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

US20110110785A1 ROTOR FOR AN AXIAL-THROUGHFLOW TURBOMACHINE AND MOVING BLADE FOR SUCH A ROTOR 有权
标题翻译：用于这种转子的轴流式涡轮机转子和移动叶片
公开(公告)号：US20110110785A1
公开(公告)日：2011-05-12
申请号：US12942565
申请日：2010-11-09
申请人： Erich Kreiselmaier , Kurt Rubischon , Christoph Nagler , Herbert Brandl
发明人： Erich Kreiselmaier , Kurt Rubischon , Christoph Nagler , Herbert Brandl
IPC分类号： F04D29/34
CPC分类号： F01D5/3038 , F05D2230/232 , F05D2250/14 , F05D2250/141 , F05D2250/70 , F05D2250/71 , F05D2260/941
摘要： A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.
摘要翻译：提供了一种用于轴向通过涡轮机的转子，其承载多个移动叶片，每个叶片根据叶片根部被推入围绕轴线延伸的转子槽中并被保持。叶片根部包括具有锤头的锤根，并且被支撑在转子槽的径向止动面上，其位于径向方向上进一步向外，抵抗作用在活动叶片上的离心力，并且被支撑在进一步向内的轴向止动面上径向方向，抵抗作用在动叶片上的轴向力。转子槽在其底部具有减小热应力，轴向和径向加宽的底部区域，具有连续弯曲的横截面轮廓。在这种转子中，叶片的叶片根部在径向上适应于加宽的底部区域，从而实现叶片的有利的适应。

2. 发明授权

US08770938B2 Rotor for an axial-throughflow turbomachine and moving blade for such a rotor 有权
标题翻译：用于这种转子的轴向通流涡轮机和活动叶片的转子
公开(公告)号：US08770938B2
公开(公告)日：2014-07-08
申请号：US12942565
申请日：2010-11-09
申请人： Erich Kreiselmaier , Kurt Rubischon , Christoph Nagler , Herbert Brandl
发明人： Erich Kreiselmaier , Kurt Rubischon , Christoph Nagler , Herbert Brandl
IPC分类号： F01D5/30
CPC分类号： F01D5/3038 , F05D2230/232 , F05D2250/14 , F05D2250/141 , F05D2250/70 , F05D2250/71 , F05D2260/941
摘要： A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.
摘要翻译：提供了一种用于轴向通过涡轮机的转子，其承载多个移动叶片，每个叶片根据叶片根部被推入围绕轴线延伸的转子槽中并被保持。叶片根部包括具有锤头的锤根，并且被支撑在转子槽的径向止动面上，其位于径向方向上进一步向外，抵抗作用在活动叶片上的离心力，并且被支撑在进一步向内的轴向止动面上径向方向，抵抗作用在动叶片上的轴向力。转子槽在其底部具有减小热应力，轴向和径向加宽的底部区域，具有连续弯曲的横截面轮廓。在这种转子中，叶片的叶片根部在径向上适应于加宽的底部区域，从而实现叶片的有利的适应。

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. 发明授权

US08360725B2 Cooling duct arrangement within a hollow-cast casting 有权
标题翻译：中空铸造铸件内的冷却管道布置
公开(公告)号：US08360725B2
公开(公告)日：2013-01-29
申请号：US12893307
申请日：2010-09-29
申请人： Jose Ma Anguisola McFeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
发明人： Jose Ma Anguisola McFeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2260/22141
摘要： A cooling passage arrangement is provided inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium. The flow region is divided in the flow direction into two cooling passages by at least one rib line which is connected to the two cast-part walls. At least one gap is provided along the at least one rib line. At the least one gap, two rib ends are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section”.
摘要翻译：冷却通道装置设置在中空铸造铸件内部，其中流动区域由至少两个间隔开的铸件壁限定，用于冷却介质。流动区域通过连接到两个铸件壁的至少一个肋线在流动方向上分成两个冷却通道。沿着至少一个肋线提供至少一个间隙。在至少一个间隙处，两个肋端部相对设置一段距离，其中一个肋端部具有以希望骨-Y截面的形式的轮廓。

6. 发明申请

US20110064585A1 COOLING DUCT ARRANGEMENT WITHIN A HOLLOW-CAST CASTING 有权
标题翻译：在中空铸造中冷却导管装置
公开(公告)号：US20110064585A1
公开(公告)日：2011-03-17
申请号：US12893307
申请日：2010-09-29
申请人： Jose Ma Anguisola Mcfeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
发明人： Jose Ma Anguisola Mcfeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2260/22141
摘要： Described is a cooling passage arrangement inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium (K), which flow region is divided in the flow direction into two cooling passages (7) by at least one rib line (6) which is connected to the two cast-part walls.The invention is characterized in that provision is made along the at least one rib line (6) for at least one gap (13), at which two rib ends (61, 62) are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section” (14).
摘要翻译：描述了一种在中空铸造铸件内部的冷却通道装置，其中流动区域由用于冷却介质（K）的至少两个间隔开的铸件壁限定，该流动区域沿流动方向分成两部分冷却通道（7）通过连接到两个铸件壁的至少一个肋线（6）。本发明的特征在于，沿着至少一个间隙（13）沿着至少一个肋线（6）进行设置，两个肋端部（61,62）相对地间隔一定距离，其中一个肋端部具有“希望骨 - ”Y“ - 横截面”的风格的轮廓（14）。

7. 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

8. 发明申请

US20110236223A1 BLADE FOR A GAS TURBINE 审中-公开
标题翻译：燃气轮机叶片
公开(公告)号：US20110236223A1
公开(公告)日：2011-09-29
申请号：US13075234
申请日：2011-03-30
申请人： Christoph Nagler , Erich Kreiselmaier , Jose McFeat Anguisola , Sergei Riazantsev
发明人： Christoph Nagler , Erich Kreiselmaier , Jose McFeat Anguisola , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/80 , F05D2250/24 , Y02T50/676
摘要： A blade for a gas turbine includes an airfoil extending in a longitudinal direction and extending transversely to the longitudinal direction between a leading edge and a trailing edge. The airfoil has a pressure side, a suction side, and a slot-like cooling medium outlet extending along the trailing edge. The cooling medium outlet is configured to discharge cooling medium supplied from an inner space of the blade. A platform extends transversely to the longitudinal direction. An end of the airfoil merges into an underside of the platform and has a transition from the airfoil to the platform at the trailing edge of the airfoil that increases in thickness in a direction toward the underside of the platform. The cooling medium outlet extends into the platform so as to reduce an operating temperature in a region of the transition from the blade airfoil to the platform.
摘要翻译：用于燃气轮机的叶片包括在纵向方向上延伸并且在前缘和后缘之间横向于纵向方向延伸的翼型件。翼型件具有压力侧，吸力侧和沿着后缘延伸的槽状冷却介质出口。冷却介质出口构造成排出从叶片的内部空间供给的冷却介质。平台横向于纵向延伸。翼型的一端合并到平台的下侧，并且在翼型的后缘处具有从翼型到平台的过渡，其在朝向平台的下侧的方向上增加厚度。冷却介质出口延伸到平台中，以便在从叶片翼型到平台的过渡区域中降低工作温度。

9. 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。

10. 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。

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