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

WO2008091377A2 NICKEL-BASE ALLOY FOR GAS TURBINE APPLICATIONS 审中-公开
标题翻译：用于汽轮机应用的镍基合金
公开(公告)号：WO2008091377A2
公开(公告)日：2008-07-31
申请号：PCT/US2007/074320
申请日：2007-07-25
申请人： POWER SYSTEMS MFG., LLC
发明人： BIONDO, Charles , STROHL, J., Page , SAMUELSON, Jeffery, W. , FUCHS, Gerhard, E.
IPC分类号： C22C19/05
CPC分类号： C22F1/10 , C22C19/03 , C22C19/05 , C22C19/056
摘要： A nickel-based alloy suitable for casting gas turbine components having a lower density and basic heat treating process while achieving improved strength is disclosed. Multiple embodiments of the alloy are disclosed capable of providing both directionally-solidified and equiaxed castings. Also disclosed is a method of making a cast and heat treated article utilizing the improved nickel-base alloy.
摘要翻译：公开了适用于铸造具有较低密度和基本热处理工艺的燃气涡轮机部件同时实现改善的强度的镍基合金。公开了能够提供定向凝固和等轴铸造两者的合金的多个实施例。还公开了使用改进的镍基合金制造铸造和热处理制品的方法。

2. 发明申请

WO2004038197A1 TRANSITION DUCT WITH ENHANCED PROFILE OPTIMIZATION 审中-公开
标题翻译：具有增强型材优化的TRANSITION DUCT
公开(公告)号：WO2004038197A1
公开(公告)日：2004-05-06
申请号：PCT/US2003/013589
申请日：2003-05-01
申请人： POWER SYSTEMS MFG., LLC
发明人： JORGENSEN, Stephen, W. , RESOS, John, C. , XIAO, Zhenhua , JOHNSTON, Heather
IPC分类号： F02C1/00
CPC分类号： F01D9/023
摘要： A transition duct (20) having a panel assembly (23) with an inlet end (21) of generally circular cross section and an outlet end (22) having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1 carried only to three decimal places wherein the coordinates are taken at a sweep angle θ wherein θ is an angle measured from said inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle θ from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.
摘要翻译：公开了具有具有大致圆形横截面的入口端（21）的面板组件（23）和具有大致矩形的弧形横截面的出口端（22）的过渡管道（20）。面板组件具有基本上根据如表1所示的坐标值X，Y和Z的未涂覆的内部轮廓，其仅承载在三位小数位置，其中坐标是以扫描角θ拍摄的，其中θ是从所述入口端和X，Y和Z是在入口端的每个角度θ处限定面板组件轮廓的坐标。还公开了一种替代实施例，其限定面板组件的未涂覆内部轮廓的包络。

3. 发明申请

WO2019025996A1 HEAT TREATMENT PROCESS FOR ADDITIVE MANUFACTURED COMPONENTS 审中-公开
公开(公告)号：WO2019025996A1
公开(公告)日：2019-02-07
申请号：PCT/IB2018/055776
申请日：2018-08-01
申请人： POWER SYSTEMS MFG., LLC
发明人： VOGEL, Gregory Edwin , METTERNICH, Jeremy , KAWECKI, Edwin John , SNYDER, Jacob
IPC分类号： B22F3/24 , B22F5/00 , B22F5/04 , C22F1/10 , B33Y40/00
CPC分类号： B22F3/1028 , B22F3/1055 , B22F3/24 , B22F5/009 , B22F5/04 , B22F2003/248 , B22F2998/10 , B33Y10/00 , B33Y40/00 , B33Y80/00 , C22F1/10 , F01D5/187 , F05D2230/22 , F05D2230/31
摘要： A method for manufacturing and heat treating a component formed from an alloy or superalloy. The component may be part of a gas turbine engine, such as an airfoil of a gas turbine engine turbine, or a combustor fuel nozzle, that includes internal cooling passages. At least part of the component is formed from the alloy or superalloy using an additive manufacturing process. The method includes determining an incipient melting point range and a recrystallization temperature of the alloy or superalloy. The component is then heated to at least the recrystallization temperature and within the incipient melting point range for a predetermined time, and ultimately cooled.

4. 发明申请

WO2007053323A3 IMPROVED AIRFLOW DISTRIBUTION TO A LOW EMISSION COMBUSTOR 审中-公开
标题翻译：改进对低排放燃烧室的气流分配
公开(公告)号：WO2007053323A3
公开(公告)日：2007-08-02
申请号：PCT/US2006040903
申请日：2006-10-19
申请人： POWER SYSTEMS MFG LLC
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F23R3/04 , F23R3/54
摘要： An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.
摘要翻译：公开了一种提供具有增加的燃烧稳定性和降低通过燃气轮机燃烧器的压降的燃气轮机燃烧器的设备和方法。多个叶片在流动套筒和燃烧衬套之间径向地固定到流动套筒。多个叶片用于引导进入流动套筒和燃烧衬套之间的区域的基本轴向方向的空气流，使得切向速度分量被去除，由此提供燃烧室的更均匀的空气流动并且减少由于试图仅通过压力降低气流而造成的压力损失。

5. 发明申请

WO2007053323A2 IMPROVED AIRFLOW DISTRIBUTION TO A LOW EMISSION COMBUSTOR 审中-公开
标题翻译：改进的气流分配到低排放燃烧器
公开(公告)号：WO2007053323A2
公开(公告)日：2007-05-10
申请号：PCT/US2006/040903
申请日：2006-10-19
申请人： POWER SYSTEMS MFG., LLC
IPC分类号： F02C3/06
CPC分类号： F01D9/023 , F23R3/04 , F23R3/54
摘要： An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.
摘要翻译：公开了一种提供具有增加的燃烧稳定性并减少跨越燃气轮机燃烧器的压降的燃气轮机燃烧器的装置和方法。多个叶片在流动套筒和燃烧衬套之间径向固定到流动套管。多个叶片用于引导进入流动套筒和燃烧衬套之间的区域的空气流在大致轴向方向上，从而去除切向速度的分量，从而提供更均匀的空气流，并减少燃烧室的量由于试图通过单独的压力降低气流而导致的压力损失。

6. 发明申请

WO2004013465A1 THERMALLY FREE AFT FRAME FOR A TRANSITION DUCT 审中-公开
标题翻译：用于过渡式导管的免费AFT框架
公开(公告)号：WO2004013465A1
公开(公告)日：2004-02-12
申请号：PCT/US2003/013280
申请日：2003-05-01
申请人： POWER SYSTEMS MFG., LLC
发明人： JORGENSEN, Stephen, W.
IPC分类号： F01D25/26
CPC分类号： F01D25/26 , F01D9/023 , Y10S138/04
摘要： A transition duct with a thermally free aft frame for use in a gas turbine engine is disclosed. The transition duct includes an aft frame that is thermally free through the use of a plurality of retention lugs, bushings, and bulkhead assemblies. The aft frame is allowed to adjust from thermal changes as a result of relative sizing between the bushings and retention lugs of the aft frame. An additional feature of this invention is the use of radially extending ribs along the sidewalls of the aft frame, to form an interlocking sealing means with adjacent transition ducts to reduce the amount compressor air leakage into the turbine inlet.
摘要翻译：公开了一种用于燃气涡轮发动机的具有无热后视框架的过渡管道。过渡管道包括通过使用多个保持凸耳，衬套和隔板组件而无热的后框架。由于后框架的衬套和保持凸耳之间的相对尺寸，后框架被允许从热变化调节。本发明的一个附加特征是沿着后部框架的侧壁使用沿径向延伸的肋条，以形成具有相邻过渡管道的互锁密封装置，以减少压缩机空气泄漏到涡轮机入口中的量。

7. 发明申请

WO2008091377A3 NICKEL-BASE ALLOY FOR GAS TURBINE APPLICATIONS 审中-公开
标题翻译：用于气体涡轮应用的镍基合金
公开(公告)号：WO2008091377A3
公开(公告)日：2008-12-24
申请号：PCT/US2007074320
申请日：2007-07-25
申请人： POWER SYSTEMS MFG LLC
发明人： BIONDO CHARLES , STROHL J PAGE , SAMUELSON JEFFERY W , FUCHS GERHARD E , WLODEK STANLEY T , WLODEK RAMONA T
IPC分类号： C22C19/03
CPC分类号： C22F1/10 , C22C19/03 , C22C19/05 , C22C19/056
摘要： A nickel-based alloy suitable for casting gas turbine components having a lower density and basic heat treating process while achieving improved strength is disclosed. Multiple embodiments of the alloy are disclosed capable of providing both directionally-solidified and equiaxed castings. Also disclosed is a method of making a cast and heat treated article utilizing the improved nickel-base alloy.
摘要翻译：公开了一种适用于铸造具有较低密度和基础热处理工艺的燃气轮机部件同时实现改进的强度的镍基合金。公开了能够提供定向凝固和等轴铸件的合金的多个实施例。还公开了利用改进的镍基合金制造铸造和热处理制品的方法。

8. 发明申请

WO2003029616A1 TURBINE BLADE POCKET SHROUD 审中-公开
标题翻译：涡轮叶片口袋
公开(公告)号：WO2003029616A1
公开(公告)日：2003-04-10
申请号：PCT/US2002/023263
申请日：2002-07-23
申请人： POWER SYSTEMS MFG, LLC
发明人： SELESKI, Richard , CHIURATO, Remo
IPC分类号： F01D5/22
CPC分类号： F01D5/187 , F01D5/147 , F01D5/225 , F05D2260/232 , F05D2260/2322
摘要： An improved gas turbine blade (40) is disclosed that utilizes a blade tip shroud (46) with tapered shroud pockets (52) to remove excess weight from the shroud (46) while not compromising shroud bending stresses. Excess shroud weight removed by the tapered pockets (52) reduces overall blade pull while maintaining material necessary to increase shroud stiffness. The resulting rib (53) created between the tapered pockets (52) provides a surface, away from possible areas of stress concentration, for drilling radial cooling holes (54).
摘要翻译：公开了一种改进的燃气轮机叶片（40），其利用具有锥形护罩袋（52）的叶片护罩（46），以从护罩（46）移除多余的重量，同时不损害护罩弯曲应力。通过锥形凹部（52）去除的过多的护罩重量降低了整体刀片拉动，同时保持了增加护罩刚度所需的材料。在锥形凹部（52）之间产生的所得肋（53）提供远离可能的应力集中区域的表面，用于钻出径向冷却孔（54）。

9. 发明申请

WO2023091306A2 MULTITUBE PILOT INJECTOR HAVING A FLAME ANCHOR FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2023091306A2
公开(公告)日：2023-05-25
申请号：PCT/US2022/048862
申请日：2022-11-03
申请人： POWER SYSTEMS MFG., LLC , KALB, Bryan , YAQUINTO, Matthew , CHONG, Gene , PARADES, David , BRACKETT, James , VOGEL, Gregory , RIZKALLA, Hany , SAM, Bernard Tam Yen , KESHAVA-BHATTU, Ramesh , HERNANDEZ, Fred , MCNALLY, Joshua R.
发明人： KALB, Bryan , YAQUINTO, Matthew , CHONG, Gene , PARADES, David , BRACKETT, James , VOGEL, Gregory , RIZKALLA, Hany , SAM, Bernard Tam Yen , KESHAVA-BHATTU, Ramesh , HERNANDEZ, Fred , MCNALLY, Joshua R.
摘要： An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A blocker is provided at an outlet portion of each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes and/or the radially inner subset of air/fuel mixing tubes to form a flame anchoring surface.

10. 发明申请

WO2004040108A1 EFFUSION COOLED TRANSITION DUCT WITH SHAPED COOLING HOLES 审中-公开
标题翻译：带有冷却过滤器的冷却过滤器
公开(公告)号：WO2004040108A1
公开(公告)日：2004-05-13
申请号：PCT/US2003/013204
申请日：2003-05-01
申请人： POWER SYSTEMS MFG., LLC
发明人： LEAHY, James, H.
IPC分类号： F02C3/14
CPC分类号： F01D9/023 , F05D2260/202
摘要： An effusion cooled transition duct (40) with angled film cooling holes in the axial and optionally transverse directions is disclosed.
摘要翻译：公开了一种在轴向和任选地横向上具有成角度的薄膜冷却孔的渗出冷却的过渡管道（40）。

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