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51.发明授权Continual radial loading device for steam turbine reaction type buckets and related method 失效用于蒸汽轮机反应式桶的连续径向加载装置及相关方法公开(公告)号：US06761538B2
公开(公告)日：2004-07-13
申请号：US10284390
申请日：2002-10-31
IPC分类号： F01D532
CPC分类号： F01D5/3038
摘要： A loading spring segment for radially loading a turbine bucket within a turbine rotor groove includes a substantially circular metal sheet with a gap between opposed edges of the sheet, the sheet defining an arcuate segment in an arcuate length direction of the spring segment; and a plurality of radial slots in the sheet, spaced along the arcuate length direction to thereby create a plurality of individual springs within the arcuate segment.
摘要翻译： 用于在涡轮转子槽内径向加载涡轮机叶片的加载弹簧段包括在片材的相对边缘之间具有间隙的基本上圆形的金属片，该片材限定了弹簧片段的弓形长度方向上的弧形段; 以及片材中沿着弓形长度方向间隔开的多个径向槽，从而在弓形段内形成多个单独的弹簧。
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公开(公告)号：US20020182081A1
公开(公告)日：2002-12-05
申请号：US10124428
申请日：2002-04-18
IPC分类号： F04D029/34
CPC分类号： F01D5/32 , F01D5/3038
摘要： A device for fastening a moving blade (3) to a rotor (2) of a thermal turbomachine is described. The moving blade (3) has a blade root (36), a blade leaf (32) and a platform (31) arranged between the blade root (36) and the blade leaf (32) and having at least two side flanks (33, 34). The idea, on which the invention is based, of avoiding axial forces occurring on the rotor (2) on account of bearing faces set obliquely to the rotor axis (4) between two adjacent moving blades (3) is that adjacent moving blades (3) meet solely at axially oriented bearing faces (52).
摘要翻译： 描述了用于将动叶片（3）紧固到热涡轮机的转子（2）上的装置。 活动叶片（3）具有叶片根部（36），叶片叶片（32）和布置在叶片根部（36）和叶片叶片（32）之间的平台（31），并且具有至少两个侧翼 ，34）。 本发明所基于的想法是避免由于在两个相邻的活动叶片（3）之间倾斜地设置在转子轴线（4）上的轴承面而在转子（2）上产生轴向力，所以相邻的活动叶片 ）仅在轴向定向的轴承面（52）处相遇。
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53.发明授权Methods of installing a balance weight for a rotary component in turbomachinery 有权在涡轮机械中安装旋转部件的平衡重的方法公开(公告)号：US06477916B2
公开(公告)日：2002-11-12
申请号：US09875141
申请日：2001-06-07
IPC分类号： B23P1904
CPC分类号： B25B13/48 , F01D5/027 , F01D5/3038 , F16F15/322 , Y10T29/53843 , Y10T29/5393 , Y10T409/304312 , Y10T409/30952 , Y10T464/50
摘要： A balance weight has first and second margins at right angles to one another with the second margin larger than the first margin. A balance weight groove in a rotor has outer and inner wall portions, with the outer wall portions spaced a distance less than the spacing between the inner wall portions. The balance weight has a central threaded opening receiving a screw and a driving slot in the upper face of the weight. An insertion tool is threaded to the balance weight to insert the balance weight through a turbomachinery access opening into the groove. The tool is rotated to locate the second margins below the outer wall portions of the groove. By inserting a driving tool through the insertion tool, the screw is rotated to lock the balance weight to the rotor and in the groove. Upon removal of the insertion and driving tools, a staking tool is inserted through turbine access opening to stake the balance weight and rotor and the screw and balance weight.
摘要翻译： 平衡重具有彼此成直角的第一和第二边缘，第二边缘大于第一边缘。 转子中的平衡重槽具有外壁部分和内壁部分，其中外壁部分的距离小于内壁部分之间的间隔。 平衡配重具有中心螺纹开口，该中心螺纹孔在重物的上表面接纳螺钉和驱动槽。 插入工具被螺纹连接到平衡重块，以将平衡重块通过涡轮机械进入开口插入槽中。 旋转工具以将凹槽的外壁部分之下的第二边缘定位。 通过将插入工具插入插入工具中，旋转螺钉以将平衡重锁定到转子和槽中。 在移除插入和驱动工具时，将打桩工具插入通过涡轮机进入开口以固定平衡重和转子以及螺钉并平衡重量。
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公开(公告)号：US20010055527A1
公开(公告)日：2001-12-27
申请号：US09880764
申请日：2001-06-15
IPC分类号： F01D005/32
CPC分类号： F01D5/32 , F01D5/3038
摘要： The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).
摘要翻译： 技术领域本发明涉及将叶片固定在涡轮喷气发动机转子盘（1）的通道（2）中并且包括其横截面与通道（2）的横截面相匹配的壳体（15）的锤扣式刀片锁定装置 ），还有一个锁定元件（16），其以可径向移动的方式安装在壳体（15）中的横向孔中，并部分地可部分地接纳在锁壳体（9a，9b）中;以及驱动螺栓（17），其作用在锁定元件 （16）。 锁定元件（16）包括在壳体（15）的窗口（22a）中滑动的止动件（32a）。 螺栓头（4）较大并且径向地固定在通道（2）的底部和壳体（15）的基部（20）之间。
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公开(公告)号：US20010022936A1
公开(公告)日：2001-09-20
申请号：US09790083
申请日：2001-02-21
发明人： Achim Zimmermamm
IPC分类号： F01D005/32
CPC分类号： F01D5/32 , F01D5/3038 , Y10S416/50 , Y10T29/49321
摘要： The blades (3) of a turbine of axial design are inserted into an undercut blade groove (2) of the turbine rotor (1) in a positive-locking manner and are secured by a blade lock. The blade lock comprises a mounting space (7), which is in connection with the blade groove (2) and into which a filler piece (8), which is in positive-locking relationship with the blade foot (6) of the blades (3), and a wedge (9) are inserted. The cross section of the mounting space (7) receiving the filler piece (8) is widened conically beginning from the blade groove (2). The cross section of the filler piece (8) is adapted to the cross section of the mounting space (7).
摘要翻译： 轴向设计的涡轮机的叶片（3）以正向锁定的方式插入涡轮转子（1）的底切叶片槽（2）中并且通过叶片锁固定。 叶片锁包括与叶片槽（2）连接的安装空间（7），并且与叶片的叶片脚（6）呈正向锁定关系的填充片（8） 3），并且插入楔（9）。 接收填料片（8）的安装空间（7）的横截面从叶片凹槽（2）开始锥形扩大。 填料片（8）的横截面适用于安装空间（7）的横截面。
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公开(公告)号：US20010019697A1
公开(公告)日：2001-09-06
申请号：US09794050
申请日：2001-02-28
发明人： Michael Mueller , Jorg Pross , Manfred Knorr
IPC分类号： F01D005/32
CPC分类号： F01D5/32 , F01D5/3038
摘要： The rotor blades of a turbomachine are fastened to the rotor (3) of the machine by means of blade roots (1) by the blade roots (1) being anchored in peripheral grooves (2). According to the invention, the blade roots (1) have at least one recess or opening (4), which extends in the peripheral direction and in each of which a connecting piece (5) is arranged. This connecting piece (5) connects at least two blade roots (1) to form a blade pack. By means of the connection, the blade roots (1) are secured against twisting and falling out of the peripheral groove (2). The connecting piece (5) consists of a shaped piece, which is laid with little clearance into the recess or opening (4), a displacement of a blade root (1) and of the connecting piece (5) relative to one another still being possible. The blade root of the last blade of a blade row which is assembled in a peripheral groove is locked to the adjacent blade roots by a final connecting piece.
摘要翻译： 涡轮机的转子叶片通过叶片根部（1）由固定在周边槽（2）中的叶根（1）固定到机器的转子（3）上。 根据本发明，叶片根部（1）具有至少一个沿圆周方向延伸的凹部或开口（4），并且其中每一个设置有连接件（5）。 该连接件（5）连接至少两个叶片根部（1）以形成刀片组件。 通过连接，叶片根部（1）被固定以防止扭曲并从周边凹槽（2）中掉出。 连接件（5）由成形件组成，该成形件在凹部或开口（4）中几乎没有间隙地放置，叶片根部（1）和连接件（5）相对于彼此的位移仍然是 可能。 组装在周边凹槽中的叶片排的最后一个叶片的叶根根部通过最终连接件与相邻叶片根部锁定。
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公开(公告)号：US5919032A
公开(公告)日：1999-07-06
申请号：US3635
申请日：1998-01-07
申请人： Jacky Naudet , Christophe Poy
发明人： Jacky Naudet , Christophe Poy
CPC分类号： F01D5/3038
摘要： The blades (10) of a turbine or a compressor are here fixed to the disk (1) by three roots (7, 8 and 9) inserted in the same number of circular grooves (4, 5 and 6). This assembly makes it possible to provide a good distribution of stresses during functioning.
摘要翻译： 涡轮机或压缩机的叶片（10）在这里通过插入相同数量的圆形槽（4,5和6）中的三根（7,8和9）固定在盘（1）上。 该组件使得可以在功能期间提供良好的应力分布。
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公开(公告)号：US5575623A
公开(公告)日：1996-11-19
申请号：US526104
申请日：1995-09-11
CPC分类号： F01D5/3038
摘要： In a drum rotor (1) for an axial-flow turbomachine, the blades are fastened with their roots (3) in rows in encircling blade grooves (10) having lateral supporting prongs. At least the first blade groove (10), on the inlet side of the working medium, is shaped in an axially asymmetrical manner by a plurality of radii (R1-R4). The preceding radius (R1) in each case is larger than the following radius (R2), and the circular arcs (21-24) formed by the radii (R1-R4) have a common tangent (T) at their contact points.
摘要翻译： 在用于轴流式涡轮机的鼓式转子（1）中，叶片以其根部（3）在具有侧向支撑尖头的环形叶片槽（10）中排成一行。 至少第一叶片槽（10）在工作介质的入口侧上通过多个半径（R1-R4）以不对称的方式成形。 在每种情况下，前半径（R1）大于随后的半径（R2），并且由半径（R1-R4）形成的圆弧（21-24）在其接触点具有共同的切线（T）。
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公开(公告)号：US4907944A
公开(公告)日：1990-03-13
申请号：US655792
申请日：1984-10-01
CPC分类号： F01D5/3038
摘要： An improved blade mounting arrangement for a gas turbine engine with a turbine and an annular flowpath therethrough is disclosed. The improvement comprises a one-piece outer casing and a one-piece inner casing bounding the flowpath. The outer casing has a plurality of circumferential recesses disposed therein with each of the recesses having first and second axially opposite circumferential slots. A plurality of first turbine blades, each with axially facing tangs on a mounting platform, mate with the slots in the outer casing recess. The inner casing has a plurality of recesses disposed therein, each of the recesses including a forward circumferential slot and concentric aft radially outer and radially inner circumferential slots. A plurality of second turbine blades, each with forward and aft axially facing tangs on a mounting platform, mate with respective ones of forward slot and radially outer slot in the inner casing recess.
摘要翻译： 公开了一种用于具有涡轮机的燃气涡轮发动机和通过其的环形流动路径的改进的叶片安装装置。 改进包括一体式外壳和围绕流路的一体式内壳。 外壳具有设置在其中的多个周向凹部，每个凹槽具有第一和第二轴向相对的圆周槽。 多个在安装平台上具有轴向面向的柄脚的第一涡轮叶片与外壳凹槽中的狭槽配合。 内壳体具有设置在其中的多个凹部，每个凹槽包括前周向槽和同心的后部径向外部和径向内周向槽。 多个第二涡轮机叶片，每个在安装平台上具有向前和向后的轴向面向的柄脚，与内壳体凹部中的前槽和径向外槽中的相应的一个配合。
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公开(公告)号：US4875830A
公开(公告)日：1989-10-24
申请号：US756462
申请日：1985-07-18
CPC分类号： F01D5/3038 , F01D11/008
摘要： In a compressor rotor assembly of an axial flow gas turbine engine, wherein the rotor disk has a circumferential blade retaining slot for receiving the root of each blade of a row of blades, a ladder seal is provided between the slot and the blade platforms to limit the leakage of working medium gases from the flow path and through the slot. During engine operation, the seal moves radially outwardly into sealing relation with the underside surface of each platform. At the same time, radially inwardly extending flanges of the seal move radially outwardly into sealing relation with the sidewalls of the disk slot.
摘要翻译： 在轴流式燃气涡轮发动机的压缩机转子组件中，其中转子盘具有用于接收一排叶片的每个叶片的根部的周向叶片保持槽，在狭槽和叶片平台之间设置梯密封件以限制 工作介质气体从流动通道和槽口泄漏。 在发动机运行期间，密封件径向向外移动，与每个平台的下表面密封。 同时，密封件的径向向内延伸的凸缘径向向外移动成与盘槽的侧壁密封。
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