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

US20210108520A1 ADDITIVE MANUFACTURING OPTIMIZED FIRST STAGE VANE 有权
公开(公告)号：US20210108520A1
公开(公告)日：2021-04-15
申请号：US16598550
申请日：2019-10-10
申请人： Power Systems Mfg., LLC
发明人： Gregory Edwin Vogel , Joshua Robert McNally , Vladimir Kitaigorod
IPC分类号： F01D5/28 , F01D9/04
摘要： An airfoil and turbine vanes and vane assemblies incorporating the same. The airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places. The Z values refer to a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of the inner platform. The turbine vane includes an inner platform, an outer platform, and an airfoil such as the one discussed above extending radially outward from the inner platform toward the outer platform. And the vane assembly includes an inner platform, an outer platform, and two or more first stage vanes extending from the inner platform to the outer platform. Each of the two or more first stage vanes include an airfoil as discussed above.

2. 发明授权

US10906100B2 Heat treatment process for additive manufactured components 有权
公开(公告)号：US10906100B2
公开(公告)日：2021-02-02
申请号：US16052321
申请日：2018-08-01
申请人： Power Systems Mfg., LLC
发明人： Gregory Edwin Vogel , Jeremy Metternich , Edwin John Kawecki , Jacob Snyder
IPC分类号： B22F3/10 , B22F5/00 , B22F3/105 , B22F3/24 , B22F5/04 , B33Y10/00 , F01D5/18 , C22F1/10 , B33Y40/00 , B33Y80/00
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.

3. 发明授权

US07685823B2 Airflow distribution to a low emissions combustor 有权
标题翻译：气流分配到低排放燃烧器
公开(公告)号：US07685823B2
公开(公告)日：2010-03-30
申请号：US11262447
申请日：2005-10-28
申请人： Vincent C. Martling , Zhenhua Xiao
发明人： Vincent C. Martling , Zhenhua Xiao
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。

4. 发明申请

US20060260316A1 Flashback Suppression System for a Gas Turbine Combustor 有权
标题翻译：燃气轮机燃烧器闪回抑制系统
公开(公告)号：US20060260316A1
公开(公告)日：2006-11-23
申请号：US10908682
申请日：2005-05-23
申请人： Peter Stuttaford
发明人： Peter Stuttaford
IPC分类号： F23R3/30
CPC分类号： F23R3/286 , F23D14/82 , F23L7/00 , F23L2900/07002 , F23R3/24
摘要： A gas turbine combustor having improved flashback margin is disclosed. Multiple embodiments of the present invention are disclosed including combustors having a single premix chamber as well as multiple premix chambers. Flashback margin is increased for the combustor by incorporating a means for introducing an inert gas, such as nitrogen, into the premix chamber(s) at the region proximate the boundary layer to purge the boundary layer of combustible mixture, thereby ensuring that no combustion reaction occurs in the boundary layer.
摘要翻译：公开了一种具有改善的闪回余量的燃气轮机燃烧器。公开了本发明的多个实施例，包括具有单个预混合室的燃烧器以及多个预混室。通过在靠近边界层的区域引入惰性气体（例如氮气）到预混合室中来提高燃烧器的闪回余量，以清除可燃混合物的边界层，从而确保没有燃烧反应发生在边界层。

5. 发明申请

US20060010873A1 Gas Turbine Combustor End Cover 有权
标题翻译：燃气轮机燃烧器端盖
公开(公告)号：US20060010873A1
公开(公告)日：2006-01-19
申请号：US10710525
申请日：2004-07-19
申请人： John Henriquez
发明人： John Henriquez
IPC分类号： F23R3/42
CPC分类号： F23R3/002 , F23R3/44
摘要： An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifolds machined into the end cover. The fluids within the end cover are kept separate proximate each of the plurality of first openings by a wall that is integrally formed from a portion of the end cover plate.
摘要翻译：公开了一种消除在端盖的板部分内使用钎焊接头的燃气轮机燃烧器的端盖。端盖包括板和多个流体入口，流体入口将流体引导到加工到端盖中的第一和第二歧管。通过由端盖板的一部分整体形成的壁，端盖内的流体被保持分离成靠近多个第一开口中的每一个。

6. 发明授权

US06957948B2 Turbine blade attachment lightening holes 失效
公开(公告)号：US06957948B2
公开(公告)日：2005-10-25
申请号：US10761766
申请日：2004-01-21
申请人： Tom Brooks , Richard Seleski , Thomas Churbuck , Thomas E. Brew, Jr.
发明人： Tom Brooks , Richard Seleski , Thomas Churbuck , Thomas E. Brew, Jr.
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/147 , F01D5/18
摘要： The present invention seeks to provide a turbine blade with increased creep capability for both uncooled and cooled turbine blades while generally maintaining operating stress levels at an interface region between the turbine blade and a turbine disk. A turbine blade is disclosed having an attachment, a neck, a platform, and an airfoil. Extending radially outward from the attachment, through the neck, and terminating radially inward of the platform is a plurality of first cavities. The turbine blade in accordance with the preferred embodiment of the present invention is cast from a high density nickel base alloy with high temperature capability and improved creep capability. A plurality of first cavities are placed in the attachment and neck region to reduce excess weight of the turbine blade due to the higher density, greater creep capable alloy. Reducing the weight of the blade in this region provides increased creep capability in the turbine blade airfoil while maintaining operating stress levels.

7. 发明授权

US06915636B2 Dual fuel fin mixer secondary fuel nozzle 有权
标题翻译：双燃料翅片混合器二次燃油喷嘴
公开(公告)号：US06915636B2
公开(公告)日：2005-07-12
申请号：US10465096
申请日：2003-06-19
申请人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Hany Rizkalla , Alfredo Cires
发明人： Peter Stuttaford , Stephen T. Jennings , Ryan McMahon , Hany Rizkalla , Alfredo Cires
IPC分类号： F23L7/00 , F23R3/28 , F23R3/36 , F02C1/00 , F02G3/00
CPC分类号： F23L7/002 , F23D2209/30 , F23D2214/00 , F23D2900/00008 , F23D2900/14004 , F23R3/286 , F23R3/36
摘要： A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly and simplify fuel nozzle manufacturing.
摘要翻译：公开了一种用于燃气轮机燃烧器的双燃料预混喷嘴和操作方法。双燃料预混喷嘴利用一种翅片组件，其包括多个径向延伸的翅片，用于喷射气体燃料和压缩空气，以便提供更均匀的注射模式和均匀的混合物。预混合燃料喷嘴包括多个同轴通道，其向翅片组件提供气体燃料和压缩空气。当处于液体燃料运行时，气体回路用压缩空气吹扫，液体燃料和水通过同轴通道到达双燃料预混燃料喷嘴的末端，在那里它们将液体燃料和水注入到二次燃烧室中。替代实施例包括沿着预混合燃料喷嘴的锥形锥形部分位于鳍片组件下游的附加气体燃料喷射区域。公开了第二替代实施例，其重新配置喷射器组件和燃料喷射位置以最小化喷射器组件处的流动阻塞问题并简化燃料喷嘴制造。

8. 发明授权

US06912838B2 Coated crossfire tube assembly 有权
标题翻译：涂层交火管总成
公开(公告)号：US06912838B2
公开(公告)日：2005-07-05
申请号：US10382410
申请日：2003-03-06
申请人： Gerry A. Sileo , Terry L. Hollis
发明人： Gerry A. Sileo , Terry L. Hollis
IPC分类号： F02C7/264 , F23R3/48 , F02C3/14
CPC分类号： F23R3/48 , F02C7/264 , F05D2230/313
摘要： A crossfire tube assembly is provided having an increased resistance to wear and oxidation. This increased resistance is provided by the application of coatings to the mating surfaces between the crossfire tube and crossfire tube clip. In the preferred embodiment, a physical vapor deposition (PVD) Titanium Aluminum Nitride coating is applied to the outer walls of the crossfire tubes which is used in combination with an air plasma spray (APS) Aluminum Bronze coating applied to the crossfire tube clip open end that mates with the crossfire tubes. The coating combination serves to protect the components from frictional wear and extend their life. In an alternate embodiment, the crossfire tubes also contain a plurality of air purge holes that provide a layer of cooling air along the crossfire tube inner wall.
摘要翻译：提供了具有增加的耐磨性和氧化性的交火管组件。这种增加的阻力是通过将涂层施加到交火管和交火管夹之间的配合表面来提供的。在优选实施例中，将物理气相沉积（PVD）钛氮化铝涂层施加到交火管的外壁，其与施加到交火管夹开口端的空气等离子体喷涂（APS）铝青铜涂层组合使用与交火管配合。涂层组合用于保护组件免受摩擦磨损并延长其使用寿命。在替代实施例中，交叉火管还包含多个空气吹扫孔，其沿交火管内壁提供冷却空气层。

9. 发明授权

US06910336B2 Combustion liner cap assembly attachment and sealing system 有权
标题翻译：燃烧衬套帽组件附件和密封系统
公开(公告)号：US06910336B2
公开(公告)日：2005-06-28
申请号：US10368754
申请日：2003-02-18
申请人： Daniel J. Sullivan , Shawn Miller , Miguel A. Garrido , Vincent C. Martling
发明人： Daniel J. Sullivan , Shawn Miller , Miguel A. Garrido , Vincent C. Martling
IPC分类号： F23R3/00 , F23R3/10 , F23R3/60 , F22R3/46
CPC分类号： F23R3/10 , F23R3/002 , F23R3/60
摘要： An attachment and sealing system for securing a combustor cap assembly to a combustion chamber, while providing effective cooling to the combustor cap assembly aft end, is disclosed. The combustor cap assembly is secured within a combustion chamber by a plurality of pins such that the aft end region of the combustor cap assembly is cooled by a fluid medium that is injected through a plurality of first holes in the combustion chamber wall. A generally annular seal, which encompasses the combustor cap assembly, has a plurality of raised ridges, which are in sealing contact with the combustion chamber wall. Multiple embodiments are disclosed regarding the length of the generally annular seal and position and orientation of the plurality of first cooling holes in the combustion chamber wall.
摘要翻译：公开了一种用于将燃烧器盖组件固定到燃烧室的附接和密封系统，同时向燃烧器盖组件后端提供有效的冷却。燃烧器盖组件通过多个销固定在燃烧室内，使得燃烧器盖组件的后端区域被注入燃烧室壁中的多个第一孔的流体介质冷却。包围燃烧器盖组件的大致环形密封件具有多个与燃烧室壁密封接触的凸脊。公开了关于大致环形密封件的长度以及燃烧室壁中的多个第一冷却孔的位置和取向的多个实施例。

10. 发明授权

US06904756B2 Transition duct support bracket wear cover 有权
标题翻译：过渡管支撑架磨损罩
公开(公告)号：US06904756B2
公开(公告)日：2005-06-14
申请号：US10377052
申请日：2003-02-28
申请人： Brian R. Mack
发明人： Brian R. Mack
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D9/023
摘要： A wear cover for use on a gas turbine transition duct support bracket is disclosed. The wear cover, which is manufactured from a single piece of sheet metal, does not require complex manufacturing processes or tools, thereby reducing component cost. The wear cover comprises first and second leg portions substantially parallel to each other and each generally perpendicular to a third leg portion. Each of the leg portions serve to protect a surface of a support bracket finger from excessive wear associated with frictional contact with mounting blocks of a transition duct. The wear cover is designed to slip onto a support bracket finger through a first opening and is fixed to the finger by a means such as welding.
摘要翻译：公开了一种用于燃气轮机过渡管道支撑支架上的耐磨盖。由单片金属板制成的磨损罩不需要复杂的制造工艺或工具，从而降低部件成本。磨损罩包括基本上彼此平行并且大致垂直于第三腿部的第一和第二腿部。每个腿部部分用于保护支撑托架手指的表面免受与与过渡管道的安装块的摩擦接触相关的过度磨损。磨损罩设计成通过第一开口滑入支撑支架指状物，并通过诸如焊接的手段固定到手指上。

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