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1. 发明申请

US20180209276A1 TURBO-MACHINE IMPELLER MANUFACTURING 审中-公开
公开(公告)号：US20180209276A1
公开(公告)日：2018-07-26
申请号：US15890693
申请日：2018-02-07
申请人： Nuovo Pignone S.r.l.
发明人： Pierluigi Tozzi , Iacopo GIOVANNETTI , Andrea MASSINI
IPC分类号： F01D5/18 , F04D29/28 , B22F3/105 , B22F5/00 , B22F5/04 , B23K26/342 , B23K15/00 , F04D29/02 , F01D5/14 , B22F5/10 , B23K101/00
CPC分类号： F01D5/18 , B22F3/1055 , B22F5/009 , B22F5/04 , B22F5/10 , B23K15/0006 , B23K15/0086 , B23K26/342 , B23K2101/001 , F01D5/147 , F04D29/023 , F04D29/284 , F05D2230/22 , F05D2230/31 , F05D2300/171 , F05D2300/174 , F05D2300/175 , F05D2300/608 , Y02P10/295
摘要： A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.

2. 发明授权

US09969035B2 Method for producing a turbine engine part, and resulting mould and intermediate blank 有权
公开(公告)号：US09969035B2
公开(公告)日：2018-05-15
申请号：US15106124
申请日：2014-12-09
申请人： Snecma
发明人： Patrick Emilien Paul Emile Huchin , Karine Deschandol , Sébastien Digard Brou De Cuissart , Serge Fargeas , Marc Soisson , Anthony Texier , Valéry Piaton
IPC分类号： B22D25/02 , B22C9/22 , B23P15/02 , B22D13/06 , B22D27/15 , F01D5/28
CPC分类号： B23P15/02 , B22C9/22 , B22D13/06 , B22D13/066 , B22D25/02 , B22D27/15 , F01D5/28 , F05D2220/323 , F05D2230/10 , F05D2230/21 , F05D2240/30 , F05D2300/173 , F05D2300/174 , F05D2300/608
摘要： The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.

3. 发明授权

US09828915B2 Hot gas path component having near wall cooling features 有权
公开(公告)号：US09828915B2
公开(公告)日：2017-11-28
申请号：US14739849
申请日：2015-06-15
申请人： General Electric Company
发明人： Carlos Miguel Miranda , Srikanth Chandrudu Kottilingam , Benjamin Paul Lacy
IPC分类号： F01D5/18 , F02C7/18 , B23P15/04
CPC分类号： F02C7/18 , B23P15/04 , F01D5/18 , F01D5/182 , F01D5/184 , F01D5/186 , F01D5/187 , F01D5/188 , F05D2230/236 , F05D2230/237 , F05D2260/204 , F05D2300/608 , F05D2300/701 , Y02T50/672 , Y02T50/676
摘要： A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.

4. 发明授权

US09770758B2 Method for forming a directionally solidified replacement body for a component using additive manufacturing 有权
公开(公告)号：US09770758B2
公开(公告)日：2017-09-26
申请号：US15219921
申请日：2016-07-26
申请人： United Technologies Corporation
发明人： JinQuan Xu
IPC分类号： B22D23/06 , B22D27/04 , B33Y10/00 , B33Y40/00 , B33Y80/00 , B22C9/10 , B22C9/22 , B22D29/00 , B22D25/02 , B22F3/105 , B22F3/24 , B22F5/04 , B23K15/00 , B23K26/342 , B23K26/70 , B23K37/00 , F01D5/00 , F01D5/12 , F01D9/04 , F02C7/22 , F23R3/00 , B23K101/00
CPC分类号： B22D27/045 , B22C9/02 , B22C9/04 , B22C9/10 , B22C9/108 , B22C9/12 , B22C9/22 , B22D23/06 , B22D25/02 , B22D29/001 , B22F3/1055 , B22F3/24 , B22F5/007 , B22F5/009 , B22F5/04 , B22F2003/248 , B22F2998/10 , B23K1/0018 , B23K9/04 , B23K9/167 , B23K15/0046 , B23K15/0086 , B23K20/00 , B23K26/34 , B23K26/342 , B23K26/70 , B23K31/02 , B23K37/00 , B23K2101/001 , B23P6/005 , B23P6/007 , B23P6/045 , B33Y10/00 , B33Y40/00 , B33Y80/00 , C30B11/00 , C30B11/003 , C30B21/02 , C30B29/52 , F01D5/005 , F01D5/12 , F01D5/18 , F01D5/186 , F01D5/187 , F01D9/04 , F02C7/222 , F05D2220/32 , F05D2230/21 , F05D2230/233 , F05D2230/234 , F05D2230/235 , F05D2230/238 , F05D2230/30 , F05D2230/80 , F05D2240/122 , F05D2240/304 , F05D2260/202 , F05D2260/204 , F05D2300/175 , F05D2300/20 , F05D2300/606 , F05D2300/608 , F23R3/002 , Y02P10/292 , Y02P10/295
摘要： A method of manufacturing a replacement body for a component is provided. The method includes the steps of: a) additively manufacturing a crucible for casting of the replacement body; b) solidifying a metal material within the crucible to form a directionally solidified microstructure within the replacement body; and c) removing the crucible to reveal the directionally solidified replacement body.

5. 发明申请

US20150017013A1 TURBO-MACHINE IMPELLER MANUFACTURING 有权
标题翻译：涡轮机叶轮制造
公开(公告)号：US20150017013A1
公开(公告)日：2015-01-15
申请号：US14380160
申请日：2013-02-20
申请人： Nuovo Pignone S.r.l.
发明人： Pierluigi Tozzi , Iacopo Giovannetti , Andrea Massini
IPC分类号： B22F5/04 , B23K26/34 , B23K15/00 , F01D5/14 , B22F3/105
CPC分类号： F01D5/18 , B22F3/1055 , B22F5/009 , B22F5/04 , B22F5/10 , B23K15/0006 , B23K15/0086 , B23K26/342 , B23K2101/001 , F01D5/147 , F04D29/023 , F04D29/284 , F05D2230/22 , F05D2230/31 , F05D2300/171 , F05D2300/174 , F05D2300/175 , F05D2300/608 , Y02P10/295
摘要： A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.
摘要翻译：一种制造涡轮机叶轮的方法，其包括在添加剂制造过程中使用粉末材料的轮毂和多个叶片。该方法包括：通过高能源向粉末材料施加能量，并固化粉末材料。照射毂的至少一个庞大部分，使得粉末材料以包围晶格结构的外部固体皮肤结构围绕的格子结构固化。

6. 发明申请

US20130255277A1 GAS TURBINE ENGINE NOSE CONE 审中-公开
标题翻译：燃气涡轮发动机油
公开(公告)号：US20130255277A1
公开(公告)日：2013-10-03
申请号：US13435738
申请日：2012-03-30
申请人： Enzo Macchia , Andreas Eleftheriou , Thomas Peter McDonough , George Guglielmin , Joe Lanzino , Barry Barnett
发明人： Enzo Macchia , Andreas Eleftheriou , Thomas Peter McDonough , George Guglielmin , Joe Lanzino , Barry Barnett
IPC分类号： F02C7/00 , F02C3/04 , B05D1/18 , F01D25/00
CPC分类号： F02C7/04 , F05D2250/232 , F05D2300/605 , F05D2300/608 , F05D2300/612
摘要： A nose cone for a turbofan gas turbine engine includes a central tip, an outer perimeter and a substantially conical outer wall extending therebetween which encloses a cavity therewithin. The outer wall includes an inner substrate layer facing the cavity and an outer layer which overlies and at least partially encloses the inner substrate layer. The outer layer is composed entirely of a nanocrystalline metal forming an outer surface of the nose cone.
摘要翻译：用于涡轮风扇燃气涡轮发动机的鼻锥包括中心尖端，外周边和在其间延伸的基本上圆锥形的外壁，其在其中封闭空腔。外壁包括面向空腔的内部基底层和覆盖并至少部分地包围内部基底层的外层。外层完全由形成鼻锥外表面的纳米晶体金属构成。

7. 发明申请

US20100322760A1 Interlocked CMC Airfoil 有权
标题翻译：联锁CMC翼型
公开(公告)号：US20100322760A1
公开(公告)日：2010-12-23
申请号：US12486180
申请日：2009-06-17
申请人： Jay A. Morrison , Anthony L. Schiavo
发明人： Jay A. Morrison , Anthony L. Schiavo
IPC分类号： F01D9/04 , F04D29/54
CPC分类号： F04D29/023 , F01D5/147 , F01D5/282 , F01D5/284 , F04D29/542 , F05D2230/23 , F05D2300/6033 , F05D2300/608 , Y10T29/49339
摘要： A ceramic matrix composite (CMC) airfoil assembled from a pressure side wall (42) and a suction side wall (52) joined by interlocking joints (18, 19) at the leading and trailing edges (22, 24) of the airfoil to produce a tapered thin trailing edge. The trailing edge (24) is thinner than a combined thicknesses of the airfoil walls (42, 52). One or both of the interlocking joints (18, 19) may be formed to allow only a single direction of assembly, as exemplified by a dovetail joint. Each joint (18, 19) includes keys (44F, 54F, 56F, 46F) on one side and respective keyways (44K, 54K, 56K, 46K) on the other side. Each keyway may have a ramp (45) that eliminates indents in the airfoil outer surface that would otherwise result from the joint.
摘要翻译：由压力侧壁（42）和吸力侧壁（52）组装的陶瓷基体复合材料（CMC）翼型件，其通过翼型件的前缘和后缘（22,24）处的互锁接头（18,19）连接，以产生锥形细的后缘。后缘（24）比翼型件壁（42,52）的组合厚度薄。互锁接头（18,19）中的一个或两个可以形成为仅允许组装的单个方向，如燕尾接头所例示。每个接头（18,19）包括一侧的键（44F，54F，56F，46F）和另一侧的键槽（44K，54K，56K，46K）。每个键槽可以具有斜面（45），其消除了否则从接头产生的翼型件外表面中的凹痕。

8. 发明授权

US4988266A Gas turbine and shroud for gas turbine 失效
标题翻译：燃气轮机和燃气轮机罩
公开(公告)号：US4988266A
公开(公告)日：1991-01-29
申请号：US321880
申请日：1989-03-10
申请人： Shigeyoshi Nakamura , Yutaka Fukui , Tetsuo Kashimura
发明人： Shigeyoshi Nakamura , Yutaka Fukui , Tetsuo Kashimura
IPC分类号： C22C19/05 , C22C19/07 , C22C30/00 , C22C38/00 , C22C38/22 , C22C38/44 , F01D5/06 , F01D5/28 , F01D11/08 , F01D11/12
CPC分类号： F01D11/122 , C22C19/055 , C22C19/07 , C22C30/00 , C22C38/22 , C22C38/44 , F01D11/08 , F01D5/28 , F05D2240/11 , F05D2300/608 , F05D2300/609
摘要： A gas turbine includes a turbine stubshaft, a plurality of turbine disks coupled to the shaft by turbine stacking bolts with spacers interposed therebetween, turbing moving blades planted in each of the disks, a shroud provided with a sliding surface in a spaced-apart relation to the tips of the moving blades, a distant piece connected to the disks by the bolts, a plurality of compressor disks coupled to the distant piece by compressor stacking bolts, compressor blades planted in each of the compressor disks, and a compressor stubshaft formed integrally with the compressor disk located at the first stage. At least a sliding portion of the shroud is made of a heat-resistant cast alloy having in turn a chilled layer and columnar grains in a direction oriented from the sliding surface thereof toward the interior thereof. A method of producing a segment-shaped shroud for a gas turbine by casting, comprises the steps of preparing a mold having a coated layer formed on at least a surface thereof which is to be in contact with a casting, the coated layer containing refractory aggregate powder at a main constituent, and refractory agent powder for accelerating generation of crystal nuclei, pouring the molten alloy into the mold, and forced-cooling the outer surface of the mold.

9. 发明公开

US20240293964A1 MOLD AND BLADE MEMBER 审中-公开
公开(公告)号：US20240293964A1
公开(公告)日：2024-09-05
申请号：US18573041
申请日：2021-06-22
申请人： NIKON CORPORTION
发明人： Go ICHINOSE
IPC分类号： B29C45/26 , B29L31/08 , F01D5/14
CPC分类号： B29C45/263 , F01D5/141 , B29L2031/082 , F05D2250/711 , F05D2300/608
摘要： A mold used to mold a molded product includes a mold surface that contacts a material, a plurality of convex structures are formed on the mold surface, at least one of a corner part of a first convex structure among the plurality of convex structures and a boundary part between adjacent first and second convex structures among the plurality of convex structures includes a curved surface, in a case where a radius of curvature of the curved surface included in at least one of the corner part and the boundary part is R, a pitch of the convex structures is P, and a height of the convex structures is H, a condition “1 micrometer

10. 发明授权

US11878949B1 Multi-component high stability environmental barrier coatings 有权
公开(公告)号：US11878949B1
公开(公告)日：2024-01-23
申请号：US15882435
申请日：2018-01-29
申请人： United States of Americas as represented by the Administrator of NASA
发明人： Dongming Zhu , Bryan J. Harder , Janet B. Hurst
IPC分类号： C04B41/52 , C04B41/87 , C04B41/89 , F01D25/00
CPC分类号： C04B41/87 , C04B41/89 , F01D25/005 , F05D2220/32 , F05D2300/608 , F05D2300/6033 , F05D2300/611
摘要： An advanced high temperature environmental barrier coating system is disclosed for protecting Si-based ceramics and SiC/SiC ceramic matrix composites (CMCs). This innovation provides a series of environmental barrier coating composition systems to achieve exceptional temperature capability, erosion and calcium-magnesium-aluminosilicate (CMAS) resistance and durability of the environmental barrier coated ceramic turbine engine hot-section components, in harsh turbine engine environments. The environmental barrier coating systems have been demonstrated for 1650° C. temperature capability and help prime-reliant designs.

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