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公开(公告)号：US06857639B2
公开(公告)日：2005-02-22
申请号：US10611941
申请日：2003-07-03
CPC分类号： F16J15/0887 , F01D11/005
摘要： The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics: each component (1) has one each groove (7) that is open towards the gap (3), the two grooves (7) are essentially facing each other in the gap (3), in each groove (7), a compensation body (16) is movably positioned transversely to the longitudinal groove direction and parallel to the gap plane (10), each compensation body (11) abuts the groove bottom (9) of the corresponding groove (7) in a sealing manner, each compensation body (11) has a V-shaped receiving groove (14) that is open towards the facing compensation body (11), a mutual sealing body (16) has a rhombus-shaped cross-section and projects with outer sides (17) into both receiving grooves (14), the straight inner sides (15) of each receiving groove (14) are angled towards each other at the same angle as the straight outer sides (17), in each receiving groove (14), at least one outer side (17) of the sealing body (16) abuts the corresponding inner side (15) of the receiving groove (14) with surface contact and in a sealing manner.
摘要翻译： 本发明涉及一种用于密封两个相邻部件（1,2）（特别是涡轮机）之间的间隙（3）的间隙密封（6），具有以下特征：每个部件（1）具有一个每个凹槽（7） 向间隙（3）开口，两个槽（7）在间隙（3）中基本上彼此面对，在每个槽（7）中，补偿体（16）可以横向于纵向槽方向 并且平行于间隙平面（10），每个补偿体（11）以密封方式与相应的凹槽（7）的凹槽底部（9）邻接，每个补偿体（11）具有V形接收凹槽（14） ）向相对的补偿体（11）开口，相互密封体（16）具有菱形的横截面并与外侧（17）突出成两个容纳槽（14），直内侧（15） 每个接收槽（14）在每个接收槽（14）中以与直的外侧（17）相同的角度彼此成角度，在 密封体（16）的至少一个外侧（17）以表面接触和密封方式与接收槽（14）的相应的内侧（15）邻接。
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公开(公告)号：US20090081027A1
公开(公告)日：2009-03-26
申请号：US12236995
申请日：2008-09-24
CPC分类号： F01D11/001 , F01D11/006 , F05D2240/57 , F16J15/061 , F16J15/0887
摘要： A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.
摘要翻译： 用于燃气轮机的密封组件布置在具有多个弯曲部的转子隔热罩的槽中。 该组件包括彼此重叠的四个密封部分，并相对于涡轮转子沿轴向，径向和圆周方向延伸。 保持装置保持一个密封部分的径向部分，允许所述密封部分的有限运动独立于另一个密封部分。 独立的运动确保各个密封部分与转子隔热罩的所有配合表面的接触以及改进的密封功能，而与转子隔热罩的位移和涡轮机部件的公差无关。
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公开(公告)号：US08105024B2
公开(公告)日：2012-01-31
申请号：US12236995
申请日：2008-09-24
IPC分类号： F02C7/28
CPC分类号： F01D11/001 , F01D11/006 , F05D2240/57 , F16J15/061 , F16J15/0887
摘要： A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.
摘要翻译： 用于燃气轮机的密封组件布置在具有多个弯曲部的转子隔热罩的槽中。 该组件包括彼此重叠的四个密封部分，并相对于涡轮转子沿轴向，径向和圆周方向延伸。 保持装置保持一个密封部分的径向部分，允许所述密封部分的有限运动独立于另一个密封部分。 独立的运动确保各个密封部分与转子隔热罩的所有配合表面的接触以及改进的密封功能，而与转子隔热罩的位移和涡轮机部件的公差无关。
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公开(公告)号：US20100047062A1
公开(公告)日：2010-02-25
申请号：US12579464
申请日：2009-10-15
IPC分类号： F01D5/08
CPC分类号： F01D11/08 , F05D2240/11 , F05D2240/57 , F05D2260/201 , F05D2260/22141
摘要： A stator heat shield (6) for a gas turbine (1) includes an outside (11) which in the installed state faces a hot gas path (9) of the gas turbine (1), and an inside (12) facing away from the outside (11). A plurality of ribs (13) are formed on the inside (12) and extend axially in the installed state with regard to an axis of rotation (8) of a rotor (3) of the gas turbine (1) and, in the circumferential direction, are spaced a distance apart from one another. At least one baffle plate (14) is arranged on the inside (12) and is in contact with the ribs (13). At least one groove (16) is designed in an end face (15) bordering the stator heat shield (6) in the circumferential direction, into which at least one sealing element (18) can be inserted. A plurality of bores (19) are included, each opening at a distance from the groove (16) in the direction of the outside (11) at the inside (12) at one end and on the end face (15) at the other end and arranged a distance apart from one another in the axial direction.
摘要翻译： 一种用于燃气轮机（1）的定子隔热罩（6）包括：外部（11），其处于安装状态，面对燃气轮机（1）的热气路径（9）;以及内部（12） 外面（11）。 多个肋（13）形成在内侧（12）上，并且相对于燃气轮机（1）的转子（3）的旋转轴线（8）在安装状态下轴向延伸，并且在周向 方向彼此隔开一段距离。 至少一个挡板（14）设置在内部（12）上并与肋（13）接触。 至少一个凹槽（16）被设计在沿圆周方向邻接定子隔热罩（6）的端面（15）中，至少一个密封元件（18）可插入该凹槽中。 包括多个孔（19），每个孔在一端处在一个端部处和在另一端的端面（15）处沿着外部（11）的方向在一个距离槽（16）处一定距离处 并且在轴向方向上彼此分开设置一段距离。
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公开(公告)号：US07997856B2
公开(公告)日：2011-08-16
申请号：US12579464
申请日：2009-10-15
IPC分类号： F01D5/08
CPC分类号： F01D11/08 , F05D2240/11 , F05D2240/57 , F05D2260/201 , F05D2260/22141
摘要： A stator heat shield (6) for a gas turbine (1) includes an outside (11) which in the installed state faces a hot gas path (9) of the gas turbine (1), and an inside (12) facing away from the outside (11). A plurality of ribs (13) are formed on the inside (12) and extend axially in the installed state with regard to an axis of rotation (8) of a rotor (3) of the gas turbine (1) and, in the circumferential direction, are spaced a distance apart from one another. At least one baffle plate (14) is arranged on the inside (12) and is in contact with the ribs (13). At least one groove (16) is designed in an end face (15) bordering the stator heat shield (6) in the circumferential direction, into which at least one sealing element (18) can be inserted. A plurality of bores (19) are included, each opening at a distance from the groove (16) in the direction of the outside (11) at the inside (12) at one end and on the end face (15) at the other end and arranged a distance apart from one another in the axial direction.
摘要翻译： 一种用于燃气轮机（1）的定子隔热罩（6）包括：外部（11），其处于安装状态，面对燃气轮机（1）的热气路径（9）;以及内部（12） 外面（11）。 多个肋（13）形成在内侧（12）上，并且相对于燃气轮机（1）的转子（3）的旋转轴线（8）在安装状态下轴向延伸，并且在周向 方向彼此隔开一段距离。 至少一个挡板（14）设置在内部（12）上并与肋（13）接触。 至少一个凹槽（16）被设计在沿圆周方向邻接定子隔热罩（6）的端面（15）中，至少一个密封元件（18）可插入该凹槽中。 包括多个孔（19），每个孔在一端处在一个端部处和在另一端的端面（15）处沿着外部（11）的方向在一个距离槽（16）处一定距离处 并且在轴向方向上彼此分开设置一段距离。
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公开(公告)号：US20080193289A1
公开(公告)日：2008-08-14
申请号：US12058934
申请日：2008-03-31
CPC分类号： F01D25/246 , F01D9/042 , F05D2230/70
摘要： A vane arrangement (1) of a turbo machine (4), in particular of a gas turbine, includes at least one vane carrier (2) attached to a housing (5) of a turbo machine (4), and several vanes (3) attached to the vane carrier (2) and circumferentially arranged side by side, wherein the attachment between the vane carrier (2) and respective vane (3) is adapted for being axially pluggable. In order to simplify dismounting of a single vane (3) at least one of the vanes (3) is provided with an extraction device (35) having at least one axially extending extraction through-hole (36). The respective extraction through hole (36) is provided with an inner thread (37), and the vane carrier (2) is provided with an abutment zone (38) axially opposing the extraction through hole (36). The extraction device (35) is adapted for inducing axially oriented extraction forces into the respective vane (3) by an extraction tool, which is provided with an outer thread and which is in order to extract the respective vane (3) from the vane carrier (2) inserted into the extraction through-hole (36) and axially pressing against the abutment zone (28).
摘要翻译： 涡轮机（4），特别是燃气轮机的叶片装置（1）包括附接到涡轮机（4）的壳体（5）的至少一个叶片载体（2）和几个叶片（3） ）并且沿周向布置并排设置，其中所述叶片承载件（2）和相应叶片（3）之间的附接适于轴向可插入。 为了简化单个叶片（3）的拆卸，至少一个叶片（3）设置有具有至少一个轴向延伸的抽吸通孔（36）的抽出装置（35）。 相应的提取通孔（36）设置有内螺纹（37），叶片承载件（2）设置有与提取通孔（36）轴向相对的邻接区域（38）。 提取装置（35）适于通过提取工具引导到相应的叶片（3）中的轴向取向的抽吸力，该提取工具设置有外螺纹，其用于从叶片承载器提取相应的叶片（3） （2）插入到提取通孔（36）中并且轴向地压靠在邻接区域（28）上。
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公开(公告)号：US08182210B2
公开(公告)日：2012-05-22
申请号：US12645880
申请日：2009-12-23
IPC分类号： F04D29/58
CPC分类号： F01D9/06 , F05D2240/11 , F05D2260/231
摘要： A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface.
摘要翻译： 燃气轮机包括涡轮机壳体; 具有涡轮叶片的可旋转涡轮转子; 以及用于定子的至少一个隔热板段。 隔热片段径向地设置在转子和壳体之间并且附接到壳体并且具有在燃气涡轮机的轴向方向上的至少一个区域中具有弯曲部分的轮廓和径向外表面。 隔热片段包括肋，第一凸台和设置在径向外表面上的第二凸台。
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公开(公告)号：US20100150712A1
公开(公告)日：2010-06-17
申请号：US12645880
申请日：2009-12-23
CPC分类号： F01D9/06 , F05D2240/11 , F05D2260/231
摘要： A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface.
摘要翻译： 燃气轮机包括涡轮机壳体; 具有涡轮叶片的可旋转涡轮转子; 以及用于定子的至少一个隔热板段。 隔热片段径向地设置在转子和壳体之间并且附接到壳体并且具有在燃气涡轮机的轴向方向上的至少一个区域中具有弯曲部分的轮廓和径向外表面。 隔热片段包括肋，第一凸台和设置在径向外表面上的第二凸台。
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公开(公告)号：US20100150710A1
公开(公告)日：2010-06-17
申请号：US12646365
申请日：2009-12-23
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , F01D11/005 , F05D2230/10 , F05D2240/11 , F05D2240/57 , F05D2240/80 , F05D2250/29
摘要： A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.
摘要翻译： 用于燃气涡轮机的导向叶片包括具有前缘和后缘的叶片体和至少在前缘和后缘之间延伸的护罩。 护罩具有基本上在燃气轮机的径向和纵向方向上延伸的第一侧壁和第二侧壁。 第一侧壁具有设置在沿着护罩的纵向方向延伸的后缘的区域中的凹槽，并且构造成容纳密封板。 第一侧壁还具有在后缘的区域中从凹槽延伸的间隙，其中在燃气轮机的圆周方向上的间隙的深度等于凹槽的深度，并且其中间隙的宽度 在护罩的纵向方向上是间隙深度的一到三倍之间。
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公开(公告)号：US20090041587A1
公开(公告)日：2009-02-12
申请号：US12185593
申请日：2008-08-04
申请人： Maxim Konter , Anton Sumin , Sergey Vorontsov , Alexander Khanin
发明人： Maxim Konter , Anton Sumin , Sergey Vorontsov , Alexander Khanin
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/211 , F05D2250/313 , F05D2260/2212 , F05D2260/22141
摘要： A rotating blade (1) for a gas turbine comprises an internal cooling structure having at least three cooling air passages (5, 6, 7) in fluid connection with one another by turns (9, 10). An opening (12) provides an outlet for dissolved core material to be removed from the blade following casting of the cooling structure without any residue remaining within. According to the invention, the cooling structure comprises trip strips (13, 15) in the first and second passage (5, 6) with specified ratio of height to distance between trip strips and the trip strips (13) in the first passage being arranged at 90° with respect to the direction of airflow. In a particular embodiment, the trip strips (15) in the second passage (6) are arranged at angle of 45°. The design according to the invention assures sufficient airflow through first and second air passages (5, 6).
摘要翻译： 用于燃气轮机的旋转叶片（1）包括内部冷却结构，其具有至少三个彼此相对流动连接的冷却空气通道（5,6）和（7,10）。 开口（12）在冷却结构的铸造之后提供用于溶解的芯材料的出口，以从铸片中取出，而不会残留残留物。 根据本发明，冷却结构包括在第一和第二通道（5,6）中的具有指定比例的跳闸带和第一通道中的跳闸带（13）之间的跳闸条（13,15） 相对于气流方向为90°。 在特定实施例中，第二通道（6）中的脱扣条（15）以45°的角度布置。 根据本发明的设计通过第一和第二空气通道（5,6）确保足够的气流。
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