专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2015017069A3 MECHANICAL JOINING USING ADDITIVE MANUFACTURING PROCESS 审中-公开
公开(公告)号：WO2015017069A3
公开(公告)日：2015-02-05
申请号：PCT/US2014/044841
申请日：2014-06-30
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： JAMES, Allister William
IPC分类号： B22F3/105 , B29C67/00 , F01D5/30 , F16L13/007 , B22F5/00 , B22F7/06
摘要： A method of manufacturing an assembly (10), including: positioning a first component (12) and a second component (14) in a desired positional relationship with each other; and building-up a locking component (16) by depositing layer after layer of material onto a surface (24, 26) of the assembly until a completed locking component is formed in-situ that holds the first component and the second component in the desired positional relationship.

2. 发明申请

WO2019046022A1 HYBRID CMC COMPONENT HAVING INTEGRAL AND MODULAR SHROUDS 审中-公开
公开(公告)号：WO2019046022A1
公开(公告)日：2019-03-07
申请号：PCT/US2018/047019
申请日：2018-08-20
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MARSH, Jan H. , JAMES, Allister William
IPC分类号： F01D5/04 , F01D5/28 , F01D5/30
CPC分类号： F01D5/282 , F01D5/04 , F01D5/041 , F01D5/284 , F01D5/3084 , F05D2300/603 , F05D2300/6033
摘要： A hybrid CMC component (25) for a gas turbine engine (100) is located in the turbine section (50) of the gas turbine engine (100). The hybrid CMC component takes advantage of features found within modular structures and within integral structures. The hybrid CMC component (25) is able to reduce leakage paths while also accommodating thermal expansion.

3. 发明申请

WO2016039715A1 HYBRID DIE CAST SYSTEM FOR FORMING A COMPONENT USABLE IN A GAS TURBINE ENGINE 审中-公开
标题翻译：用于形成在气体涡轮发动机中可用的组件的混合式灭弧室系统
公开(公告)号：WO2016039715A1
公开(公告)日：2016-03-17
申请号：PCT/US2014/054463
申请日：2014-09-08
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： BEECK, Alexander Ralph , JAMES, Allister William , MERRILL, Gary B.
IPC分类号： B22D17/22
CPC分类号： B22D17/229 , B22D17/22 , B22D17/2218 , B22D17/32
摘要： A hybrid die cast system (10) having an inner liner insert (12) that enables the configuration of a component (18) produced by the system (10) to be easily changed by changing the inner liner insert (12) without having to rework the die housing (16) is disclosed. Because the inner liner insert (12) only need be removed and replaced to change the configuration of an outer surface (18) of a component (18) produced by the system (10), the cost savings is significant in contrast with conventional systems in which the die would have to be reworked. The system (10) may also include a cooling system (20) for controlling the casting process by controlling the rate of solidification and the rate of cooling of the casting. Local heating and cooling may be used to control the microstructure, enhance mold fill and reduce casting defects such as porosity.
摘要翻译：具有内衬垫片（12）的混合压铸系统（10），其能够通过改变内衬垫片（12）而容易地改变由系统（10）制成的部件（18）的构型，而不必返工公开了模具外壳（16）。因为内衬垫（12）仅需要被移除和更换以改变由系统（10）制造的部件（18）的外表面（18）的构造，所以与常规系统相比，成本节约是显着的这个模具必须要重新加工。系统（10）还可以包括用于通过控制铸件的凝固速率和冷却速度来控制铸造过程的冷却系统（20）。局部加热和冷却可用于控制微观结构，增强模具填充并减少诸如孔隙率的铸造缺陷。

4. 发明申请

WO2020068109A1 MODULAR COOLING ARRANGEMENT FOR COOLING AIRFOIL COMPONENTS IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2020068109A1
公开(公告)日：2020-04-02
申请号：PCT/US2018/053393
申请日：2018-09-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , FISCHLE, Moritz , MARSH, Jan H. , FU, Wentao , JAMES, Allister William , MILLER, Andrew , MITCHELL, David J.
IPC分类号： F01D5/14 , F01D5/28 , F01D9/04
摘要： A modular cooling arrangement for cooling an airfoil component (10) in a combustion turbine engine is provided. A body (16) of the airfoil component, and a cooling manifold (18) or a flow sleeve (50, 60) may be disposed in a cavity in the body of the airfoil component. By way of example, the body of the airfoil component may be a ceramic matrix composite body, a MAX phase ternary ceramic body, or a metallic body. Disclosed embodiments are effective to reliably and cost-effectively reduce a level of internal pressurization in the component while providing appropriate cooling to portions of the component subject to a hot flow of gases and accommodating thermal growth differences that may develop between components of the modular cooling arrangement and anchoring structures to which the modular cooling arrangement may be affixed.

5. 发明申请

WO2017123207A1 THERMALLY CONDUCTIVE BUMPER ELEMENTS FOR A HYBRID AIRFOIL 审中-公开
标题翻译：混合式机翼的导热保温元件
公开(公告)号：WO2017123207A1
公开(公告)日：2017-07-20
申请号：PCT/US2016/012999
申请日：2016-01-12
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , JAMES, Allister William
IPC分类号： F01D5/18 , F01D5/26
CPC分类号： F01D5/188 , F01D5/189 , F01D5/26
摘要： An airfoil (30) for a turbine (10) wherein the airfoil (30) includes a core support structure (34) having a core outer surface (44) and a high heat resistant outer shell (32) having leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The outer shell (32) also includes a shell inner surface (46), wherein a portion of the core support structure (34) is located within the outer shell (32) and wherein the core outer surface (44) and shell inner surface (46) are separated by a surface gap (48). Further, the airfoil (30) includes at least one bumper element (56) located within the surface gap (48), wherein the at least one bumper element (56) provides a thermally conductive path for conducting heat from the outer shell (32) to the core support structure (34) and wherein the at least one bumper element (56) is flexible to absorb relative movement between the outer shell (32) and the core support structure (34) to reduce stress levels in the airfoil (30).
摘要翻译：一种用于涡轮机（10）的翼型件（30），其中翼型件（30）包括具有型芯外表面（44）和高耐热外壳（32）的型芯支撑结构（34））具有前缘（36）和后缘（38）以及高（40）和低（42）压力表面。外壳（32）还包括壳内表面（46），其中芯支撑结构（34）的一部分位于外壳（32）内，并且其中芯外表面（44）和壳内表面 46）被表面间隙（48）隔开。此外，翼型件（30）包括位于表面间隙（48）内的至少一个缓冲器元件（56），其中至少一个缓冲器元件（56）提供用于从外壳（32）传导热量的导热路径，（34），并且其中所述至少一个缓冲器元件（56）是柔性的以吸收所述外壳（32）和所述芯支撑结构（34）之间的相对运动，以减小所述翼型件（30）中的应力水平。

6. 发明申请

WO2014130441A1 PRE-WELD HEAT TREATMENT FOR A NICKEL BASED SUPERALLOY 审中-公开
标题翻译：用于镍基超级合金的预焊热处理
公开(公告)号：WO2014130441A1
公开(公告)日：2014-08-28
申请号：PCT/US2014/016868
申请日：2014-02-18
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： ANGAL, Ravishankar P. , JAMES, Allister William
IPC分类号： C21D1/84 , B23K1/00 , B23K1/20 , C22C19/00 , C22C19/05 , C22F1/10
CPC分类号： C22F1/10 , C21D1/84 , C21D9/50 , C21D9/505 , C22C19/055
摘要： A pre-weld heat treatment of the nickel based superalloy including heating a nickel based superalloy (e.g., IN939) casting to 2120°F at a rate of 2°F per minute, and then soaking the casing for one hour at 2120°F. The casting is then cooled in stages including slowly cooling the casting at a rate of 1°F per minute to about 1900°F and holding at that temperature for about 10 minutes. Then the casting is further slowly cooled at a rate of 1°F per minute to about 1800°F and holding at that temperature for about 10 minutes, and further slowly cooled to a temperature range of 1650°F to 1450°F, and then fast cooled to room temperature. The pre-weld heat treatment may optionally include a step of heating the casting to about 1850°F at a rate of 50°F per minute before slowly heating to 2120°F
摘要翻译：镍基超级合金的预焊接热处理包括以每分钟2°F的速度将镍基超级合金（例如IN939）铸造加热到2120°F，然后在2120°F下将套管浸泡1小时。然后将铸件分阶段冷却，包括以1°F /分钟的速度将铸件缓慢冷却至约1900°F，并在该温度下保持约10分钟。然后将铸件以1°F /分钟的速度进一步缓慢冷却至约1800°F，并在该温度下保持约10分钟，并进一步缓慢冷却至1650°F至1450°F的温度范围，然后快速冷却至室温。预焊接热处理可以任选地包括以50°F /分钟的速度将铸件加热到约1850°F的步骤，然后缓慢加热至2120°F

7. 发明申请

WO2017105380A1 TURBINE AIRFOIL COMPRISING A CORE SUPPORT STRUCTURE AND A HEAT RESISTANT OUTER SHELL 审中-公开
标题翻译：包含核心支撑结构和耐热外壳的涡轮机叶片
公开(公告)号：WO2017105380A1
公开(公告)日：2017-06-22
申请号：PCT/US2015/065424
申请日：2015-12-14
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D , JAMES, Allister William , SHINDE, Sachin R. , MORRISON, Jay A.
IPC分类号： F01D5/14 , F01D5/18 , F01D5/28 , F01D9/06
CPC分类号： F01D5/147 , F01D5/18 , F01D5/282 , F01D9/065 , F05D2230/51 , F05D2230/60 , F05D2260/37 , F05D2300/175 , F05D2300/6033
摘要： An airfoil (30) for a turbine (10), wherein the airfoil (30) includes leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The airfoil (30) includes a core support structure (34) having first (46) and second (54) support sections that include first (50) and second (56) air inlets, respectively. The airfoil (30) also includes at least one first air channel (62) that extends from the first air inlet (50) and through the first support section (46) to an associated air exit hole (60). In addition, the airfoil (30) includes at least one truss (58) connected between the first (46) and second (54) support sections and at least one second air channel (66) that extends from the second air inlet (56) and through the second support section (54), truss (58) and first support section (46) to an associated air exit hole (60). Further, the airfoil (30) includes a high heat resistant outer shell (32), wherein a portion (48) of the core support structure (30) is located within the outer shell (32). The outer shell may include first and second high heat resistant members.
摘要翻译：一种用于涡轮机（10）的翼型件（30），其中所述翼型件（30）包括前缘（36）和后缘（38）边缘以及高（40）和低（42）压力表面。翼型件（30）包括具有分别包括第一（50）和第二（56）进气口的第一支架部分（46）和第二支架部分（54）的芯支撑结构（34）。翼型件30还包括至少一个第一空气通道62，该第一空气通道62从第一空气入口50并通过第一支撑部分46延伸到相关的空气出口孔60。此外，翼型件30包括连接在第一支撑部分46和第二支撑部分54之间的至少一个桁架58以及从第二空气入口56延伸的至少一个第二空气通道66，并通过第二支撑部分（54），桁架（58）和第一支撑部分（46）到达相关的空气出口孔（60）。此外，翼型件（30）包括高耐热外壳（32），其中芯支撑结构（30）的一部分（48）位于外壳（32）内。外壳可以包括第一和第二高耐热构件。

8. 发明申请

WO2017082868A1 LAMINATED AIRFOIL FOR A GAS TURBINE 审中-公开
标题翻译：燃气轮机的叠层机翼
公开(公告)号：WO2017082868A1
公开(公告)日：2017-05-18
申请号：PCT/US2015/059842
申请日：2015-11-10
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： JAMES, Allister William
IPC分类号： F01D5/18 , B23K20/08 , B21K25/00
CPC分类号： F01D5/187 , B23K20/08 , F01D5/188 , F05D2230/232 , F05D2230/31
摘要： An airfoil (30) for a gas turbine (10) wherein the airfoil (30) includes an outer wall (32) having leading (34) and trailing (36) edges and convex (40) and concave (38) surfaces and wherein the outer wall (32) forms an internal cavity (52). The airfoil (30) includes at least one inner layer (42) located within the cavity (52), wherein the inner layer (42) has a shape that corresponds to the shape of the outer wall (32). The airfoil (30) also includes a leading edge insert (58) located adjacent the leading edge (34) of the outer wall (32). Further, the airfoil (30) includes a trailing edge insert (60) located adjacent the trailing edge (36) of the outer wall (32) wherein the at least one inner layer (42) is bonded to an inside surface (56) of the outer wall (32) to encapsulate the leading (58) and trailing (60) edge inserts.
摘要翻译：一种用于燃气轮机（10）的翼型件（30），其中翼型件（30）包括具有前缘（34）和后缘（36）以及凸缘（40）的外壁（32）和凹形（38）表面，并且其中外壁（32）形成内腔（52）。翼型件（30）包括位于空腔（52）内的至少一个内层（42），其中内层（42）具有与外壁（32）的形状相对应的形状。翼型件（30）还包括位于外壁（32）的前缘（34）附近的前缘插入件（58）。此外，翼型件（30）包括位于外壁（32）的后缘（36）附近的后缘插入件（60），其中至少一个内层（42）粘结到外壁（32）的内表面外壁（32）封装前缘（58）和后缘（60）的边缘插件。

9. 发明申请

WO2015023506A1 REPAIR SYSTEM FOR TURBOMACHINERY COMPONENTS USING ADDITIVE MANUFACTURING TECHNOLOGY 审中-公开
标题翻译：使用添加剂制造技术的涡轮机组件修理系统
公开(公告)号：WO2015023506A1
公开(公告)日：2015-02-19
申请号：PCT/US2014/050094
申请日：2014-08-07
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： JAMES, Allister William , MÜNZER, Jan , OTT, Michael
IPC分类号： B23P6/00 , F01D5/00
CPC分类号： B23P6/007 , B23K2201/001 , B23P6/00 , B23P6/005 , F01D5/005 , F05D2220/31 , F05D2240/80 , Y10T29/49734 , Y10T29/53013
摘要： A system and method for repairing a machinery component (200) is provided. The system comprises a detector (104) for detecting one or more defects (208, 210) on the component (200). The system also comprises a cutting tool (106) for removing at least one portion (304, 308) from the component (200). The at least one portion (304, 308) includes at least one from one or more defects (208, 210) detected by the detector (104). At least one slot (302, 306) is formed on the surface of the component by removing the at least one portion (304, 308) from the component (200). The system further comprises a scanner (108) connected to a processing unit (102). The scanner (108) scans the at least one slot (302, 306) and the processing unit (102) generates one or more data points corresponding to the at least one slot (302, 306). The system also has a repair coupon producing unit (110) connected to the processing unit (102). The repair coupon producing unit (110) manufactures at least one repair coupon (502, 506) based on the one or more data points received from the processing unit (102, 410).
摘要翻译：提供了一种用于修理机械部件（200）的系统和方法。该系统包括用于检测组件（200）上的一个或多个缺陷（208,210）的检测器（104）。该系统还包括用于从组件（200）移除至少一个部分（304,308）的切割工具（106）。至少一个部分（304,308）包括由检测器（104）检测到的至少一个来自一个或多个缺陷（208,210）。通过从组件（200）移除至少一个部分（304,308），在组件的表面上形成至少一个槽（302,306）。该系统还包括连接到处理单元（102）的扫描器（108）。扫描器（108）扫描至少一个时隙（302,306），并且处理单元（102）产生对应于至少一个时隙（302,306）的一个或多个数据点。该系统还具有连接到处理单元（102）的修理券生产单元（110）。修理券生产单元（110）基于从处理单元（102,410）接收的一个或多个数据点制造至少一个维修券（502,506）。

10. 发明申请

WO2017189208A1 GAS TURBINE BLADE WITH CORRUGATED TIP WALL 审中-公开
标题翻译：瓦楞原纸瓦斯涡轮叶片
公开(公告)号：WO2017189208A1
公开(公告)日：2017-11-02
申请号：PCT/US2017/026484
申请日：2017-04-07
申请人： SIEMENS ENERGY, INC.
发明人： CAMPBELL, Christian Xavier , KULKARNI, Anand A. , ESHAK, Daniel M. , JAMES, Allister William , BEHLING, Phillip , KAMEL, Ahmed
IPC分类号： B22F3/105 , B22F5/04 , B22F7/08 , F01D5/14 , F01D5/20
CPC分类号： B22F3/1055 , B22F5/04 , B22F7/08 , F01D5/147 , F01D5/20 , F05D2230/31 , F05D2300/606 , Y02P10/295
摘要： A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings (80) defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.
摘要翻译：一种燃气涡轮发动机叶片（10），其包括具有铸造壁的基座部分（12）和附接到所述基座部分并且具有壁（60）的顶端部分（14），所述壁由增材制造工艺。尖端部分壁可以形成为实心并且厚度小于2mm，或者其可以是波纹状的并且厚度大于2mm。限定壁波纹的开口（80）的横截面形状可以是半圆形，矩形，梯形或椭圆形。生成的叶片具有较低的叶尖重量，同时保持足够的机械性能尖端部分可以形成为在具有等轴晶粒结构的基底部分上具有定向凝固的晶粒结构。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式