-
公开(公告)号：US20020090295A1
公开(公告)日：2002-07-11
申请号：US09998668
申请日：2001-12-03
IPC分类号： F01D009/06
CPC分类号： F01D25/12 , F01D5/186 , F05D2240/81 , Y10S415/914
摘要： In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.
摘要翻译： 在用于燃气轮机的冷却结构中，冷却空气扩散孔由平台的内表面到外表面形成，以便从邻近的低压侧叶片表面的方向偏移的活动叶片的高压侧叶片表面打开 在主流动方向上面对高压侧叶片表面的动叶片。
-
公开(公告)号：US20020098079A1
公开(公告)日：2002-07-25
申请号：US09998201
申请日：2001-12-03
发明人： Tatsuaki Fujikawa , Yasuoki Tomita , Shunsuke Torii , Ryotaro Magoshi , Masamitsu Kuwabara , Shinichi Inoue
IPC分类号： F01D011/24
CPC分类号： F01D11/08 , F01D9/00 , F01D11/18 , F05D2250/181 , F05D2250/282 , F05D2260/201 , F05D2260/30
摘要： In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than that of the circumferential rib are, respectively, formed in plural lines, so that it is possible to suppress heat deformation in the axial direction which largely contributes to reduction of the tip clearance compared to head deformation in the circumferential direction more efficiently.
摘要翻译： 在燃气轮机分割环中，在两个机舱附接凸缘之间的外周面1b上，沿圆周方向延伸的周向肋和沿轴向延伸并且具有比周向肋高的高度的轴向肋是 分别形成为多条线，从而可以更有效地抑制与圆周方向上的头部变形相比大大有助于减小顶端间隙的轴向热变形。
-
公开(公告)号：US20030012647A1
公开(公告)日：2003-01-16
申请号：US10189413
申请日：2002-07-08
IPC分类号： F01D001/02
CPC分类号： F01D11/005 , B23K26/389 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/80 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.
摘要翻译： 燃气轮机固定叶片包括设置有用于冷却空气的通道的固定叶片部分，用于在冷却空气的排出口的侧面支撑固定叶片部分的内护罩，以及多个部分，每个部分包括在 至少一个固定叶片部分和至少一个内部护罩。 流动通道从冷却空气的排出口被拉出，并且流动通道被引入内护罩的前边缘角部并且沿内护罩的侧边缘向后延伸。
-
公开(公告)号：US20040009059A1
公开(公告)日：2004-01-15
申请号：US10191448
申请日：2002-07-10
IPC分类号： F01D009/04
摘要： A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direction of the gas turbine. A concave portion is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.
摘要翻译： 燃气轮机的固定叶片，其可以降低在固定叶片的内护罩的后边缘附近的部分产生的热应力。 固定叶片沿着燃气轮机的轴向方向定位成与活动叶片盘中的至少一个相邻。 在内护罩中设置有凹部，使得凹部形成在内护罩的后缘附近和内护罩的内周面附近，在内罩的内周面上， 面向移动刀片盘的旋转轴的周边面; 并且在内护罩的后边缘处形成有朝向旋转轴突出的突出部。
-
公开(公告)号：US20020090296A1
公开(公告)日：2002-07-11
申请号：US10025593
申请日：2001-12-26
发明人： Masamitsu Kuwabara , Yoshiyuki Morii , Yasuoki Tomita , Shunsuke Torii , Shigehiro Shiozaki , Kotaro Ohshima , Tatsuaki Fujikawa , Ryotaro Magoshi , Shinichi Inoue
IPC分类号： F01D011/00
CPC分类号： F01D11/005 , F01D11/006 , F01D11/008
摘要： The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.
摘要翻译： 分隔壁由多个分隔壁部分构成，形成高温气体的通道壁，其沿着叶片的排列方向连接以形成整个具有大致圆形横截面的壁表面， 结构，用于防止高温气体从形成在高温气体的流动方向上的分隔壁部分之间的连接部分处的间隙从间隙中的高温气体的上游侧的开口或气流 限制结构用于防止高温气体包围在间隙中，例如，形成为具有作为整体的T形横截面的棱镜的密封构件由作为密封部分的平面部分和用于填充的突出部分组成 提供了差距。
-
6.发明申请Method for managing lifespans of high temperature gas turbine components and its implementation through computer program 审中-公开管理高温燃气轮机组件寿命的方法及其通过计算机程序实现公开(公告)号：US20040073400A1
公开(公告)日：2004-04-15
申请号：US10268957
申请日：2002-10-11
发明人： Yasuoki Tomita , Masamitsu Kuwabara , Junichiro Masada , Friedrich Soechting , Vinod Kallianpur , Jun-Hee Lee
IPC分类号： G06F015/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/11
摘要： It provides a method for managing the remaining life of a high temperature component used in a gas turbine that enables a state of fatigue of a high temperature component to be evaluated and controlled with a high level of accuracy, and a program medium for performing the method for managing the remaining life of a high temperature gas turbine component on a computer. In the method for managing the lifespan of a high temperature component used in a gas turbine, the lifespan of a high temperature component being evaluated is set within an operating area bounded by a component life limit line that is determined on the basis of field data giving the correlation between the operating time and operating cycles for the state of fatigue from past high temperature components. As the program medium, a medium is employed that is provided with a program in which this method is used for managing a lifespan of a high temperature component used in a gas turbine.
摘要翻译： 它提供了一种用于管理燃气轮机中使用的高温部件的剩余寿命的方法，其能够高精度地评估和控制高温部件的疲劳状态，以及用于执行该方法的程序介质 用于管理计算机上的高温燃气轮机部件的剩余寿命。 在用于管理燃气轮机中使用的高温部件的使用寿命的方法中，被评估的高温部件的寿命被设定在由基于现场数据给出的部件寿命限制线所限定的操作区域内 过去高温部件的疲劳状态的运行时间和运行周期之间的相关性。 作为程序介质，使用具有该方法用于管理在燃气轮机中使用的高温部件的寿命的程序的介质。
-
公开(公告)号：US20040018082A1
公开(公告)日：2004-01-29
申请号：US10202654
申请日：2002-07-25
IPC分类号： F01D009/06
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/81 , F05D2260/201
摘要： A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooling air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.
摘要翻译： 具有多个小孔的碰撞板以与内罩的底面间隔设置形成室，将冷却空气从小孔引导到室内。 前缘流路沿着宽度方向设置在前缘侧并引入冷却空气。 侧流路设置在内护罩的两侧，并将冷却空气引导到后缘侧。 沿着后缘附近的宽度方向形成头部，并且从侧流路引导冷却空气。 多个后缘流动路径沿着宽度方向间隔地形成在后缘侧，每个流动路径的一端连接到集管，另一端在后缘开口，并且集管中的冷却空气 从后缘弹出。
-
公开(公告)号：US20040009066A1
公开(公告)日：2004-01-15
申请号：US10192676
申请日：2002-07-11
IPC分类号： F01D005/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/189 , F05D2250/70 , F05D2260/202
摘要： A turbine blade applicable to a gas turbine has a turbine blade body having film cooling holes, the interior space of which is partitioned into two cavities by a rib. Hollow inserts each having impingement holes are respectively arranged in the cavities to form cooling spaces therebetween. Communication is ensured between the cavities by a communication means, so that the impingement cooling is interrupted with respect to the prescribed side having a good heat transmission in the turbine blade body. A partition wall is further arranged between the rib and the insert arranged in the trailing-edge side, thus providing a separation between the cooling spaces respectively arranged in the rear side and front side. Thus, it is possible to noticeably reduce the amount of cooling air in the turbine blade body; and it is possible to reduce temperature differences entirely over the turbine blade body as small as possible.
摘要翻译： 适用于燃气轮机的涡轮叶片具有涡轮叶片体，其具有膜冷却孔，其内部空间通过肋分隔成两个空腔。 各个具有冲击孔的中空插入件分别设置在空腔中，以在它们之间形成冷却空间。 通过连通装置确保空腔之间的通信，使得冲击冷却相对于在涡轮机叶片体中具有良好的热传递的规定侧被中断。 分隔壁还布置在布置在后缘侧的肋和插入件之间，从而在分别布置在后侧和前侧的冷却空间之间分开。 因此，可以显着地减少涡轮叶片体内的冷却空气量; 并且可以尽可能小地将涡轮叶片体上的温差完全降低。
-
公开(公告)号：US20020106276A1
公开(公告)日：2002-08-08
申请号：US10025533
申请日：2001-12-26
IPC分类号： F01D005/20
CPC分类号： F01D5/225 , F01D11/001 , F01D11/005
摘要： A base plate and honeycomb member disposed at the inner circumference side of an inside shroud are fixed to the inside shroud, at a phase deviation in the peripheral direction, with respect to the inside shroud, so as to plug the missing range of seal member, out of gaps between adjacent inside shrouds, and therefore leak of purge air from the missing range of seal member is prevented without adding new constituent members.
摘要翻译： 设置在内侧护罩的内周侧的基板和蜂窝构件相对于内侧护罩以周向的相位偏移固定在内侧护罩上，从而堵塞密封构件的缺失范围， 在相邻的内部护罩之间的间隙之外，因此防止了来自密封构件的缺失范围的吹扫空气的泄漏，而不添加新的构成构件。
-
-
-
-
-
-
-
-
搜索结果
9 条记录 (耗时 0.018 秒)
