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1. 发明申请

US20110236222A1 BLADE FOR A GAS TURBINE AND CASTING TECHNIQUE METHOD FOR PRODUCING SAME 审中-公开
标题翻译：一种用于生产气体的燃气轮机和铸造技术方法
公开(公告)号：US20110236222A1
公开(公告)日：2011-09-29
申请号：US12961659
申请日：2010-12-07
申请人： Jose Anguisola MCFEAT , Jörg KRÜCKELS , Roland DÜCKERSHOFF , Brian Kenneth WARDLE
发明人： Jose Anguisola MCFEAT , Jörg KRÜCKELS , Roland DÜCKERSHOFF , Brian Kenneth WARDLE
IPC分类号： F01D5/18 , B22C9/00 , B22D25/02
CPC分类号： B22D25/02 , B22C7/06 , B22C9/10 , F01D5/147 , F05D2230/211
摘要： A blade for a gas turbine has a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough. A multiplicity of turbulators or pins, which are formed on the wall, are arranged in a distributed manner in the region of the trailing edge and project from the internal surfaces into the cavity, to improve the transfer of heat between the wall of the blade and the cooling air. An improvement of the internal cooling is achieved by the turbulators or pins extending into the cavity in a direction which can be freely selected within an angular range.
摘要翻译：用于燃气轮机的叶片具有前缘和后缘以及由内表面限定的用于引导冷却空气的内腔。形成在壁上的多个紊流器或销以分布的方式布置在后缘的区域中并从内表面突出到空腔中，以改善叶片的壁和冷却空气。内部冷却的改进是通过在可以在角度范围内自由选择的方向上延伸到空腔中的扰流器或销钉实现的。

2. 发明授权

US07628587B2 Gas turbine blade shroud 有权
标题翻译：燃气轮机叶片护罩
公开(公告)号：US07628587B2
公开(公告)日：2009-12-08
申请号：US11589262
申请日：2006-10-30
申请人： Jose Anguisola McFeat , Ingolf Schulz , Dirk Wilhelm
发明人： Jose Anguisola McFeat , Ingolf Schulz , Dirk Wilhelm
IPC分类号： B63H1/16
CPC分类号： F01D5/141 , B33Y80/00 , F01D5/225 , F05D2230/90 , F05D2240/80 , F05D2250/12 , F05D2250/13 , F05D2250/141
摘要： A gas turbine blade shroud includes a platform and one or more fins extending toward a stator and side rails that extend radially toward the stator and along the edge of the platform. The increased wall thickness in the side regions of the blade shroud effects an increase in stiffness and a decrease in deformation during turbine operation. Due to a localised increase in wall thickness the mass of the blade shroud can be minimized such that mechanical loading is not significantly increased. The side rails can improve a lining up of adjacent blades and decrease a probability of hot gas leakage into the cavity between blade shroud and stator. The side rails have profile shapes that can be optimised in view of stiffness and mechanical loading and are suitable for casting. The blade shroud with side rails can have an improved life time.
摘要翻译：燃气轮机叶片护罩包括平台和朝向定子延伸的一个或多个翅片和沿着定子并沿着平台的边缘径向延伸的侧轨道。在叶片护罩的侧部区域中增加的壁厚在涡轮机操作期间增加刚度和变形减小。由于壁厚的局部增加，叶片护罩的质量可以最小化，使得机械负载不会显着增加。侧轨可以改善相邻叶片的排列，并降低热气体泄漏到叶片护罩和定子之间的空腔的可能性。侧轨具有可根据刚度和机械载荷优化的轮廓形状，并且适合于铸造。具有侧轨的刀片护罩可以具有改善的寿命。

3. 发明授权

US08920110B2 Gas turbine vane with improved cooling 有权
标题翻译：燃气轮机叶片具有改进的冷却
公开(公告)号：US08920110B2
公开(公告)日：2014-12-30
申请号：US12783046
申请日：2010-05-19
申请人： Jose Anguisola McFeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
发明人： Jose Anguisola McFeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/186 , F01D5/188 , F01D9/02 , F05D2240/81 , F05D2260/201
摘要： The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.
摘要翻译：本发明涉及一种中空燃气涡轮机叶片，该中空燃气涡轮机叶片由构造成顺序冷却叶片的端壁及其翼型并且同时为叶片的两个端壁顺序冷却的装置而冷却。这种布置可以减少冷却空气需求，这可能对涡轮机的效率产生积极的影响。

4. 发明授权

US08142143B2 Guide vane for a gas turbine 有权
标题翻译：燃气轮机导叶
公开(公告)号：US08142143B2
公开(公告)日：2012-03-27
申请号：US12884851
申请日：2010-09-17
申请人： Erich Kreiselmaier , Jose Anguisola McFeat , Christoph Nagler , Sergei Riazantsev , Brian Kenneth Wardle
发明人： Erich Kreiselmaier , Jose Anguisola McFeat , Christoph Nagler , Sergei Riazantsev , Brian Kenneth Wardle
IPC分类号： F04D29/54
CPC分类号： F01D25/246 , F01D11/005 , F01D25/08 , F05D2240/10 , F05D2240/11 , F05D2240/81 , F05D2270/114
摘要： A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud.
摘要翻译：一种用于燃气轮机的定子叶片包括在叶片的纵向方向上延伸并由前缘和后缘限定的叶片翼型件。定子叶片包括护罩，其内侧暴露于流过燃气轮机的热气体。用于将定子叶片紧固在燃气涡轮机壳体上的钩状紧固元件在后缘区域中向外突出。紧固元件具有在后缘上方的定位槽，用于固定热屏蔽件，该隔热罩沿着热气体的流动方向连接到护罩。在护罩之间设置有用于隔热罩的定位槽和叶片翼型件的后缘之间的空腔，用于减小后缘和护罩之间的过渡区域内的热和机械应力。

5. 发明申请

US20050118024A1 Coolable component 失效
标题翻译：可冷却组件
公开(公告)号：US20050118024A1
公开(公告)日：2005-06-02
申请号：US10992789
申请日：2004-11-22
申请人： Jose Anguisola McFeat , Werner Balbach
发明人： Jose Anguisola McFeat , Werner Balbach
IPC分类号： F01D5/18 , F04D31/00
CPC分类号： F01D5/186 , F01D5/188 , F05D2260/607
摘要： Throughflow openings are provided for a cooling medium in a coolable component. The throughflow opening comprises an insert that reduces the size of the first opening cross-section to a second opening cross-section, and that is released from the first opening if the second opening cross-section becomes blocked as a result of a local temperature rise and a thermally unstable joining between the insert and the component, being mounted in a first opening. The present throughflow opening greatly reduces the risk of damage to components to be cooled, in particular turbine blades, as a result of fine throughflow openings becoming blocked.
摘要翻译：为可冷却部件中的冷却介质提供流通开口。通流开口包括将第一开口横截面尺寸减小到第二开口横截面的插入件，并且如果第二开口横截面由于局部温度升高而被阻塞，则该插入件从第一开口释放以及插入件和部件之间的热不稳定接合，安装在第一开口中。当前的通流开口大大降低了被冷却的部件，特别是涡轮叶片损坏的风险，这是由于细流通开口被阻塞的结果。

6. 发明授权

US08727720B2 Guide vane of a gas turbine and method for replacing a cover plate of a guide vane of a gas turbine 有权
标题翻译：燃气轮机的导向叶片和用于更换燃气轮机的导向叶片的盖板的方法
公开(公告)号：US08727720B2
公开(公告)日：2014-05-20
申请号：US12827696
申请日：2010-06-30
申请人： Christoph Nagler , Jose Anguisola McFeat , Sergei Riazantsev , Marcel Koenig , Erich Kreiselmaier
发明人： Christoph Nagler , Jose Anguisola McFeat , Sergei Riazantsev , Marcel Koenig , Erich Kreiselmaier
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D5/005 , F05D2240/80
摘要： The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.
摘要翻译：燃气轮机的引导叶片包括具有可连接到导向叶片承载件或燃气轮机壳体的外部平台的叶片，并且在相对端具有承载盖板的内部平台。内平台具有连接盖板的燕尾形外壳。更换盖板的方法在于通过沿着燕尾形外壳的轮廓切割将盖板与内平台分开，然后使盖板从燕尾壳体滑出，从而将新的或翻新的盖板插入燕尾屋

7. 发明申请

US20120063891A1 COOLED COMPONENT FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的冷却组件
公开(公告)号：US20120063891A1
公开(公告)日：2012-03-15
申请号：US13247429
申请日：2011-09-28
申请人： Jörg Krückels , Tanguy Arzel , Jose Anguisola Mcfeat , Martin Schnieder
发明人： Jörg Krückels , Tanguy Arzel , Jose Anguisola Mcfeat , Martin Schnieder
IPC分类号： F04D29/58
CPC分类号： F01D5/186 , F01D5/187 , F01D5/225 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A cooled component for a gas turbine is disclosed, which by an outer side of a wall delimits hot gas passage of the gas turbine and on an inner side has a device for impingement cooling. The impingement cooling device can include a multiplicity of impingement cooling chambers which are arranged next to each other, operate in parallel, are covered by impingement cooling plates which are equipped with impingement cooling holes, and are impinged upon by cooling air during operation.
摘要翻译：公开了一种用于燃气轮机的冷却部件，其通过壁的外侧限定燃气轮机的热气体通道，并且在内侧具有用于冲击冷却的装置。冲击冷却装置可以包括彼此相邻布置的多个冲击冷却室，并联操作，被装有冲击冷却孔的冲击冷却板覆盖，并且在操作期间被冷却空气撞击。

8. 发明申请

US20110070089A1 GUIDE VANE FOR A GAS TURBINE 有权
标题翻译：燃气轮机指南
公开(公告)号：US20110070089A1
公开(公告)日：2011-03-24
申请号：US12884851
申请日：2010-09-17
申请人： Erich Kreiselmaier , Jose Anguisola McFeat , Christoph Nagler , Sergei Riazantsev , Brian Kenneth Wardle
发明人： Erich Kreiselmaier , Jose Anguisola McFeat , Christoph Nagler , Sergei Riazantsev , Brian Kenneth Wardle
IPC分类号： F01D5/30
CPC分类号： F01D25/246 , F01D11/005 , F01D25/08 , F05D2240/10 , F05D2240/11 , F05D2240/81 , F05D2270/114
摘要： A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud, thereby extending the service life of the stator blade.
摘要翻译：一种用于燃气轮机的定子叶片包括在叶片的纵向方向上延伸并由前缘和后缘限定的叶片翼型件。定子叶片包括护罩，其内侧暴露于流过燃气轮机的热气体。用于将定子叶片紧固在燃气涡轮机壳体上的钩状紧固元件在后缘区域中向外突出。紧固元件具有在后缘上方的定位槽，用于固定热屏蔽件，该隔热罩沿着热气体的流动方向连接到护罩。在护罩之间设置有用于隔热罩的定位槽和叶片翼型的后缘之间的空腔，用于减小后缘和护罩之间的过渡区域内的热和机械应力，从而延长了定子的使用寿命刀。

9. 发明申请

US20110008177A1 GAS TURBINE VANE WITH IMPROVED COOLING 有权
标题翻译：燃气涡轮风扇改进冷却
公开(公告)号：US20110008177A1
公开(公告)日：2011-01-13
申请号：US12783046
申请日：2010-05-19
申请人： Jose ANGUISOLA MCFEAT , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
发明人： Jose ANGUISOLA MCFEAT , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F01D9/02 , F05D2240/81 , F05D2260/201
摘要： The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.
摘要翻译：本发明涉及一种中空燃气涡轮机叶片，该中空燃气涡轮机叶片由构造成顺序冷却叶片的端壁及其翼型并且同时为叶片的两个端壁顺序冷却的装置而冷却。这种布置可以减少冷却空气需求，这可能对涡轮机的效率产生积极的影响。

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