-
公开(公告)号：US20110286849A1
公开(公告)日：2011-11-24
申请号：US13091605
申请日：2011-04-21
IPC分类号： F01D5/14
CPC分类号： F01D5/225 , F05B2240/33
摘要： A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
摘要翻译： 公开了一种用于燃气涡轮机的叶片，其包括翼型件，该翼型件沿着纵向轴线从叶片根部延伸到叶片尖端，并且在叶片尖端处具有护罩段。 护罩部分与第一和第二边缘邻接抵靠相邻刀片的护罩部分以形成环形护罩。 第一和第二边缘分别在护罩段的上侧设置有相应的侧轨。 每个侧轨分为不同高度和/或宽度的部分。
-
公开(公告)号：US08632309B2
公开(公告)日：2014-01-21
申请号：US13091605
申请日：2011-04-21
IPC分类号： F01D5/14
CPC分类号： F01D5/225 , F05B2240/33
摘要： A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
摘要翻译： 公开了一种用于燃气涡轮机的叶片，其包括翼型件，该翼型件沿着纵向轴线从叶片根部延伸到叶片尖端，并且在叶片尖端处具有护罩段。 护罩部分与第一和第二边缘邻接抵靠相邻刀片的护罩部分以形成环形护罩。 第一和第二边缘分别在护罩段的上侧设置有相应的侧轨。 每个侧轨分为不同高度和/或宽度的部分。
-
公开(公告)号：US08371808B2
公开(公告)日：2013-02-12
申请号：US12617310
申请日：2009-11-12
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , B22C9/043 , F05D2230/21 , F05D2230/211 , F05D2240/40 , Y02T50/671 , Y02T50/673
摘要： Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud.
摘要翻译： 提供了一种工业燃气轮机多叶片段，其可以使用蜡模式法一体铸造。 多叶片段包括一个平台; 从平台径向延伸的至少三个翼型件，具有组合的翼型体积，弦长和翼型件厚度; 以及具有护罩体积的护罩，其设置在径向远离平台的所述翼型件的端部上。 护罩体积与组合的翼型体积的比值定义第一比例，而多叶片段具有大于或等于1.4:1的第一比例。 该比率使得在浇铸之前优先凝固翼片前的翼型件。
-
4.发明授权公开(公告)号：US08382433B2
公开(公告)日：2013-02-26
申请号：US13113630
申请日：2011-05-23
申请人： Brian Kenneth Wardle , Beat Von Arx
发明人： Brian Kenneth Wardle , Beat Von Arx
CPC分类号： F01D5/187 , B22C9/04 , B22C9/108 , F05D2230/21 , Y10T29/49243 , Y10T29/49245
摘要： A method is provided for producing a blade, by casting, for a gas turbine. The blade includes an elongate airfoil which extends in a blade longitudinal direction, merges into a blade root at the lower end, has a shroud segment at the blade tip and is pervaded by a single cooling air channel running in the blade longitudinal direction from the blade root to the blade tip. The method includes, during the casting of the blade, the blade material being fed exclusively from the blade root into the mold provided therefor, and the cooling air channel is formed during the casting of the blade by using a single core body, which is provided, at the blade tip, with a local casting cross section increasing element.
摘要翻译： 提供了一种用于通过铸造生产用于燃气轮机的叶片的方法。 叶片包括沿叶片纵向方向延伸的细长翼型件，在下端处并入叶片根部，在叶片尖端处具有护罩段，并且由叶片纵向方向上从叶片延伸的单个冷却空气通道渗出 根到叶片尖端。 该方法包括在刀片铸造过程中，将刀片材料从叶片根部单独供给到为其提供的模具中，并且通过使用单个芯体在铸造刀片期间形成冷却空气通道，所述单个芯体 ，在叶片尖端处，具有局部铸造截面增加元件。
-
公开(公告)号：US08231349B2
公开(公告)日：2012-07-31
申请号：US12400035
申请日：2009-03-20
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/676
摘要： A turbine component (25) includes a root (21), a tip (22), and an airfoil portion (7) having a leading and a trailing edge (8,9), an external suction side and pressure side wall (13, 14) between the leading and trailing edge. The walls enclose a central cavity (1-6) for the passage of cooling air, the cavity being partitioned into a leading edge- and a trailing edge region (7a, 7b) by at least one longitudinally extending first web (15) connecting the suction side wall with the pressure side wall and a second longitudinally extending web (16), connecting the first web with the suction side wall, thereby defining a first and second entry chamber (2, 3). The first web (15) is provided with at least one cross-over hole (H1) between the first entry chamber and the leading edge chamber (1), whereas the second web has no openings.
摘要翻译： 涡轮机部件（25）包括根部（21），尖端（22）和具有前缘和后缘（8,9）的翼型部分（7），外部吸力侧和压力侧壁（13， 14）在前缘和后缘之间。 壁围绕中心腔（1-6）以通过冷却空气，空腔通过至少一个纵向延伸的第一腹板（15）分隔成前缘区域和后缘区域（7a，7b），第一腹板（15）连接 吸力侧壁与压力侧壁和第二纵向延伸腹板（16）连接，第一腹板与吸力侧壁连接，由此限定第一和第二入口腔室（2,3）。 第一腹板（15）在第一进入室和前缘室（1）之间设置有至少一个交叉孔（H1），而第二腹板没有开口。
-
公开(公告)号：US08721281B2
公开(公告)日：2014-05-13
申请号：US13193548
申请日：2011-07-28
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2260/2212
摘要： A cooled blade for a gas turbine includes a blade airfoil extending between leading and trailing edges in a flow direction and on suction and pressure sides is delimited by a wall, which include an interior space in which cooling air flows towards the trailing edge in the flow direction and discharges to the outside in the region of the trailing edge. The pressure-side wall terminates at a distance in front of the trailing edge in the flow direction, forming a pressure-side lip, such that the cooling air discharges from the interior space on the pressure side. Multiple ribs subdivides the interior space, parallel to the flow direction, into a plurality of parallel cooling passages which create a high pressure drop and in which turbulators are arranged for increasing cooling. Before the outlet, multiple flow barriers are provided in the cooling air flow path, distributed transversely to the flow direction.
摘要翻译： 用于燃气涡轮机的冷却叶片包括沿流动方向在前缘和后缘之间延伸的叶片翼型件，并且在抽吸和压力侧面由壁限定，所述壁包括内部空间，冷却空气朝向流动中的后缘流动 方向并在后缘的区域中排出到外部。 压力侧壁在流动方向上在后缘前方的距离处终止，形成压力侧唇缘，使得冷却空气从压力侧的内部空间排出。 多个肋部将平行于流动方向的内部空间细分成多个平行的冷却通道，其产生高压降，并且其中布置有用于增加冷却的湍流器。 在出口之前，在冷却空气流路中设置有多个流动阻挡层，横向于流动方向分布。
-
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。
-
公开(公告)号：US20100254824A1
公开(公告)日：2010-10-07
申请号：US12400035
申请日：2009-03-20
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/676
摘要： A turbine component (25) includes a root (21), a tip (22), and an airfoil portion (7) having a leading and a trailing edge (8,9), an external suction side and pressure side wall (13, 14) between the leading and trailing edge. The walls enclose a central cavity (1-6) for the passage of cooling air, the cavity being partitioned into a leading edge- and a trailing edge region (7a, 7b) by at least one longitudinally extending first web (15) connecting the suction side wall with the pressure side wall and a second longitudinally extending web (16), connecting the first web with the suction side wall, thereby defining a first and second entry chamber (2, 3). The first web (15) is provided with at least one cross-over hole (H1) between the first entry chamber and the leading edge chamber (1), whereas the second web has no openings.
摘要翻译： 涡轮机部件（25）包括根部（21），尖端（22）和具有前缘和后缘（8,9）的翼型部分（7），外部吸力侧和压力侧壁（13， 14）在前缘和后缘之间。 壁围绕中心腔（1-6）以通过冷却空气，空腔通过至少一个纵向延伸的第一腹板（15）分隔成前缘区域和后缘区域（7a，7b），第一腹板（15）连接 吸力侧壁与压力侧壁和第二纵向延伸腹板（16）连接，第一腹板与吸力侧壁连接，由此限定第一和第二入口腔室（2,3）。 第一腹板（15）在第一进入室和前缘室（1）之间设置有至少一个交叉孔（H1），而第二腹板没有开口。
-
公开(公告)号：US09051838B2
公开(公告)日：2015-06-09
申请号：US13330919
申请日：2011-12-20
CPC分类号： F01D5/081 , F01D5/087 , F01D5/188 , Y10T29/49341
摘要： A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.
摘要翻译： 轴向涡轮机的涡轮机叶片包括内部冷却流体通道，其具有连接到叶片根部中的孔的径向向外延伸的通道。 这些孔通常是在铸造过程中提供对芯的稳定性的核心打印输出，但是不需要并且需要关闭以保证冷却系统的功能。 这通过至少一个覆盖板来实现。 该板由位于涡轮叶片根部处的至少两个槽保持。 因此，位于根部处的用于冷却流体的供应孔由简单的机械装置例如不需要随后的钎焊/焊接操作的板封闭。 此外，该板是可拆卸的，以方便检查/清洁，或在维修间隔进一步处理叶片。
-
公开(公告)号：US08459934B2
公开(公告)日：2013-06-11
申请号：US12888564
申请日：2010-09-23
CPC分类号： F01D5/147 , F01D5/187 , F01D9/041 , F05D2220/3215 , F05D2230/21 , F05D2240/301 , F05D2250/185 , F05D2260/22141
摘要： A guide blade for a gas turbine includes an inner and an outer platform, an airfoil extending in a radial direction between the inner and the outer platforms and having a height in the radial direction, and at least one cooling channel disposed in an interior of the airfoil and configured to receive a cooling medium flowing through the at least one cooling channel configured to cool the guide blade, wherein a cross-sectional area of a blade material of the airfoil varies over the height.
摘要翻译： 用于燃气轮机的引导叶片包括内平台和外平台，在内平台和外平台之间沿径向方向延伸并且具有径向高度的翼型件和设置在内平台内的至少一个冷却通道 翼型件并且构造成接收流过构造成冷却导向叶片的至少一个冷却通道的冷却介质，其中翼型件的叶片材料的横截面面积在高度上变化。
-
-
-
-
-
-
-
-
-
搜索结果
12 条记录 (耗时 0.022 秒)
