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1. 发明授权

US09097118B2 Transitional region for a combustion chamber of a gas turbine 有权
标题翻译：燃气轮机燃烧室的过渡区域
公开(公告)号：US09097118B2
公开(公告)日：2015-08-04
申请号：US13226020
申请日：2011-09-06
申请人： Martin Schnieder , Jörg Krückels , Uwe Rüdel , Christoph Appel , Urs Benz
发明人： Martin Schnieder , Jörg Krückels , Uwe Rüdel , Christoph Appel , Urs Benz
IPC分类号： F02C7/24 , F23R3/04 , F01D9/02 , F23R3/00
CPC分类号： F01D9/023 , F02C7/24 , F23R3/002 , F23R3/007 , F23R2900/00005 , F23R2900/03042 , Y02T50/67 , Y02T50/675
摘要： A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.
摘要翻译：一种燃气轮机，包括燃烧室和第一排导叶，基本上直接布置在涡轮的下游。由至少一个外部和/或内部热屏蔽限定的燃烧室的外部和/或内部限制，其安装在径向外侧和/或内部布置的至少一个燃烧室结构上。引导叶片排的区域中的热气体流动通道至少间接地安装在至少一个涡轮机载体上的外部和/或内部叶片平台的外侧和/或内部径向限制。通过至少间接地安装在涡轮机载体上至少一个微型隔热罩来实现第一排导叶直接上游的最小间隙尺寸，其布置在第一排导叶的上游并且基本上邻近叶片平台和流体隔热板和叶片平台之间的方向。

2. 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。

3. 发明授权

US08534999B2 Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：US08534999B2
公开(公告)日：2013-09-17
申请号：US12871353
申请日：2010-08-30
申请人： Bruno Stephan , Jörg Krückels , Thomas Sommer
发明人： Bruno Stephan , Jörg Krückels , Thomas Sommer
IPC分类号： F03B3/16
CPC分类号： F01D9/023 , F01D5/14 , F01D5/141 , F01D5/142 , F01D9/041 , F05D2220/3212 , F05D2240/12
摘要： A gas turbine is provided including a compressor, a combustion chamber, a guide vane row and a rotor airfoil row. The guide vane row includes a plurality of guide vane airfoils having a blade and an inner platform. The ratio between the pitch and the leading edge diameter of the guide vane airfoils is between 6.3-7.6 and the ratio between the platform length and the leading edge diameter of the guide vane airfoils is between 4.0-5.5.
摘要翻译：提供一种燃气轮机，包括压缩机，燃烧室，导向叶片排和转子翼型排。导向叶片列包括具有叶片和内平台的多个导向叶片翼型件。导叶叶片的间距和前缘直径之间的比例在6.3-7.6之间，导叶翼型的平台长度与前缘直径的比值在4.0-5.5之间。

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

US20110236222A1 BLADE FOR A GAS TURBINE AND CASTING TECHNIQUE METHOD FOR PRODUCING SAME 审中-公开
标题翻译：一种用于生产气体的燃气轮机和铸造技术方法
公开(公告)号：US20110236222A1
公开(公告)日：2011-09-29
申请号：US12961659
申请日：2010-12-07
申请人： Jose Anguisola MCFEAT , Jörg KRÜCKELS , Roland DÜCKERSHOFF , Brian Kenneth WARDLE
发明人： Jose Anguisola MCFEAT , Jörg KRÜCKELS , Roland DÜCKERSHOFF , Brian Kenneth WARDLE
IPC分类号： F01D5/18 , B22C9/00 , B22D25/02
CPC分类号： B22D25/02 , B22C7/06 , B22C9/10 , F01D5/147 , F05D2230/211
摘要： A blade for a gas turbine has a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough. A multiplicity of turbulators or pins, which are formed on the wall, are arranged in a distributed manner in the region of the trailing edge and project from the internal surfaces into the cavity, to improve the transfer of heat between the wall of the blade and the cooling air. An improvement of the internal cooling is achieved by the turbulators or pins extending into the cavity in a direction which can be freely selected within an angular range.
摘要翻译：用于燃气轮机的叶片具有前缘和后缘以及由内表面限定的用于引导冷却空气的内腔。形成在壁上的多个紊流器或销以分布的方式布置在后缘的区域中并从内表面突出到空腔中，以改善叶片的壁和冷却空气。内部冷却的改进是通过在可以在角度范围内自由选择的方向上延伸到空腔中的扰流器或销钉实现的。

6. 发明授权

US09062555B2 Gas turbine blade and method for producing a blade 有权
标题翻译：燃气轮机叶片及其制造方法
公开(公告)号：US09062555B2
公开(公告)日：2015-06-23
申请号：US13528013
申请日：2012-06-20
申请人： Martin Schnieder , Jörg Krückels
发明人： Martin Schnieder , Jörg Krückels
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , F05D2260/22141 , Y10T29/49341
摘要： A blade (10) for a gas turbine has a blade airfoil (11), the blade wall (18) of which encloses an interior space (17). For cooling the blade wall (18), the blade wall (18) includes a cooling arrangement (19) which has a radial passage (20) extending in the longitudinal direction of the blade and from which a multiplicity of cooling passages (21, 22), extending in the blade wall (18), branch in the transverse direction, and from which a multiplicity of film-cooling holes (23) are led to the outside in the transverse direction. Particularly efficient cooling is made possible by the distribution of the film-cooling holes (23) along the radial passage (20) being selected independently of the distribution of the cooling passages (21, 22) along the radial passage (20).
摘要翻译：用于燃气涡轮机的叶片（10）具有叶片翼型件（11），其叶片壁（18）包围内部空间（17）。为了冷却叶片壁（18），叶片壁（18）包括冷却装置（19），该冷却装置具有在叶片的纵向方向上延伸的径向通道（20），多个冷却通道（21,22 ）在叶片壁（18）中延伸，在横向方向上分支，多个薄膜冷却孔（23）从该横向方向被引导到外部。通过沿着径向通道（20）分配不同于冷却通道（21,22）的分配的径向通道（20）分布薄膜冷却孔（23），可以实现特别有效的冷却。

7. 发明申请

US20130004332A1 GAS TURBINE BLADE AND METHOD FOR PRODUCING A BLADE 有权
标题翻译：气体涡轮叶片及其制造方法
公开(公告)号：US20130004332A1
公开(公告)日：2013-01-03
申请号：US13528013
申请日：2012-06-20
申请人： Martin Schnieder , Jörg Krückels
发明人： Martin Schnieder , Jörg Krückels
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , F05D2260/22141 , Y10T29/49341
摘要： A blade (10) for a gas turbine has a blade airfoil (11), the blade wall (18) of which encloses an interior space (17). For cooling the blade wall (18), the blade wall (18) includes a cooling arrangement (19) which has a radial passage (20) extending in the longitudinal direction of the blade and from which a multiplicity of cooling passages (21, 22), extending in the blade wall (18), branch in the transverse direction, and from which a multiplicity of film-cooling holes (23) are led to the outside in the transverse direction. Particularly efficient cooling is made possible by the distribution of the film-cooling holes (23) along the radial passage (20) being selected independently of the distribution of the cooling passages (21, 22) along the radial passage (20).
摘要翻译：用于燃气涡轮机的叶片（10）具有叶片翼型件（11），其叶片壁（18）包围内部空间（17）。为了冷却叶片壁（18），叶片壁（18）包括冷却装置（19），该冷却装置具有在叶片的纵向方向上延伸的径向通道（20），多个冷却通道（21,22 ）在叶片壁（18）中延伸，在横向方向上分支，多个薄膜冷却孔（23）从该横向方向被引导到外部。通过沿着径向通道（20）分配不同于冷却通道（21,22）的分配的径向通道（20）分布薄膜冷却孔（23），可以实现特别有效的冷却。

8. 发明申请

US20120063891A1 COOLED COMPONENT FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的冷却组件
公开(公告)号：US20120063891A1
公开(公告)日：2012-03-15
申请号：US13247429
申请日：2011-09-28
申请人： Jörg Krückels , Tanguy Arzel , Jose Anguisola Mcfeat , Martin Schnieder
发明人： Jörg Krückels , Tanguy Arzel , Jose Anguisola Mcfeat , Martin Schnieder
IPC分类号： F04D29/58
CPC分类号： F01D5/186 , F01D5/187 , F01D5/225 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A cooled component for a gas turbine is disclosed, which by an outer side of a wall delimits hot gas passage of the gas turbine and on an inner side has a device for impingement cooling. The impingement cooling device can include a multiplicity of impingement cooling chambers which are arranged next to each other, operate in parallel, are covered by impingement cooling plates which are equipped with impingement cooling holes, and are impinged upon by cooling air during operation.
摘要翻译：公开了一种用于燃气轮机的冷却部件，其通过壁的外侧限定燃气轮机的热气体通道，并且在内侧具有用于冲击冷却的装置。冲击冷却装置可以包括彼此相邻布置的多个冲击冷却室，并联操作，被装有冲击冷却孔的冲击冷却板覆盖，并且在操作期间被冷却空气撞击。

9. 发明申请

US20120060503A1 TRANSITIONAL REGION FOR A COMBUSTION CHAMBER OF A GAS TURBINE 有权
标题翻译：燃气轮机燃烧室过渡区
公开(公告)号：US20120060503A1
公开(公告)日：2012-03-15
申请号：US13226020
申请日：2011-09-06
申请人： Martin SCHNIEDER , Jörg Krückels , Uwe Rüdel , Christoph APPEL , Urs BENZ
发明人： Martin SCHNIEDER , Jörg Krückels , Uwe Rüdel , Christoph APPEL , Urs BENZ
IPC分类号： F23R3/42
CPC分类号： F01D9/023 , F02C7/24 , F23R3/002 , F23R3/007 , F23R2900/00005 , F23R2900/03042 , Y02T50/67 , Y02T50/675
摘要： A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.
摘要翻译：一种燃气轮机，包括燃烧室和第一排导叶，基本上直接布置在涡轮的下游。由至少一个外部和/或内部热屏蔽限定的燃烧室的外部和/或内部限制，其安装在径向外侧和/或内部布置的至少一个燃烧室结构上。引导叶片排的区域中的热气体流动通道至少间接地安装在至少一个涡轮机载体上的外部和/或内部叶片平台的外侧和/或内部径向限制。通过至少间接地安装在涡轮机载体上至少一个微型隔热罩来实现第一排导叶直接上游的最小间隙尺寸，其布置在第一排导叶的上游并且基本上邻近叶片平台和流体隔热板和叶片平台之间的方向。

10. 发明申请

US20110058940A1 GAS TURBINE 有权
标题翻译：燃气轮机
公开(公告)号：US20110058940A1
公开(公告)日：2011-03-10
申请号：US12871353
申请日：2010-08-30
申请人： Bruno STEPHAN , Jörg KRÜCKELS , Thomas SOMMER
发明人： Bruno STEPHAN , Jörg KRÜCKELS , Thomas SOMMER
IPC分类号： F04D29/44
CPC分类号： F01D9/023 , F01D5/14 , F01D5/141 , F01D5/142 , F01D9/041 , F05D2220/3212 , F05D2240/12
摘要： A gas turbine is provided including a compressor, a combustion chamber, a guide vane row and a rotor airfoil row. The guide vane row includes a plurality of guide vane airfoils having a blade and an inner platform. The ratio between the pitch and the leading edge diameter of the guide vane airfoils is between 6.3-7.6 and the ratio between the platform length and the leading edge diameter of the guide vane airfoils is between 4.0-5.5.
摘要翻译：提供一种燃气轮机，包括压缩机，燃烧室，导向叶片排和转子翼型排。导向叶片列包括具有叶片和内平台的多个导向叶片翼型件。导叶叶片的间距和前缘直径之间的比例在6.3-7.6之间，导叶翼型的平台长度与前缘直径的比值在4.0-5.5之间。

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