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公开(公告)号：US07766619B2
公开(公告)日：2010-08-03
申请号：US11907420
申请日：2007-10-12
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/70 , F05D2260/201
摘要： A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.
摘要翻译： 燃气轮机具有沿着叶片翼型的前缘延伸的冷却空气通道，该冷却空气通道具有布置在叶片尖端的区域中的出口。 出口开口的轮廓几何形状与冷却空气通道的横截面类似。 结果，避免了冷却空气流的不均匀性，其局部地不利地影响热传递，并因此降低了冷却效率。
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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：US20080181784A1
公开(公告)日：2008-07-31
申请号：US11907420
申请日：2007-10-12
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/70 , F05D2260/201
摘要： A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.
摘要翻译： 燃气轮机具有沿着叶片翼型的前缘延伸的冷却空气通道，该冷却空气通道具有布置在叶片尖端的区域中的出口。 出口开口的轮廓几何形状与冷却空气通道的横截面类似。 结果，避免了冷却空气流的不均匀性，其局部地不利地影响热传递，并因此降低了冷却效率。
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公开(公告)号：US07220099B2
公开(公告)日：2007-05-22
申请号：US11008988
申请日：2004-12-13
申请人： Igor A. Bekrenev , Arkadi Fokine , Frank Hummel , Igor Ossipov , Sergey Trifonov
发明人： Igor A. Bekrenev , Arkadi Fokine , Frank Hummel , Igor Ossipov , Sergey Trifonov
IPC分类号： F01D11/00
CPC分类号： F01D11/006 , F01D11/005 , F01D11/008 , F05D2230/642
摘要： A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.
摘要翻译： 用于涡轮机的转子的密封装置包括用于在叶片（2）和隔热罩（3,4）之间密封的叶片（2），隔热罩（3,4）和密封元件（5,6） 当叶片（2），隔热罩（3,4）和密封元件（5,6）组装用于转子时。 隔热罩（3,4）包括用于容纳密封元件（5,6）的第一构件（11,12）的第一槽（7,8），并且叶片（2）的根部包括第二槽 以及用于容纳密封元件（5,6）的第二构件（13,14）的第三槽（9,10）。 第一槽（7,8）沿与第二槽和第三槽（9）延伸的方向基本相互垂直的方向延伸，并且第一构件（11,12）沿基本相互垂直的方向延伸 到第二构件（13,14）延伸的方向。
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公开(公告)号：US20050118016A1
公开(公告)日：2005-06-02
申请号：US10865844
申请日：2004-06-14
申请人： Arkadi Fokine , Anatoli Kwasnikov , Igor Ossipov , Christoph Pfeiffer , Joerg Stengele , Sergey Trifonov
发明人： Arkadi Fokine , Anatoli Kwasnikov , Igor Ossipov , Christoph Pfeiffer , Joerg Stengele , Sergey Trifonov
CPC分类号： F01D11/005 , F16J15/0887
摘要： A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).
摘要翻译： 一种具有热积聚段（3）的燃气轮机装置，其在燃气轮机的外壳上布置有相对的活动叶片，并且具有与在热积聚段（3）之间的圆周上相邻布置的导叶（1） 燃气轮机的壳体和转子，动叶片和导叶（1）布置在燃气轮机的热气通道（5）中。 在导向叶片（1）和热积聚段（3）之间存在布置在圆周上的至少一个密封元件（4），并且可以通过保护罩（6）与热气管道（5）分离 ）。
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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：US07121790B2
公开(公告)日：2006-10-17
申请号：US10865844
申请日：2004-06-14
申请人： Arkadi Fokine , Anatoli Kwasnikov , Igor Ossipov , Christoph Pfeiffer , Joerg Stengele , Sergey Trifonov
发明人： Arkadi Fokine , Anatoli Kwasnikov , Igor Ossipov , Christoph Pfeiffer , Joerg Stengele , Sergey Trifonov
IPC分类号： F04D29/08
CPC分类号： F01D11/005 , F16J15/0887
摘要： A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).
摘要翻译： 一种具有热积聚段（3）的燃气轮机装置，其在燃气轮机的外壳上布置有相对的活动叶片，并且具有与在热积聚段（3）之间的圆周上相邻布置的导叶（1） 燃气轮机的壳体和转子，动叶片和导叶（1）布置在燃气轮机的热气通道（5）中。 在导向叶片（1）和热积聚段（3）之间存在布置在圆周上的至少一个密封元件（4），并且可以通过保护罩（6）与热气管道（5）分离 ）。
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公开(公告)号：US20050129525A1
公开(公告)日：2005-06-16
申请号：US11008988
申请日：2004-12-13
申请人： Igor Bekrenev , Arkadi Fokine , Frank Hummel , Igor Ossipov , Sergey Trifonov
发明人： Igor Bekrenev , Arkadi Fokine , Frank Hummel , Igor Ossipov , Sergey Trifonov
CPC分类号： F01D11/006 , F01D11/005 , F01D11/008 , F05D2230/642
摘要： A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.
摘要翻译： 用于涡轮机的转子的密封装置包括用于在叶片（2）和隔热罩（3,4）之间密封的叶片（2），隔热罩（3,4）和密封元件（5,6） 当叶片（2），隔热罩（3,4）和密封元件（5,6）组装用于转子时。 隔热罩（3,4）包括用于容纳密封元件（5,6）的第一构件（11,12）的第一槽（7,8），并且叶片（2）的根部包括第二槽 以及用于容纳密封元件（5,6）的第二构件（13,14）的第三槽（9,10）。 第一槽（7,8）沿与第二槽和第三槽（9）延伸的方向基本相互垂直的方向延伸，并且第一构件（11,12）沿基本相互垂直的方向延伸 到第二构件（13,14）延伸的方向。
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公开(公告)号：US06857848B2
公开(公告)日：2005-02-22
申请号：US10372331
申请日：2003-02-25
CPC分类号： F01D11/005
摘要： A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, on the other hand, adjacent to the heat shield carrier.
摘要翻译： 燃气轮机中的间隙密封，用于从燃气轮机的热气体空间密封形成在隔热罩和隔热罩载体之间的冷却空间。 一方面，密封体以可移动的方式保持在隔热板上，另一方面与叶片载体相对地保持在隔热板载体上。
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