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1. 发明申请

US20080050233A1 Turbo Machine 有权
标题翻译：涡轮机
公开(公告)号：US20080050233A1
公开(公告)日：2008-02-28
申请号：US11841333
申请日：2007-08-20
申请人： Ulrich Steiger , Sven Olmes
发明人： Ulrich Steiger , Sven Olmes
IPC分类号： F01D25/00
CPC分类号： F01D11/02 , F01D11/001 , F05D2250/182 , F05D2250/283 , F05D2250/314
摘要： A turbomachine (1), in particular a gas turbine, has a stator (2) and a rotor (3) and with at least one axial sealing device (6) arranged between them. On the stator side, the sealing device (6) has a radially stepped sealing contour (8) with regions (9, 10) projecting and retracting in the direction of the rotor (3), on the rotor side a plurality of sealing fins (11) projecting in the direction of the stator (2) being arranged, which engage in each case into adjacent retracting regions (10) of the stator-side sealing contour (8). On the rotor side, at least one additional fin (12) projecting in the direction of the stator (2) is provided, which is positioned between two adjacent sealing fins (11) arranged on the rotor side and which lies opposite a projecting region of the stator-side sealing contour (8).
摘要翻译：涡轮机（1），特别是燃气轮机，具有定子（2）和转子（3），并且在它们之间具有至少一个轴向密封装置（6）。在定子侧，密封装置（6）具有径向阶梯状的密封轮廓（8），区域（9,10）在转子（3）的方向上突出和缩回，转子侧有多个密封翅片 11）在定子（2）的方向上突出设置，每个壳体与定子侧密封轮廓（8）的相邻的缩回区域（10）啮合。在转子侧，设置有沿定子（2）的方向突出的至少一个附加的翅片（12），其位于设置在转子侧上的相邻的两个密封翅片（11）之间，定子侧密封轮廓（8）。

2. 发明授权

US08182211B2 Turbo machine 有权
标题翻译：涡轮机
公开(公告)号：US08182211B2
公开(公告)日：2012-05-22
申请号：US11841333
申请日：2007-08-20
申请人： Ulrich Steiger , Sven Olmes
发明人： Ulrich Steiger , Sven Olmes
IPC分类号： F01D11/02
CPC分类号： F01D11/02 , F01D11/001 , F05D2250/182 , F05D2250/283 , F05D2250/314
摘要： A turbomachine (1), in particular a gas turbine, has a stator (2) and a rotor (3) and with at least one axial sealing device (6) arranged between them. On the stator side, the sealing device (6) has a radially stepped sealing contour (8) with regions (9, 10) projecting and retracting in the direction of the rotor (3), on the rotor side a plurality of sealing fins (11) projecting in the direction of the stator (2) being arranged, which engage in each case into adjacent retracting regions (10) of the stator-side sealing contour (8). On the rotor side, at least one additional fin (12) projecting in the direction of the stator (2) is provided, which is positioned between two adjacent sealing fins (11) arranged on the rotor side and which lies opposite a projecting region of the stator-side sealing contour (8).
摘要翻译：涡轮机（1），特别是燃气轮机，具有定子（2）和转子（3），并且在它们之间具有至少一个轴向密封装置（6）。在定子侧，密封装置（6）具有径向阶梯状的密封轮廓（8），区域（9,10）在转子（3）的方向上突出和缩回，转子侧有多个密封翅片 11）在定子（2）的方向上突出设置，每个壳体与定子侧密封轮廓（8）的相邻的缩回区域（10）啮合。在转子侧，设置有沿定子（2）的方向突出的至少一个附加的翅片（12），其位于设置在转子侧上的相邻的两个密封翅片（11）之间，定子侧密封轮廓（8）。

3. 发明授权

US08979470B2 Gas turbine engine and method for cooling the compressor of a gas turbine engine 有权
标题翻译：燃气涡轮发动机和用于冷却燃气涡轮发动机的压缩机的方法
公开(公告)号：US08979470B2
公开(公告)日：2015-03-17
申请号：US13197840
申请日：2011-08-04
申请人： Sergei Riazantsev , Holger Kiewel , Sven Olmes , Thomas Kramer , Sergey Shchukin
发明人： Sergei Riazantsev , Holger Kiewel , Sven Olmes , Thomas Kramer , Sergey Shchukin
IPC分类号： F01D5/08 , F01D5/18 , F01D5/30 , F04D29/32 , F04D29/58
CPC分类号： F01D5/084 , F01D5/3007 , F04D29/321 , F04D29/584 , F05D2220/32
摘要： A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.
摘要翻译：燃气涡轮发动机包括具有转子叶片的压缩机，转子叶片具有连接到压缩机鼓的座中的根部。转子叶片根部和/或压缩机滚筒具有用于冷却流体的纵向通道，将较高压力区域连接到燃气涡轮发动机的较低压力区域。

4. 发明授权

US08092150B2 Gas turbine with axial thrust balance 有权
标题翻译：燃气轮机轴向推力平衡
公开(公告)号：US08092150B2
公开(公告)日：2012-01-10
申请号：US12167800
申请日：2008-07-03
申请人： Stefan Rofka , Rene Waelchli , Sven Olmes , Thomas Zierer
发明人： Stefan Rofka , Rene Waelchli , Sven Olmes , Thomas Zierer
IPC分类号： F01D3/00 , F01D3/04
CPC分类号： F01D3/04
摘要： A method for axial thrust control of a gas turbine, and a gas turbine with a device for controlling axial thrust are provided. A gas turbine, with regard to aerodynamic forces and pressure forces, which exert an axial force upon the rotor, is configured such that at no-load and low partial load it has a negative thrust, and at high load it has a positive thrust. In order to ensure a resulting positive thrust upon the thrust bearing within the entire load range of the gas turbine, an additional thrust is applied in a controlled manner. The additional thrust for example can be controlled in dependence upon the gas turbine load. The resulting thrust force at full load is consequently less than in the case of a conventionally designed gas turbine without thrust balance.
摘要翻译：提供了一种用于燃气轮机的轴向推力控制的方法，以及具有用于控制轴向推力的装置的燃气轮机。关于在转子上施加轴向力的空气动力和压力的燃气轮机被构造成使得在空载和低部分负载时，其具有负推力，并且在高负载下具有正推力。为了确保在燃气轮机的整个负载范围内的推力轴承产生的正向推力，以受控的方式施加额外的推力。附加的推力例如可以根据燃气轮机负载来控制。因此，所得的满载推力因此小于常规设计的没有推力平衡的燃气轮机的情况。

5. 发明申请

US20120036864A1 GAS TURBINE ENGINE AND METHOD FOR COOLING THE COMPRESSOR OF A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机和用于冷却气体涡轮发动机的压缩机的方法
公开(公告)号：US20120036864A1
公开(公告)日：2012-02-16
申请号：US13197840
申请日：2011-08-04
申请人： Sergei RIAZANTSEV , Holger Kiewel , Sven Olmes , Thomas Kramer , Sergey Shchukin
发明人： Sergei RIAZANTSEV , Holger Kiewel , Sven Olmes , Thomas Kramer , Sergey Shchukin
IPC分类号： F02C7/18 , F02C7/141
CPC分类号： F01D5/084 , F01D5/3007 , F04D29/321 , F04D29/584 , F05D2220/32
摘要： A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.
摘要翻译：燃气涡轮发动机包括具有转子叶片的压缩机，转子叶片具有连接到压缩机鼓的座中的根部。转子叶片根部和/或压缩机滚筒具有用于冷却流体的纵向通道，将较高压力区域连接到燃气涡轮发动机的较低压力区域。

6. 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。

7. 发明申请

US20070095072A1 Gas turbine with cooling air 失效
标题翻译：燃气轮机带冷却空气
公开(公告)号：US20070095072A1
公开(公告)日：2007-05-03
申请号：US11548992
申请日：2006-10-12
申请人： Sven Olmes , Wilhelm Reiter , Thomas Zierer
发明人： Sven Olmes , Wilhelm Reiter , Thomas Zierer
IPC分类号： F02C7/18
CPC分类号： F02C7/185 , F02C3/22 , F02C7/141 , F02C7/22 , Y02E20/16 , Y02T50/675
摘要： A gas turbine includes a compressor for compressing the combustion air, at least one combustion chamber, in which a fuel is burned while compressed combustion air is supplied, and at least one first turbine arranged downstream of the combustion chamber and in which the hot combustion gases from the combustion chamber are expanded to perform work. Part of the compressed combustion air is branched off, cooled in a cooling air cooler, brought to a lower cooling air pressure by a second turbine and supplied to the gas turbine for cooling purposes.
摘要翻译：燃气轮机包括用于压缩燃烧空气的压缩机，至少一个燃烧室，其中在供应压缩的燃烧空气的同时燃烧燃料，以及布置在燃烧室下游的至少一个第一涡轮机，其中热燃烧气体从燃烧室扩大进行工作。压缩的燃烧空气的一部分被分支，在冷却空气冷却器中冷却，由第二涡轮机降低冷却空气压力，并供给到燃气轮机用于冷却目的。

8. 发明申请

US20090067984A1 GAS TURBINE WITH AXIAL THRUST BALANCE 有权
标题翻译：具有轴向力平衡的气体涡轮机
公开(公告)号：US20090067984A1
公开(公告)日：2009-03-12
申请号：US12167800
申请日：2008-07-03
申请人： Stefan Rofka , Rene Waelchli , Sven Olmes , Thomas Zierer
发明人： Stefan Rofka , Rene Waelchli , Sven Olmes , Thomas Zierer
IPC分类号： F01D3/04
CPC分类号： F01D3/04
摘要： A method for axial thrust control of a gas turbine, and a gas turbine with a device for controlling axial thrust are provided. A gas turbine, with regard to aerodynamic forces and pressure forces, which exert an axial force upon the rotor, is configured such that at no-load and low partial load it has a negative thrust, and at high load it has a positive thrust. In order to ensure a resulting positive thrust upon the thrust bearing within the entire load range of the gas turbine, an additional thrust is applied in a controlled manner. The additional thrust for example can be controlled in dependence upon the gas turbine load. The resulting thrust force at full load is consequently less than in the case of a conventionally designed gas turbine without thrust balance.
摘要翻译：提供了一种用于燃气轮机的轴向推力控制的方法，以及具有用于控制轴向推力的装置的燃气轮机。关于在转子上施加轴向力的空气动力和压力的燃气轮机被构造成使得在空载和低部分负载时，其具有负推力，并且在高负载下具有正推力。为了确保在燃气轮机的整个负载范围内的推力轴承产生的正向推力，以受控的方式施加额外的推力。附加的推力例如可以根据燃气轮机负载来控制。因此，所得的满载推力因此小于常规设计的没有推力平衡的燃气轮机的情况。

9. 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。

10. 发明授权

US07810332B2 Gas turbine with heat exchanger for cooling compressed air and preheating a fuel 失效
标题翻译：带有热交换器的燃气轮机，用于冷却压缩空气并预热燃料
公开(公告)号：US07810332B2
公开(公告)日：2010-10-12
申请号：US11548992
申请日：2006-10-12
申请人： Sven Olmes , Wilhelm Reiter , Thomas Zierer
发明人： Sven Olmes , Wilhelm Reiter , Thomas Zierer
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F02C7/185 , F02C3/22 , F02C7/141 , F02C7/22 , Y02E20/16 , Y02T50/675
摘要： A gas turbine includes a compressor for compressing the combustion air, at least one combustion chamber, in which a fuel is burned while compressed combustion air is supplied, and at least one first turbine arranged downstream of the combustion chamber and in which the hot combustion gases from the combustion chamber are expanded to perform work. Part of the compressed combustion air is branched off, cooled in a cooling air cooler, brought to a lower cooling air pressure by a second turbine and supplied to the gas turbine for cooling purposes.
摘要翻译：燃气轮机包括用于压缩燃烧空气的压缩机，至少一个燃烧室，其中在供应压缩的燃烧空气的同时燃烧燃料，以及布置在燃烧室下游的至少一个第一涡轮机，其中热燃烧气体从燃烧室扩大进行工作。压缩的燃烧空气的一部分被分支，在冷却空气冷却器中冷却，由第二涡轮机降低冷却空气压力，并供给到燃气轮机以进行冷却。

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