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11. 发明授权

US07334800B2 Seal for a gas turbine engine having improved flexibility 有权
标题翻译：具有改进的灵活性的燃气涡轮发动机的密封
公开(公告)号：US07334800B2
公开(公告)日：2008-02-26
申请号：US10907016
申请日：2005-03-16
申请人： Mark Minnich
发明人： Mark Minnich
IPC分类号： F16J15/02 , F16J15/08
CPC分类号： F16J15/0887 , F01D11/005 , F05D2240/57
摘要： A seal extending between adjacent slots of a gas turbine engine is disclosed. The seal comprises a plurality of generally planar members fixed together along a central axis. The outer member further comprises rounded ends that encompass the second and plurality of third generally planar members. The seal disclosed herein improves sealing capability by providing a more compliant seal over the prior art while reducing the mechanical loads experienced along the seal weld joint, thereby improving seal durability.
摘要翻译：公开了在燃气涡轮发动机的相邻狭槽之间延伸的密封件。密封件包括沿着中心轴固定在一起的多个大致平面的构件。外部构件还包括围绕第二和多个第三大体平坦构件的圆形端部。这里公开的密封件通过在现有技术中提供比较顺从的密封件来提高密封能力，同时减少沿着密封焊接接头的机械载荷，从而提高密封耐久性。

12. 发明授权

US07293957B2 Vane platform rail configuration for reduced airfoil stress 有权
标题翻译：叶片平台导轨配置减少翼型应力
公开(公告)号：US07293957B2
公开(公告)日：2007-11-13
申请号：US11692505
申请日：2007-03-28
申请人： Charlie Ellis , David Parker , J. Page Strohl , David Medrano
发明人： Charlie Ellis , David Parker , J. Page Strohl , David Medrano
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D11/005 , F05D2260/941
摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resistance to thermal deflection. This is accomplished by placing an opening along the innermost vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.
摘要翻译：公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。这是通过沿着最内侧叶片组装轨道放置开口来实现的，该开口减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。

13. 发明申请

US20070240422A1 Gas turbine transition duct 有权
标题翻译：燃气轮机过渡管
公开(公告)号：US20070240422A1
公开(公告)日：2007-10-18
申请号：US11404343
申请日：2006-04-14
申请人： Stephen Jorgensen , Heather Johnston
发明人： Stephen Jorgensen , Heather Johnston
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F05D2250/20 , F05D2250/74
摘要： A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end 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. The coordinates are taken at a sweep angle θ wherein θ is an angle measured from the 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：公开了一种具有具有大致圆形截面的入口端和具有大致矩形的弧形横截面的出口端的面板组件的过渡管道。面板组件具有基本上根据表1所示的坐标值X，Y和Z的未涂覆内部轮廓。坐标是以扫描角θ拍摄的，其中θ是从入口端测量的角度，X，Y ，Z是从入口端在每个角度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。

14. 发明授权

US07178340B2 Transition duct honeycomb seal 有权
标题翻译：过渡管蜂窝密封
公开(公告)号：US07178340B2
公开(公告)日：2007-02-20
申请号：US10669924
申请日：2003-09-24
申请人： Stephen W. Jorgensen
发明人： Stephen W. Jorgensen
IPC分类号： F01D25/24 , F02C7/20
CPC分类号： F01D11/003 , F01D9/023
摘要： A sealing device for use between a gas turbine combustor transition duct aft frame and a turbine inlet having improved durability, reduced wear on the mating turbine vane, and reduced manufacturing costs, is disclosed. The sealing device has a circumferential length, an axial width, and a radial height and contains a plurality of channels extending axially along the seal inner surface for passing a controlled amount of cooling air to a turbine inlet. The sealing device is formed of abradable honeycomb having a plurality of honeycomb cells with the honeycomb cells oriented to ensure maximum control against cooling air leakage while also providing maximum flexibility during assembly. The sealing device is captured between the transition duct aft frame, bulkhead, and turbine vane platform, thereby allowing easy replacement of the seal without requiring major disassembly of the transition duct aft frame section.
摘要翻译：公开了一种用于燃气轮机燃烧器过渡管后部框架和具有改善的耐久性的涡轮进口，减少配合涡轮叶片上的磨损以及降低的制造成本的密封装置。密封装置具有圆周长度，轴向宽度和径向高度，并且包含沿密封件内表面轴向延伸的多个通道，用于将受控量的冷却空气传递到涡轮机入口。密封装置由具有多个蜂窝单元的可耐磨蜂窝体形成，蜂窝单元取向成确保对冷却空气泄漏的最大控制，同时在组装期间也提供最大的灵活性。密封装置被捕获在过渡管道后部框架，隔板和涡轮叶片平台之间，从而允许容易地更换密封件，而不需要重新拆卸过渡管道后部框架部分。

15. 发明授权

US06932577B2 Turbine blade airfoil having improved creep capability 有权
标题翻译：涡轮叶片翼型具有改善的蠕变能力
公开(公告)号：US06932577B2
公开(公告)日：2005-08-23
申请号：US10719927
申请日：2003-11-21
申请人： J. Page Strohl , David G. Parker , Michael Barrett
发明人： J. Page Strohl , David G. Parker , Michael Barrett
IPC分类号： B63H1/14 , F01D5/14 , F01D5/18
CPC分类号： F01D5/187 , F01D5/141
摘要： A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil. The aerodynamic profile of the airfoil has been reconfigured to reduce airfoil stress for a given operating temperature, thereby resulting in increased creep rupture life of the airfoil.
摘要翻译：公开了一种包括具有根据表1的轮廓的翼型的涡轮叶片。涡轮机叶片具有径向向外延伸穿过翼型的多个冷却通道。已经重构了翼型件的空气动力学特性，以减少给定工作温度下的翼型应力，从而导致翼型件的蠕变断裂寿命增加。

16. 发明授权

US06857271B2 Secondary fuel nozzle with readily customizable pilot fuel flow rate 有权
标题翻译：二次燃料喷嘴具有易于定制的先导燃料流量
公开(公告)号：US06857271B2
公开(公告)日：2005-02-22
申请号：US10320990
申请日：2002-12-16
申请人： Robert J. Kraft , Alfredo Cires
发明人： Robert J. Kraft , Alfredo Cires
IPC分类号： F02C7/32 , F23D14/64 , F23R3/28 , F23R3/14 , F02C7/22
CPC分类号： F23D14/64 , F02C7/32 , F23R3/286
摘要： An improved secondary fuel distribution system having a readily adjustable premix pilot nozzle for use in a gas turbine combustor is disclosed. The secondary fuel nozzle assembly has a premix fuel nozzle comprising an annular tubular manifold and a premix pilot nozzle. Multiple embodiments of premix pilot nozzles are disclosed that have a fuel flow rate that can be controlled and adjusted as required, including a plate and feed hole combination, a pressfit premix pilot nozzle, and a premix pilot nozzle that is threaded into the secondary fuel nozzle assembly.
摘要翻译：公开了一种改进的二次燃料分配系统，其具有用于燃气轮机燃烧器中的易于调节的预混合引燃喷嘴。二次燃料喷嘴组件具有包括环形管状歧管和预混合引燃喷嘴的预混合燃料喷嘴。公开了预混合引燃喷嘴的多个实施例，其具有可根据需要进行控制和调节的燃料流量，包括板和进料孔组合，加压预混合引燃喷嘴和螺旋进入次燃料喷嘴的预混合引燃喷嘴部件。

17. 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.

18. 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.

19. 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。

20. 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。

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