01D15/12 , C23C4/134 , C23C4/08 , C23C4/18
CPC分类号： F16H57/032 , C23C4/08 , C23C4/134 , C23C4/18 , F01D15/12 , F02C7/32 , F05D2230/312 , F05D2240/14 , F05D2300/125 , F05D2300/131 , F16H2057/02039
摘要： The invention proposes a process for maintaining a casting made of magnesium alloy, said casting being a turbomachine accessory gearbox housing or a housing cover, comprising at least one cylindrical surface suitable for receiving a rolling bearing cage, the process being characterized in that it comprises a step (200) that consists in depositing molybdenum on the surface of the casting by plasma spraying.

155. 发明申请

US20160273368A1 BLADE OF A TURBOMACHINE MADE OF DIFFERENT MATERIALS AND METHOD FOR THE PRODUCTION THEREOF 审中-公开
标题翻译：不同材料的涡轮机制品的叶片及其生产方法
公开(公告)号：US20160273368A1
公开(公告)日：2016-09-22
申请号：US15067430
申请日：2016-03-11
申请人： MTU Aero Engines AG
发明人： Wilfried SMARSLY , Markus FRIED
IPC分类号： F01D5/28 , B23K20/02 , B23K20/12 , B23K13/01 , B23K15/00 , B22F5/04 , B23K26/323 , B23K20/22 , B22F3/15 , B22F3/04 , B22F3/10 , B22F3/14 , C22C27/04 , B23K26/21
CPC分类号： C22C1/045 , B22F3/04 , B22F3/10 , B22F3/1039 , B22F3/12 , B22F3/14 , B22F3/15 , B22F3/17 , B22F3/18 , B22F3/20 , B22F3/24 , B22F5/04 , B22F2003/175 , B22F2301/20 , B22F2998/10 , B23K13/01 , B23K15/0093 , B23K20/02 , B23K20/12 , B23K20/22 , B23K26/21 , B23K26/323 , B23K2101/001 , B23K2103/18 , B33Y10/00 , B33Y70/00 , B33Y80/00 , C22C1/0491 , C22C27/04 , C22C30/00 , F01D5/282 , F01D5/286 , F01D5/288 , F05D2230/22 , F05D2230/233 , F05D2230/234 , F05D2230/236 , F05D2230/239 , F05D2230/25 , F05D2230/42 , F05D2300/13 , F05D2300/131 , F05D2300/172 , F05D2300/177 , F05D2300/222 , Y02T50/672 , Y02T50/6765
摘要： The present invention relates to a blade for a turbomachine, in particular for an aircraft engine, which comprises a blade root (2) for arranging the blade (1) in the turbomachine and a main blade part (3) for interaction with a fluid flowing through the turbomachine, the blade root and the main blade part being formed from different materials and the main blade part being formed from a metal-intermetallic composite material. The metal matrix, in which intermetallic phases are incorporated for forming the metal-intermetallic composite material, is formed by a molybdenum alloy. The invention also relates to a corresponding method for producing such a blade.
摘要翻译：本发明涉及一种用于涡轮机的叶片，特别是用于飞行器发动机，其包括用于将叶片（1）布置在涡轮机中的叶根（2）和用于与流体流动相互作用的主叶片部分（3）通过涡轮机，叶片根部和主叶片部分由不同的材料形成，主叶片部分由金属 - 金属间复合材料形成。通过钼合金形成用于形成金属 - 金属间复合材料的金属间相的金属基体。本发明还涉及用于生产这种叶片的相应方法。

156. 发明申请

US20160153290A1 GAS TURBINE BLADE AND METHOD OF PROTECTING SAME 审中-公开
标题翻译：气体涡轮叶片及其保护方法
公开(公告)号：US20160153290A1
公开(公告)日：2016-06-02
申请号：US14529652
申请日：2014-10-31
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
IPC分类号： F01D5/30 , F01D5/28 , F01D5/00
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： A method of protecting a blade of a gas turbine engine by applying a nanocrystalline metal coating to a portion of the blade root is disclosed, which includes preparing at least a portion of a dovetail of the blade root for coating; and then applying a nanocrystalline metal coating to said portion.
摘要翻译：公开了一种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燃气涡轮发动机的叶片的方法，其包括制备用于涂覆的叶片根部的至少一部分燕尾榫; 然后对所述部分施加纳米晶体金属涂层。

157. 发明申请

US20160153282A1 Stress Reduction For Film Cooled Gas Turbine Engine Component 审中-公开
标题翻译：薄膜冷却燃气轮机发动机部件应力减少
公开(公告)号：US20160153282A1
公开(公告)日：2016-06-02
申请号：US14707409
申请日：2015-05-08
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Brandon W Spangler
IPC分类号： F01D5/18 , F01D11/08 , F01D25/12 , F01D9/04
CPC分类号： F01D5/186 , F01D5/284 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/55 , F05D2250/14 , F05D2260/202 , F05D2300/131 , F05D2300/20 , F05D2300/5024
摘要： A component for a gas turbine engine includes a highly conductive film cooled component with a leading edge area and a trailing edge area, the leading edge area including a multiple of film holes spaced to reduce a thermal gradient between the leading edge area and the trailing edge area to below about 200 F (93 C).
摘要翻译：用于燃气涡轮发动机的部件包括具有前缘区域和后缘区域的高导电膜冷却部件，前缘区域包括间隔开的多个膜孔，以减小前缘区域和后缘之间的热梯度面积低于约200°F（93°C）。

158. 发明申请

US20130121823A1 CHROMIUM ALLOY 有权
标题翻译：铬合金
公开(公告)号：US20130121823A1
公开(公告)日：2013-05-16
申请号：US13297560
申请日：2011-11-16
申请人： Ayan BHOWMIK , Howard J. STONE , Ian M. EDMONDS
发明人： Ayan BHOWMIK , Howard J. STONE , Ian M. EDMONDS
IPC分类号： F01D25/00 , F01D5/14 , C22C27/06
CPC分类号： C22C27/06 , F05D2200/30 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/17
摘要： A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminium, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components.
摘要翻译：一种过共晶铬合金，其由9至12at％的钽，4至15at％的硅，0至7at％的钼，0至7at％的铝，0至7at％的钛，0至5at％的铼，0至 2％银，0至2at％铪，0至2at％镧，0至2at％铈，0至2at％钇，余量为铬和附带杂质。过共晶铬合金具有良好的抗氧化性和良好的断裂韧性。铬合金可用于制造燃气涡轮发动机涡轮机叶片，涡轮叶片，涡轮密封件，燃烧室瓦片，排气喷嘴段或汽轮机部件。

159. 发明授权

US08142163B1 Turbine blade with spar and shell 有权
标题翻译：涡轮叶片与翼梁和壳
公开(公告)号：US08142163B1
公开(公告)日：2012-03-27
申请号：US12024667
申请日：2008-02-01
申请人： Daniel O Davies
发明人： Daniel O Davies
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/187 , F01D5/20 , F05D2300/131
摘要： A turbine blade for use in a gas turbine engine, the turbine blade being made from a spar and shell construction in which the spar extends from the root and forms a cavity in which cooling air is supplied to the blade. The shell is held between the tip cap and the platform in grooves. A tension rod extends from the root and through the cavity within the spar to engage with the tip cap and secure the tip cap and the shell in place. A pretension nut is secured to the tension rod on the root end and engages a surface of the root to allow for a tension to be applied to the tension rod. Ceramic rope seals are secured within the grooves between the shell ends and the groove to form a seal. An inner seal is secured within a groove of the spar and engages with a projecting member on the tip cap to form a seal. Heat shields are wrapped around the platforms to provide thermal protection to the platforms.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片，涡轮机叶片由翼梁和壳体结构制成，其中翼梁从根部延伸并形成冷却空气供应到叶片的空腔。壳体保持在顶盖和平台之间的凹槽中。张力杆从根部延伸并且穿过翼梁内的空腔，以与尖端盖接合并将尖端盖和壳固定在适当位置。预紧螺母固定在根部的拉杆上，并与根部的表面接合以允许将张力施加到张力杆上。陶瓷绳密封件固定在壳体端部和凹槽之间的凹槽内以形成密封。内密封件固定在翼梁的凹槽内，并与顶盖上的突出构件接合以形成密封。隔热罩围绕平台缠绕，为平台提供热保护。

160. 发明申请

US20110158844A1 RING-SHAPED DISK FOR GAS TURBINE 有权
标题翻译：用于气体涡轮的环形盘
公开(公告)号：US20110158844A1
公开(公告)日：2011-06-30
申请号：US12991511
申请日：2009-05-08
申请人： Jun Ohsone , Akira Mitsuhashi , Takanori Matsui , Yuji Ishiwari
发明人： Jun Ohsone , Akira Mitsuhashi , Takanori Matsui , Yuji Ishiwari
IPC分类号： C22C19/05 , C22C30/00
CPC分类号： F01D5/02 , B21H1/06 , C22C19/056 , C22F1/10 , F01D5/28 , F05C2201/0466 , F05D2260/94 , F05D2300/121 , F05D2300/131 , F05D2300/132 , F05D2300/133
摘要： This ring-shaped disk for a gas turbine includes a ring-shaped disk material consisting of a Ni-based alloy, wherein the Ni-based alloy has a composition that includes, in terms of percent by mass, Ni: 50.00 to 55.00%, Cr: 17.0 to 21.0%, Nb: 4.75 to 5.60%, Mo: 2.8 to 3.3%, Ti: 0.65 to 1.15%, Al: 0.20 to 0.80%, and C: 0.01 to 0.08%, with the balance being Fe and inevitable impurities, and has a microstructure in which δ phase particles are distributed in a matrix thereof, and wherein, in the microstructure, flattened δ phase particles of which maximum length directions are oriented at angles within a range of 60 to 120° with respect to a radial direction of the ring-shaped disk material are present in an amount of 60% or more of a total amount of the δ phase particles distributed in the matrix.
摘要翻译：该用于燃气轮机的环形盘包括由Ni基合金构成的环形盘材料，其中Ni基合金的组成按质量百分比计包含Ni：50.00至55.00％， Cr：17.0〜21.0％，Nb：4.75〜5.60％，Mo：2.8〜3.3％，Ti：0.65〜1.15％，Al：0.20〜0.80％，C：0.01〜0.08％杂质，并且具有其中δ相颗粒分布在其基体中的微结构，并且其中在微观结构中，最大长度方向相对于a的角度在60至120°的范围内的平坦化的δ相颗粒环状盘材的径向方向以分散在基体中的δ相粒子总量的60％以上的量存在。

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