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公开(公告)号：US06464460B2
公开(公告)日：2002-10-15
申请号：US09725722
申请日：2000-11-30
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/225 , F05D2240/81 , F05D2250/141
摘要： In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).
摘要翻译： 在风叶涡轮叶片（10）中，在叶片尖端处具有护罩带元件（11），所述护罩带元件（11）横向于叶片纵向轴线延伸，中空空间（16,16'，17 ，17'）设置在所述护罩带元件（11）的内部，所述中空空间（16,16'，17,17'）在入口侧连接到至少一个冷却空气通道（ 18）通过涡轮机叶片（10）到叶片尖端并且在出口侧打开到围绕涡轮机叶片（10）的外部空间中，中空空间（16,16'，17,17'）和护罩 - 带元件（11）的形状和尺寸彼此匹配，以便减少护罩带元件（11）的重量。
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公开(公告)号：US06547525B2
公开(公告)日：2003-04-15
申请号：US09984204
申请日：2001-10-29
IPC分类号： F01D508
CPC分类号： F01D5/187 , B22C9/10 , B22C9/24 , Y10T29/49341
摘要： A cooled component, such as a turbine blade for gas turbines is provided, having efficient internal cooling, with an interior cooling passageway having a round cross-section. A row of feeding holes for the coolant are arranged spaced from each other in the direction of the longitudinal axis of the cooling passageway and originating from a common coolant channel. Each of the feeding holes intersects the cooling passageway tangentially. The ease of manufacturing the cooling component is improved in that the majority of the feeding holes have a hole diameter that is smaller than half of the hydraulic diameter of the cooling passageway, and selected feeding holes have a hole diameter that is greater than half of the hydraulic diameter of the cooling channel.
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公开(公告)号：US06416282B1
公开(公告)日：2002-07-09
申请号：US09686963
申请日：2000-10-12
申请人： Alexander Beeck , Herbert Brandl , Hartmut Haehnle , Beat von Arx
发明人： Alexander Beeck , Herbert Brandl , Hartmut Haehnle , Beat von Arx
IPC分类号： F01D518
CPC分类号： F01D5/087 , F01D5/3015
摘要： A rotor for a gas turbine comprises a multiplicity of rotor blades of which each comprises a blade airfoil, a blade root and a platform arranged between blade airfoil and blade root and each of which, together with the blade root, is pushed into an axial location slot, which is arranged on the outer periphery of a rotor disk, and is releasably retained there in such a way that hollow spaces are formed between the platform and the peripheral surface of the rotor disk, and each of which is supplied, for cooling purposes, with cooling air through at least one cooling air supply passage extending in the rotor disk and emerging into the location slot, which cooling air is fed through the blade root to within the blade airfoil.
摘要翻译： 用于燃气轮机的转子包括多个转子叶片，每个转子叶片包括叶片翼型件，叶片根部和布置在叶片翼型件和叶片根部之间的平台，并且每个转子叶片与叶片根部一起被推入轴向位置 槽，其布置在转子盘的外周上，并且可释放地保持在其中，使得在平台和转子盘的周边表面之间形成中空空间，并且为了冷却目的而提供每个槽 其中冷却空气通过至少一个在转子盘中延伸的冷却空气供应通道并且出现到定位槽中，该冷却空气通过叶片根部被供给到叶片翼型内。
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公开(公告)号：US06439848B2
公开(公告)日：2002-08-27
申请号：US09739283
申请日：2000-12-19
申请人： Hartmut Haehnle , Bernhard Weigand
发明人： Hartmut Haehnle , Bernhard Weigand
IPC分类号： F03D1102
CPC分类号： F01D5/187 , F01D5/186 , F05D2260/202
摘要： A blade component of a gas turbine is disclosed around the outside of which hot air flows. The blade component is constructed as a hollow profile having outside walls and a tip cover, and having guiding walls arranged between the outside walls and connecting said outside walls. The blade component is cooled on the inside by cooling air flowing through cooling channels between the outside walls and the guiding walls. Cooling air flows through deflection areas in which the cooling air is deflected into flow stagnation zones. An efficient cooling of the blade component in the area of the stagnation zones is obtained in the area of the flow stagnation zones which are located at the outer corner of the deflection area. At least one drilled opening is provided in the outside wall through which drilled opening cooling air is able to flow at the stagnation zone from the cooling channel onto the outside of the blade component.
摘要翻译： 公开了一种燃气轮机的叶片部件，其周围热空气流动。 叶片部件被构造为具有外壁和尖端盖的中空型材，并且具有布置在外壁之间并连接所述外壁的引导壁。 叶片部件通过流过外壁和引导壁之间的冷却通道的冷却空气在内部被冷却。 冷却空气流过其中冷却空气偏转到流动停滞区域的偏转区域。 在位于偏转区域的外角处的流动停滞区域中获得在停滞区域中的叶片部件的有效冷却。 在外壁上设置至少一个钻孔，钻孔开口冷却空气能够在停滞区域从冷却通道流到叶片部件的外侧。
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公开(公告)号：US08950192B2
公开(公告)日：2015-02-10
申请号：US12857131
申请日：2010-08-16
申请人： Remigi Tschuor , Russell Bond Jones , Luis J. Rodriguez , Hartmut Haehnle , Marion Duggan (-Oneil)
发明人： Remigi Tschuor , Russell Bond Jones , Luis J. Rodriguez , Hartmut Haehnle , Marion Duggan (-Oneil)
CPC分类号： F01D9/023 , F02C7/28 , F05D2240/55 , F05D2250/42
摘要： A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an outer shell delimiting the combustor and splittable at a parting plane; a plenum enclosing the outer shell; a rotor; a turbine vane carrier encompassing the rotor; a plurality of stator vanes disposed on the vane carrier, and at least two sealing segments forming a ring, each of the at least two sealing segments having an inner edge and a head and a foot section and being movably mounted on the inner edge by the foot section to the outer shell and by the head section to the turbine vane carrier so as to mechanically connect the combustor to the turbine vane carrier.
摘要翻译： 燃气轮机包括涡轮部分; 设置在所述涡轮部分的上游并且被配置为将出口侧的热气流排放到所述涡轮部分的环形燃烧器; 外壳限定燃烧器并在分型平面处可分开; 包围外壳的增压室; 转子 包围转子的涡轮叶片载体; 设置在所述叶片载体上的多个定子叶片和形成环的至少两个密封段，所述至少两个密封段中的每一个具有内边缘和头部和脚部，并且可移动地安装在所述内边缘上 脚部到外壳，并且通过头部到达涡轮叶片载体，以便将燃烧器机械地连接到涡轮叶片载体。
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公开(公告)号：US08272220B2
公开(公告)日：2012-09-25
申请号：US12860620
申请日：2010-08-20
申请人： Hartmut Haehnle , Gregory Vogel , Russell Bond Jones , Marion Duggans (-Oneil) , Remigi Tschuor
发明人： Hartmut Haehnle , Gregory Vogel , Russell Bond Jones , Marion Duggans (-Oneil) , Remigi Tschuor
IPC分类号： F02C3/00
CPC分类号： F23R3/04 , F01D9/023 , F01D25/26 , F02C6/12 , F05D2220/40 , F23R3/005 , F23R2900/03044
摘要： A thermal machine including a wall defining a hot gas duct for transferring a hot gas stream and a cooling jacket disposed at a distance from the wall on an outside of the hot gas duct so as to define a cooling duct with an inlet and an outlet. The cooling duct is configured to conduct a cooling medium along an external face of the wall from the inlet to an outlet in a direction counter to a flow of hot gas in the hot gas duct. An impingement cooling plate is disposed at the inlet of the cooling duct and includes cooling baffle holes configured such that cooling medium entering the cooling duct through the cooling baffle holes flows in a direction perpendicular to the wall. The impingement cooling plate is positioned such that an inflow-side edge sealingly abuts the wall of the hot gas duct so as to reduce a transverse flow of the cooling medium through the cooling duct.
摘要翻译： 一种热机器，其包括限定用于传输热气流的热气管道的壁和在所述热气体管道的外部设置为距离所述壁一定距离的冷却套管，以限定具有入口和出口的冷却管道。 所述冷却管道构造成沿着所述壁的外表面沿与所述热气体管道中的热气流相反的方向从入口向出口导入冷却介质。 冲击冷却板设置在冷却管道的入口处，并且包括冷却挡板孔，其构造成使得通过冷却挡板进入冷却管道的冷却介质沿垂直于壁的方向流动。 冲击冷却板被定位成使得流入侧边缘密封地邻接热气管道的壁，以便减少冷却介质通过冷却管道的横向流动。
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7.发明授权公开(公告)号：US08006381B2
公开(公告)日：2011-08-30
申请号：US12633541
申请日：2009-12-08
申请人： Hartmut Haehnle , Ingo Schwarz , Christoph Nagler
发明人： Hartmut Haehnle , Ingo Schwarz , Christoph Nagler
IPC分类号： B23P6/00
CPC分类号： F01D5/005 , F01D5/225 , Y10T29/49316 , Y10T29/49318 , Y10T29/49336 , Y10T29/49716
摘要： A method of modifying an existing casting mold for a turbine moving blade having a shroud band segment with an initial coupling geometry for coupling with a further shroud band segment, the coupling geometry having an initial coupling angle of the shroud band segment relative to a circumferential direction of the turbine, includes calculating a modified coupling geometry for the shroud band segment, the modified coupling geometry including a modified coupling angle of the shroud band segment relative to the circumferential direction. The method further includes creating at least one of a removal zone and an application zone, wherein the creating of the removal zone includes removing a first amount of casting mold material from the removal zone and wherein the creating of the application zone includes applying a second amount of an additional casting mold material to the application zone, wherein the removing and the applying steps result in the casting mold having the modified coupling angle.
摘要翻译： 一种用于涡轮机动叶片的现有铸模的修改方法，所述铸造模具具有具有初始耦合几何形状的护罩带段，用于与另一护罩带段联接，所述耦合几何形状具有所述护罩带段相对于圆周方向的初始耦合角度 所述涡轮机包括计算用于所述护罩带段的改进的联接几何形状，所述改进的联接几何形状包括所述护罩带段相对于所述圆周方向的改进的联接角度。 所述方法还包括产生去除区域和施用区域中的至少一个，其中所述去除区域的产生包括从所述去除区域移除第一量的铸模材料，并且其中所述施加区域的产生包括施加第二量 的额外的铸模材料施加到施加区域，其中移除和施加步骤导致具有改变的联接角度的铸模。
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公开(公告)号：US08758502B2
公开(公告)日：2014-06-24
申请号：US12826798
申请日：2010-06-30
CPC分类号： C04B35/486 , C04B35/04 , C04B35/62222 , C04B35/6316 , C04B2235/3201 , C04B2235/3225 , C04B2235/3418 , C04B2235/36 , C23C24/08 , C23C24/082 , Y10T428/249954
摘要： A slurry formulation for production of a patch or a strip of a thermal barrier coating includes 20-60 dry weight percent of alkali metal silicate binder, 40-80 dry weight percent of ceramic fillers including at least one ceramic filler selected from the group consisting of yttria-stabilized zirconia and magnesia, 0-20 dry weight percent of additives, wherein the dry weight percent of the alkali metal silicate binder, the ceramic fillers and the additives add up to 100%, and one of a solvent and suspension agent.
摘要翻译： 用于生产隔热涂层的贴剂或条带的浆料制剂包括20-60干重的碱金属硅酸盐粘合剂，40-80重量％的陶瓷填料，其包括至少一种选自以下的陶瓷填料： 氧化钇稳定的氧化锆和氧化镁，0-20重量％的添加剂，其中碱金属硅酸盐粘合剂，陶瓷填料和添加剂的干重百分比加起来为100％，以及溶剂和悬浮剂之一。
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公开(公告)号：US08413449B2
公开(公告)日：2013-04-09
申请号：US12857171
申请日：2010-08-16
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F23R2900/03045
摘要： A thermal machine includes a hot gas channel; a shell bounding the hot gas channel; a cooling shirt surrounding the shell; and a cooling channel disposed between the shell and the cooling shirt and configured to convection cool the hot gas channel with a cooling medium, wherein the cooling shirt includes at least one local divergence in the guidance of the cooling medium so as to compensate for non-uniformities in at least one of a thermal load on the shell and a flow of the cooling medium in the cooling channel.
摘要翻译： 热机器包括热气通道; 封闭热气通道的壳体; 围绕外壳的冷却衬衫; 以及冷却通道，其设置在所述外壳和所述冷却衬衫之间并且被配置为用冷却介质对所述热气体通道进行对流，其中所述冷却衬衫在所述冷却介质的引导中包括至少一个局部散度， 在壳体上的热负荷和冷却通道中的冷却介质流中的至少一个中的均匀性。
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10.发明申请METHOD OF MODIFYING THE COUPLING GEOMETRY IN SHROUD BAND SEGMENTS OF TURBINE MOVING BLADES 失效风力发电机组风力发电机组耦合几何调整方法公开(公告)号：US20100077586A1
公开(公告)日：2010-04-01
申请号：US12633541
申请日：2009-12-08
申请人： Hartmut Haehnle , Christoph Nagler , Ingo Schwarz
发明人： Hartmut Haehnle , Christoph Nagler , Ingo Schwarz
IPC分类号： B23P17/04
CPC分类号： F01D5/005 , F01D5/225 , Y10T29/49316 , Y10T29/49318 , Y10T29/49336 , Y10T29/49716
摘要： A method of modifying an existing casting mold for a turbine moving blade having a shroud band segment with an initial coupling geometry for coupling with a further shroud band segment, the coupling geometry having an initial coupling angle of the shroud band segment relative to a circumferential direction of the turbine, includes calculating a modified coupling geometry for the shroud band segment, the modified coupling geometry including a modified coupling angle of the shroud band segment relative to the circumferential direction. The method further includes creating at least one of a removal zone and an application zone, wherein the creating of the removal zone includes removing a first amount of casting mold material from the removal zone and wherein the creating of the application zone includes applying a second amount of an additional casting mold material to the application zone, wherein the removing and the applying steps result in the casting mold having the modified coupling angle.
摘要翻译： 一种用于涡轮机动叶片的现有铸模的修改方法，所述铸造模具具有具有初始耦合几何形状的护罩带段，用于与另一护罩带段联接，所述耦合几何形状具有护罩带段相对于圆周方向的初始耦合角度 所述涡轮机包括计算用于所述护罩带段的改进的联接几何形状，所述改进的联接几何形状包括所述护罩带段相对于所述圆周方向的改进的联接角度。 所述方法还包括产生去除区域和施用区域中的至少一个，其中所述去除区域的产生包括从所述去除区域移除第一量的铸模材料，并且其中所述施加区域的产生包括施加第二量 的额外的铸模材料施加到施加区域，其中移除和施加步骤导致具有改变的联接角度的铸模。
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