-
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。
-
2.发明申请Turbine blade fatigue life evaluating method, turbine blade creep elongation strain measuring apparatus, and turbine blade 有权涡轮叶片疲劳寿命评估方法，涡轮叶片蠕变伸长应变测量装置和涡轮叶片公开(公告)号：US20040139809A1
公开(公告)日：2004-07-22
申请号：US10635494
申请日：2003-08-07
IPC分类号： G01B005/30 , G01M013/00 , G01B005/16 , F01D005/12
CPC分类号： G01B5/205 , F01D21/003 , F05D2260/80 , F05D2270/11 , G01B5/30 , G01M13/00
摘要： In order to provide a turbine blade fatigue life evaluating method for quantitively evaluating the fatigue life of a turbine blade, the turbine blade is determined to be within its fatigue life if the creep elongation strain in the longitudinal direction of the turbine blade is less than 0.5% of an initial length, and is determined to exceed its fatigue life if the creep elongation strain is 0.5% or more than the initial length. A turbine blade creep elongation strain measuring apparatus 20 comprises a first fixed end 21, a second fixed end 22, and a dial gauge 24. A dimension in the longitudinal direction is stamped on the surface of a turbine blade.
摘要翻译： 为了提供一种用于定量评估涡轮机叶片的疲劳寿命的涡轮叶片疲劳寿命评估方法，如果涡轮叶片的纵向上的蠕变伸长应变小于0.5，则涡轮叶片被确定在其疲劳寿命内 如果蠕变伸长应变为初始长度的0.5％或更大，则确定其超过其疲劳寿命。 涡轮叶片蠕变伸长应变测量装置20包括第一固定端21，第二固定端22和千分表24.在涡轮叶片的表面上冲压沿纵向的尺寸。
-
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：US20040096328A1
公开(公告)日：2004-05-20
申请号：US10299711
申请日：2002-11-20
IPC分类号： F01D005/18
CPC分类号： F01D5/187 , F01D5/20 , F01D11/122 , F05D2250/292 , F05D2260/201
摘要： Holes 38 and 39 have upstream opening portions 38b and 39b and downstream opening portions 38a and 39a which have a larger cross-sectional area than upstream opening portions 38b and 39b, and are formed at top portion TP of each moving blade. Holes 38 and 39 have tapered shapes T1 and T2 or step portions, and preferably, downstream opening portions 38a and 39a are eccentrically formed toward the moving direction. When tip squealer 37 is formed, hole 38 is formed so that its opening portion is provided at the side surface of tip squealer 37. Without covering the holes for cooling which are formed at the top portion of the turbine blade due to rubbing or the like, the turbine blade is accurately cooled and stably driven.
摘要翻译： 孔38,39具有比上游侧开口部38b，39b大的截面积的上游侧开口部38b，39b以及下游侧开口部38a，39a，形成在各动作叶片的顶部TP。 孔38和39具有锥形T 1和T 2或台阶部分，并且优选地，下游开口部分38a和39a朝向移动方向偏心地形成。 当形成尖端尖叫器37时，形成孔38，使得其开口部分设置在尖端尖叫器37的侧表面。不覆盖由于摩擦等而形成在涡轮叶片的顶部的用于冷却的孔 ，涡轮叶片被精确地冷却和稳定地驱动。
-
公开(公告)号：US20040047725A1
公开(公告)日：2004-03-11
申请号：US10235825
申请日：2002-09-06
发明人： Yasuoki Tomita , Osamu Isumi , Shinichi Inoue , Friedrich Soechting , Vincent Laurello , Hiroshige Matsuoka
IPC分类号： F01D011/08
CPC分类号： F01D25/12 , F01D11/005 , F01D11/08 , F01D25/246 , F05D2240/55 , F05D2260/201
摘要： An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidization is prevented, and high temperature deformation is prevented. In order to achieve the object, the present invention provides a ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades comprising a plurality of individual units which define an annular form by being arranged around the peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from the tips of the moving blades, wherein grooves which extends along the axial direction of the main shaft of the turbine are formed upon of the individual units so as mutually to confront one another; a seal plate which is inserted into each mutually confronting pair of the grooves so as to connect together the adjacent pair of individual units; and contact surfaces which are formed at positions more radially inward than the seal plates, which extend in the axial direction and the peripheral direction and which mutually contact one another.
摘要翻译： 本发明的目的是提供一种燃气轮机的环状部分，其中温度保持较低，防止了由高温氧化引起的损伤，并且防止了高温变形。 为了实现该目的，本发明提供了一种燃气轮机的环形段，其包括叶片环，主轴和包括多个独立单元的活动叶片，所述多个单独的单元通过围绕 主轴，并且配置成使得其内周面与动叶片的前端保持恒定的距离，其中沿着涡轮主轴的轴向延伸的槽形成在各个单元上，以便相互 相互对抗 密封板，其插入每个相互面对的一对槽中，以将相邻的一对单独的单元连接在一起; 以及形成在比轴向和周向延伸并彼此相互接触的密封板更径向向内的位置处的接触表面。
-
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。
-
公开(公告)号：US20040146402A1
公开(公告)日：2004-07-29
申请号：US10351479
申请日：2003-01-27
IPC分类号： B63H001/14 , F01D005/08 , F01D005/18 , B63H007/02 , B64C011/00 , F03D011/02 , F04D029/58
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/22141 , Y02T50/676
摘要： The object of the present invention is to provide a turbine moving blade that has high heat resistance and can be used for a long period of time by improving the cooling efficiency of the turbine moving blade, and to improve both the thermal efficiency and operating efficiency of a gas turbine through the use of this turbine moving blade. In order to achieve the object, the present invention provide a turbine moving blade arranged in a combustion gas flow path in which a plurality of blow-out openings for blowing out a cooling medium are formed in its outer surface, wherein among a plurality of cooling medium trailing edge blow-out openings arranged from the vicinity of a blade base to the vicinity of a blade tip along a blade trailing edge of turbine moving blade, the opening area of a blade tip trailing edge blow-out opening located in the vicinity of blade tip is set to be larger than the opening area of the other trailing edge blow-out openings.
摘要翻译： 本发明的目的是提供一种具有高耐热性并可通过提高涡轮机动叶片的冷却效率而长时间使用的涡轮机动叶片，并提高热效率和操作效率 通过使用该涡轮机动叶片的燃气轮机。 为了实现该目的，本发明提供了一种设置在燃烧气体流路中的涡轮机动叶片，其中在其外表面形成有用于吹出冷却介质的多个吹出口，其中在多个冷却 从叶片底部附近到涡轮机动叶片的叶片后缘的叶片尖端附近布置的中间后缘吹出开口，位于涡轮机动叶片附近的叶片尖端后缘吹出开口的开口面积 叶片尖端被设定为大于其他后缘吹出口的开口面积。
-
公开(公告)号：US20040076511A1
公开(公告)日：2004-04-22
申请号：US10270639
申请日：2002-10-16
IPC分类号： F01D009/06
CPC分类号： F01D5/18 , F01D25/12 , Y02T50/676
摘要： One object of the present invention is to provide a gas turbine where cooling failure attributable to the occurrence of a horseshoe vortex produced in the vicinity of the stationary blades of the turbine, can be prevented. In order to achieve the object, the present invention provides a gas turbine comprising moving blades provided on a rotor side which rotate together with the rotor, and stationary blades provided on a stationary side which cover the periphery of the moving blades and form a combustion gas flow path in the interior, and which are arranged alternately with the moving blades in the rotation axis direction of the rotor, and where the stationary blades have a blade portion arranged inside the combustion gas flow path, an outside shroud provided on an outer peripheral end side of the blade portion, and an inside shroud provided on an inner peripheral end side of the blade portion, in one or both of the outside shroud and the inside shroud, corresponding to a leading edge of the blade portion, there is provided a first cooling air flow path which blows out cooling air into the combustion gas flow path, from downstream to upstream in the flow direction of the combustion gas.
摘要翻译： 本发明的一个目的是提供一种燃气轮机，其中可以防止由于在涡轮机的固定叶片附近产生的马蹄涡涡发生的冷却故障。 为了实现该目的，本发明提供一种燃气轮机，其包括设置在与转子一起旋转的转子侧的动叶片，以及设置在固定侧的固定叶片，该固定叶片覆盖动叶片的周边并形成燃烧气体 内部的流路，与所述动叶片沿所述转子的旋转轴方向交替排列，所述固定叶片具有设置在所述燃烧气体流路内部的叶片部，所述外侧罩设置在所述外周端 并且与所述叶片部的前缘对应地设置在所述叶片部的内周端侧的内侧罩中，在所述外侧护罩和所述内侧护罩中的一个或两个中，设置有第一 从燃烧气体的流动方向的下游到上游将冷却空气吹入燃烧气体流路的冷却空气流路。
-
公开(公告)号：US20020094268A1
公开(公告)日：2002-07-18
申请号：US10043201
申请日：2002-01-14
IPC分类号： F01D025/26
摘要： A split ring is disposed on an inner wall of a gas turbine casing. The split ring is composed of a plurality of split segments that are arranged on the inner wall of the casing in circumferential direction. A predetermined clearance is formed between the inner face of a split segment and the rotor blade tips. The split segments are arranged so that a predetermined circumferential clearance is formed between the split segments in order to allow the thermal expansion of the segments. A circumferential end face located upstream side of the segments with respect to the direction of the rotor blade rotation is connected to the inner face by a transition face having a surface formed as an inclined plane. The inclined plane prevents the swirl flow caused by the rotating rotor blade from impinging the upstream end face and, thereby, suppresses a temperature rise of the split segment at the upstream end face.
摘要翻译： 开口环设置在燃气轮机壳体的内壁上。 开口环由沿圆周方向配置在壳体的内壁上的多个分割段构成。 在分割段的内表面和转子叶片尖之间形成预定的间隙。 分割段被布置成使得在分割段之间形成预定的周向间隙以允许段的热膨胀。 相对于转子叶片旋转方向位于段的上游侧的周向端面通过具有形成为倾斜平面的表面的过渡面连接到内表面。 倾斜面防止旋转的转子叶片引起的涡流撞击上游端面，从而抑制上游端面处的分割段的温度上升。
-
-
-
-
-
-
-
-
-
搜索结果
17 条记录 (耗时 0.186 秒)
