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

US20080247867A1 GAP SEAL IN BLADES OF A TURBOMACHINE 有权
标题翻译： GAP密封在涡轮机的叶片
公开(公告)号：US20080247867A1
公开(公告)日：2008-10-09
申请号：US12057506
申请日：2008-03-28
申请人： Thomas Heinz-Schwarzmaier , Sven Olmes , Ronald Wifling
发明人： Thomas Heinz-Schwarzmaier , Sven Olmes , Ronald Wifling
IPC分类号： F01D11/00
CPC分类号： F01D11/008
摘要： A gap seal (9) radially seals a gap (8) which extends axially and radially between two blades (1, 2) of a turbomachine which are adjacent in the circumferential direction (3). The two blades (1, 2) have, in each case, an axially extending longitudinal slot (10, 11), which is open towards the gap (8), on its respective blade root (6, 7). A band-form or strip-form sealing element (12) engages with its longitudinal sides (13, 14) in the two longitudinal slots (10, 11) and bridges the gap (8). The one blade (1) has a projection (15) on its blade root (6), which projects from the blade root (6) in the circumferential direction (3) and extends in the circumferential direction (3) and radially, at least in the region of the respective longitudinal slot (10), and bridges an axial longitudinal end of the gap (8) in the process. The other blade (2) has a step-shaped recess (16) on its blade root (7), complementary to the projection (15) of the one blade (1) and in which the projection engages. The projection (15) has a transverse slot (17) which extends in the circumferential direction (3) and is open towards the gap (8). The sealing element (12) engages with an end face (18) in the transverse slot (17).
摘要翻译：间隙密封件（9）径向密封在圆周方向（3）上相邻的涡轮机的两个叶片（1,2）之间轴向和径向延伸的间隙（8）。在每种情况下，两个叶片（1,2）在其相应的叶片根部（6,7）上具有朝向间隙（8）开口的轴向延伸的纵向槽（10,11）。带状或带状密封元件（12）与两个纵向狭槽（10,11）中的纵向侧面（13,14）接合并桥接间隙（8）。一个叶片（1）在其叶片根部（6）上具有在叶片根部（6）沿圆周方向（3）突出并且在周向（3）上径向延伸的突起（15），至少在相应的纵向狭槽（10）的区域中，并且在该过程中桥接间隙（8）的轴向纵向端部。另一个叶片（2）在其叶片根部（7）上具有与所述一个叶片（1）的突出部（15）互补并且突起接合的台阶形凹部（16）。突起（15）具有沿圆周方向（3）延伸并且朝向间隙（8）打开的横向槽（17）。密封元件（12）与横向槽（17）中的端面（18）接合。

2. 发明授权

US08353663B2 Shroud seal segments arrangement in a gas turbine 有权
标题翻译：护罩密封段布置在燃气轮机中
公开(公告)号：US08353663B2
公开(公告)日：2013-01-15
申请号：US13011203
申请日：2011-01-21
申请人： Tanguy Arzel , Thomas Heinz-Schwarzmaier , Martin Schnieder
发明人： Tanguy Arzel , Thomas Heinz-Schwarzmaier , Martin Schnieder
IPC分类号： F04D29/38
CPC分类号： F01D11/24 , F01D5/08 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.
摘要翻译：提供了一种燃气轮机，其包括能够绕轴线旋转并且配备有转子叶片的转子，并且由配置有定子叶片的壳体一定距离同心地封闭，该壳体形成环形的热气体通道。具有定子叶片和转子叶片的环以轴向交替排列。在相邻的定子叶片之间，布置有隔热板段，其在转子叶片的区域中限定外部的热气体通道，并且通过来自外部环形空腔的冷却介质流入隔热板段的冲击冷却来冷却。

3. 发明授权

US08303257B2 Shiplap arrangement 有权
标题翻译： Shiplap安排
公开(公告)号：US08303257B2
公开(公告)日：2012-11-06
申请号：US12572034
申请日：2009-10-01
申请人： Thomas Heinz-Schwarzmaier , Ulrich Rathmann , Carlos Simon-Delgado
发明人： Thomas Heinz-Schwarzmaier , Ulrich Rathmann , Carlos Simon-Delgado
IPC分类号： F01D11/02 , F01D5/22
CPC分类号： F01D11/02 , F01D11/005 , F01D11/04 , F05D2240/57
摘要： An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal.
摘要翻译：描述了涡轮机中的叶片排中的叶片元件之间的布置。每个叶片元件具有至少一个护罩元件和叶片翼型件，其抵靠并连接到护罩元件，并且基本上相对于叶片排的主轴线径向延伸。当安装时，沿周向延伸的护罩元件侧邻接在相邻的相邻叶片元件的相邻的护罩元件上，每个形成基本上径向的间隙。至少一个叶片元件具有突出部，其突出到邻接叶片元件的护罩元件中并沿周向延伸，并且至少一个叶片元件具有容纳这种突起的凹部。在突起或凹槽的区域中，存在径向间隙的台阶区域，并且在该阶梯区域中的径向间隙的引导是迷宫式密封。

4. 发明申请

US20120020787A1 COOLED BLADE FOR A GAS TURBINE 有权
标题翻译：用于气体涡轮的冷却叶片
公开(公告)号：US20120020787A1
公开(公告)日：2012-01-26
申请号：US13193548
申请日：2011-07-28
申请人： Jörg KRÜCKELS , Thomas HEINZ-SCHWARZMAIER , Brian Kenneth WARDLE
发明人： Jörg KRÜCKELS , Thomas HEINZ-SCHWARZMAIER , Brian Kenneth WARDLE
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。

5. 发明申请

US20100119371A1 SHIPLAP ARRANGEMENT 有权
标题翻译：船舶安排
公开(公告)号：US20100119371A1
公开(公告)日：2010-05-13
申请号：US12572034
申请日：2009-10-01
申请人： Thomas Heinz-Schwarzmaier , Ulrich Rathmann , Carlos Simon-Delgado
发明人： Thomas Heinz-Schwarzmaier , Ulrich Rathmann , Carlos Simon-Delgado
IPC分类号： F01D5/22
CPC分类号： F01D11/02 , F01D11/005 , F01D11/04 , F05D2240/57
摘要： An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal.
摘要翻译：描述了涡轮机中的叶片排中的叶片元件之间的布置。每个叶片元件具有至少一个护罩元件和叶片翼型件，其抵靠并连接到护罩元件，并且基本上相对于叶片排的主轴线径向延伸。当安装时，沿周向延伸的护罩元件侧邻接在相邻的相邻叶片元件的相邻的护罩元件上，每个形成基本上径向的间隙。至少一个叶片元件具有突出部，其突出到邻接叶片元件的护罩元件中并沿周向延伸，并且至少一个叶片元件具有容纳这种突起的凹部。在突起或凹槽的区域中，存在径向间隙的台阶区域，并且在该阶梯区域中的径向间隙的引导是迷宫式密封。

6. 发明授权

US08721281B2 Cooled blade for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片
公开(公告)号：US08721281B2
公开(公告)日：2014-05-13
申请号：US13193548
申请日：2011-07-28
申请人： Jörg Krückels , Thomas Heinz-Schwarzmaier , Brian Kenneth Wardle
发明人： Jörg Krückels , Thomas Heinz-Schwarzmaier , Brian Kenneth Wardle
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。

7. 发明授权

US08534675B2 Strip seal and method for designing a strip seal 有权
标题翻译：带状密封和设计带状密封的方法
公开(公告)号：US08534675B2
公开(公告)日：2013-09-17
申请号：US12694765
申请日：2010-01-27
申请人： Thomas Heinz-Schwarzmaier , Ulrich Steiger , Ulrich Rathmann
发明人： Thomas Heinz-Schwarzmaier , Ulrich Steiger , Ulrich Rathmann
IPC分类号： F16J3/00
CPC分类号： F01D11/005 , F01D25/04 , F05D2240/11 , F05D2240/57 , F05D2260/96 , F05D2300/501
摘要： A strip seal and method of configuration thereof for sealing two adjacent non-rotating gas turbine hot gas components exposed to pressure pulsations. The strip seal has at least two clamping projections distributed along discrete points of the strip seal length that extend out from a pressure face of the strip seal. The location of the projections are defined by two ratios. The first ratio, of less than 25, is the strip seal length extending free of clamping projections from any one of the ends of the strip seal to a clamping projection to the ratio of strip seal thickness. The second ratio, of less than 200, is the ratio of the strip seal length extending free of clamping projections between any two projections to the thickness of the strip seal. This seal arrangement ameliorates detrimental effects of induced resonance.
摘要翻译：一种带状密封件及其构造方法，用于密封暴露于压力脉动的两个相邻的非旋转燃气轮机热气体组件。带状密封件具有沿带状密封件长度的离散点分布的至少两个夹紧突起，其从带状密封件的压力表面延伸出来。突起的位置由两个比例定义。小于25的第一比率是从带状密封件的任何一个端部延伸到没有夹紧突起的条形密封长度到夹紧突起到条形密封件厚度的比率。小于200的第二比率是在任何两个突起之间没有夹紧突起的条形密封长度与带状密封件的厚度之间的比率。该密封装置改善了诱导共振的有害影响。

8. 发明授权

US08043050B2 Gap seal in blades of a turbomachine 有权
标题翻译：涡轮机刀片间隙密封
公开(公告)号：US08043050B2
公开(公告)日：2011-10-25
申请号：US12057506
申请日：2008-03-28
申请人： Thomas Heinz-Schwarzmaier , Sven Olmes , Ronald Wifling
发明人： Thomas Heinz-Schwarzmaier , Sven Olmes , Ronald Wifling
IPC分类号： F01D1/00
CPC分类号： F01D11/008
摘要： A gap seal (9) radially seals a gap (8) which extends axially and radially between two blades (1, 2) of a turbomachine which are adjacent in the circumferential direction (3). The two blades (1, 2) have, in each case, an axially extending longitudinal slot (10, 11), which is open towards the gap (8), on its respective blade root (6, 7). A band-form or strip-form sealing element (12) engages with its longitudinal sides (13, 14) in the two longitudinal slots (10, 11) and bridges the gap (8). The one blade (1) has a projection (15) on its blade root (6), which projects from the blade root (6) in the circumferential direction (3) and extends in the circumferential direction (3) and radially, at least in the region of the respective longitudinal slot (10), and bridges an axial longitudinal end of the gap (8) in the process. The other blade (2) has a step-shaped recess (16) on its blade root (7), complementary to the projection (15) of the one blade (1) and in which the projection engages. The projection (15) has a transverse slot (17) which extends in the circumferential direction (3) and is open towards the gap (8). The sealing element (12) engages with an end face (18) in the transverse slot (17).
摘要翻译：间隙密封件（9）径向密封在圆周方向（3）上相邻的涡轮机的两个叶片（1,2）之间轴向和径向延伸的间隙（8）。在每种情况下，两个叶片（1,2）在其相应的叶片根部（6,7）上具有朝向间隙（8）开口的轴向延伸的纵向槽（10,11）。带状或带状密封元件（12）与两个纵向狭槽（10,11）中的纵向侧面（13,14）接合并桥接间隙（8）。一个叶片（1）在其叶片根部（6）上具有在叶片根部（6）沿圆周方向（3）突出并且在周向（3）上径向延伸的突起（15），至少在相应的纵向狭槽（10）的区域中，并且在该过程中桥接间隙（8）的轴向纵向端部。另一个叶片（2）在其叶片根部（7）上具有与所述一个叶片（1）的突出部（15）互补并且突起接合的台阶形凹部（16）。突起（15）具有沿圆周方向（3）延伸并且朝向间隙（8）打开的横向槽（17）。密封元件（12）与横向槽（17）中的端面（18）接合。

9. 发明申请

US20110171039A1 BLADE ARRANGEMENT OF A GAS TURBINE 审中-公开
标题翻译：气体涡轮叶片布置
公开(公告)号：US20110171039A1
公开(公告)日：2011-07-14
申请号：US13024545
申请日：2011-02-10
申请人： Thomas HEINZ-SCHWARZMAIER , Thomas DUDA , Alexander SCHNELL
发明人： Thomas HEINZ-SCHWARZMAIER , Thomas DUDA , Alexander SCHNELL
IPC分类号： F01D5/18
CPC分类号： F01D11/122 , F01D5/288 , F01D11/14
摘要： A blade arrangement of a gas turbine, with at least one blade which in the radial direction projects into a hot gas passage arranged concentrically to an axis, and terminates in a blade tip which with a clearance lies opposite a heat shield which delimits the hot gas passage. The blade and the heat shield are movable in relation to each other in the circumferential direction, and the blade tip and the heat shield are covered with coatings, which enable a directed cutting of the blade tip into the heat shield. By such a blade arrangement, a reduction of the clearance as a result of cutting in is simply achieved by the heat shield having a porous thermal barrier coating as an outer, abradable coating, and by the blade tip being provided with a homogenous, metallic cover coating.
摘要翻译：一种燃气轮机的叶片装置，其具有至少一个叶片，其沿径向突出到与轴线同心设置的热气体通道中，并且终止于叶片尖端，其间隙与限定热气体的隔热罩相对通道。叶片和隔热罩可在圆周方向上相对移动，并且叶片尖端和隔热罩覆盖有涂层，从而能够将叶片尖端定向切割成隔热层。通过这样的叶片装置，通过具有作为外部可磨损涂层的多孔隔热涂层的隔热罩简单地实现由于切割而导致的间隙减小，并且通过叶片尖端设置有均匀的金属盖涂层。

10. 发明申请

US20110171013A1 SHROUD SEAL SEGMENTS ARRANGEMENT IN A GAS TURBINE 有权
标题翻译： SHROUD在气体涡轮机中的密封部分安装
公开(公告)号：US20110171013A1
公开(公告)日：2011-07-14
申请号：US13011203
申请日：2011-01-21
申请人： Tanguy ARZEL , Thomas HEINZ-SCHWARZMAIER , Martin SCHNIEDER
发明人： Tanguy ARZEL , Thomas HEINZ-SCHWARZMAIER , Martin SCHNIEDER
IPC分类号： F01D5/08
CPC分类号： F01D11/24 , F01D5/08 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.
摘要翻译：提供了一种燃气轮机，其包括能够绕轴线旋转并且配备有转子叶片的转子，并且由配置有定子叶片的壳体一定距离同心地封闭，该壳体形成环形的热气体通道。具有定子叶片和转子叶片的环以轴向交替排列。在相邻的定子叶片之间，布置有隔热板段，其在转子叶片的区域中限定外部的热气体通道，并且通过来自外部环形空腔的冷却介质流入隔热板段的冲击冷却来冷却。

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