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1.发明申请公开(公告)号：US20110014054A1
公开(公告)日：2011-01-20
申请号：US12827696
申请日：2010-06-30
申请人： Christoph NAGLER , Jose Anguisola Mc Feat , Sergei Riazantsev , Marcel Koenig , Erich Kreiselmaier
发明人： Christoph NAGLER , Jose Anguisola Mc Feat , Sergei Riazantsev , Marcel Koenig , Erich Kreiselmaier
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
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2.发明授权Guide vane of a gas turbine and method for replacing a cover plate of a guide vane of a gas turbine 有权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
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公开(公告)号：US08360725B2
公开(公告)日：2013-01-29
申请号：US12893307
申请日：2010-09-29
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。
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公开(公告)号：US20110064585A1
公开(公告)日：2011-03-17
申请号：US12893307
申请日：2010-09-29
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）。
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公开(公告)号：US08920110B2
公开(公告)日：2014-12-30
申请号：US12783046
申请日：2010-05-19
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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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。
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公开(公告)号：US20110236223A1
公开(公告)日：2011-09-29
申请号：US13075234
申请日：2011-03-30
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。
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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。
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公开(公告)号：US20110008177A1
公开(公告)日：2011-01-13
申请号：US12783046
申请日：2010-05-19
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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公开(公告)号：US09464529B2
公开(公告)日：2016-10-11
申请号：US13245707
申请日：2011-09-26
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05D2240/81 , F05D2260/202
摘要： A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.
摘要翻译： 用于燃气轮机的叶片包括具有布置在其上端上的护罩段的叶片翼型件。 护罩部分与叶片排的其它叶片的护罩部分一起形成环形护罩，其限定燃气轮机的热气体通道，并且所述护罩段在其邻接环形护罩的相邻护罩段的侧面上设置有 向上突出的侧轨，其沿着侧边缘延伸，以改善对热气体通道的密封。 侧轨包括轨道平行或基本上轨道平行的向上开口的狭槽，经由护罩段从叶片翼型的内部引入的冷却空气通过该槽排放到护罩段上方的空间中。
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