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1. 发明公开

EP2010773A2 TURBINENSCHAUFEL FÜR EINE TURBINE 有权
标题翻译： BLADE用于涡轮
公开(公告)号：EP2010773A2
公开(公告)日：2009-01-07
申请号：EP07726757.3
申请日：2007-03-09
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： BEECK, Alexander Ralph , HOFFMANN, Stefan
IPC分类号： F02C3/16 , F01D5/18 , F02K3/08 , F02K3/10 , F01D9/06 , F23R3/28
CPC分类号： F23R3/14 , F01D5/18 , F01D9/065 , F02C3/16 , F02K3/08 , F02K3/10 , F23C2900/07001 , F23R3/286
摘要： The invention relates to a blade (20) for a turbine comprising a blade wall (30, 32), a first channel (36) for guiding a first medium (M1) and a second channel (38) for guiding a second medium (M2) that can be supplied to the turbine blade (20) separately from the first medium (M1). In order to combine both media (M1, M2), which are supplied separately, into one mixture, the turbine blade (20) has least one chamber (40) which is arranged in the interior or in the blade wall (32, 34) and said chamber is connected to said channels (36, 38) via a respective connection line (42, 44). In order to provide a particularly simple component that is eco

2. 发明公开

EP3551853A1 LEITSCHAUFEL FÜR EINE STRÖMUNGSMASCHINE 有权转让
公开(公告)号：EP3551853A1
公开(公告)日：2019-10-16
申请号：EP18707247.5
申请日：2018-02-06
申请人： Siemens Aktiengesellschaft
发明人： BEECK, Alexander Ralph , BOLMS, Hans-Thomas
IPC分类号： F01D11/00 , F01D11/02 , F01D25/12

3. 发明授权

EP2010757B1 TURBINENSCHAUFEL 有权
标题翻译：涡轮叶片
公开(公告)号：EP2010757B1
公开(公告)日：2013-06-19
申请号：EP07726359.8
申请日：2007-02-13
申请人： Siemens Aktiengesellschaft
发明人： BEECK, Alexander Ralph , HOFFMANN, Stefan
IPC分类号： F01D5/18 , F02K3/08 , F01D9/06 , F02C3/16 , F01D5/14
CPC分类号： F01D5/145 , F01D5/186 , F01D5/187 , F01D5/189 , F01D9/065 , F02C3/16 , F02K3/08 , F05D2240/122 , F05D2240/124 , F05D2250/25 , F05D2260/204

4. 发明公开

EP3292277A1 TURBINE AIRFOIL WITH INTERNAL COOLING CHANNELS 审中-公开
标题翻译：涡轮机内部冷却通道
公开(公告)号：EP3292277A1
公开(公告)日：2018-03-14
申请号：EP15722021.1
申请日：2015-05-07
申请人： Siemens Aktiengesellschaft
发明人： MARTIN, Jr., Nicholas F. , MERRILL, Gary B. , MILLER, Jr., Samuel R. , BEECK, Alexander Ralph
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/20 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/81 , F05D2260/20 , F05D2260/2212 , F05D2260/22141
摘要： A turbine airfoil (10) with an internal cooling system (12) having one or more bladders (14) forming near-wall cooling channels (16) is disclosed. The bladder (14) may be conformed to a shape of an inner surface (44) forming a cavity (18) within the internal cooling system (12). One or more standoff ribs (56) may extend radially inward from the inner surface (44) forming the cavity (18) to maintain the bladder (14) in position off of the inner surface (44) so that the near-wall cooling channel (16) is formed between the bladder (14) and the inner surface (44). The near-wall cooling channel (16) may be formed by inserting a bladder (14) into the cavity (18) in a first insertable position (22) and expanding the bladder (14) into a second expanded position (24). In at least one embodiment, the chamber (26) formed by the bladder (14) may be dead space that does not contain cooling fluids as a part of the cooling system (12).

5. 发明公开

EP3191241A1 HYBRID DIE CAST SYSTEM FOR FORMING A COMPONENT USABLE IN A GAS TURBINE ENGINE 审中-公开
标题翻译：用于形成可用于燃气涡轮发动机的部件的混合压铸系统
公开(公告)号：EP3191241A1
公开(公告)日：2017-07-19
申请号：EP14780658.2
申请日：2014-09-08
申请人： Siemens Aktiengesellschaft
发明人： BEECK, Alexander Ralph , JAMES, Allister William , MERRILL, Gary B.
IPC分类号： B22D17/22
CPC分类号： B22D17/229 , B22D17/22 , B22D17/2218 , B22D17/32
摘要： A hybrid die cast system (10) having an inner liner insert (12) that enables the configuration of a component (18) produced by the system (10) to be easily changed by changing the inner liner insert (12) without having to rework the die housing (16) is disclosed. Because the inner liner insert (12) only need be removed and replaced to change the configuration of an outer surface (18) of a component (18) produced by the system (10), the cost savings is significant in contrast with conventional systems in which the die would have to be reworked. The system (10) may also include a cooling system (20) for controlling the casting process by controlling the rate of solidification and the rate of cooling of the casting. Local heating and cooling may be used to control the microstructure, enhance mold fill and reduce casting defects such as porosity.
摘要翻译：具有内衬垫插入物（12）的混合压铸系统（10）能够通过改变内衬垫插入物（12）容易地改变由系统（10）产生的部件（18）的构造，而不必返工公开了模具外壳（16）。由于内衬垫插入件（12）仅需要被移除和替换以改变由系统（10）产生的部件（18）的外表面（18）的构造，与传统系统相比，成本节约显着死亡将不得不重新工作。系统（10）还可以包括用于通过控制铸件的凝固速率和冷却速率来控制铸造过程的冷却系统（20）。局部加热和冷却可用于控制微观结构，增强模具填充并减少铸造缺陷，如孔隙率。

6. 发明授权

EP2010773B1 TURBINENSCHAUFEL FÜR EINE TURBINE 有权
标题翻译： BLADE用于涡轮
公开(公告)号：EP2010773B1
公开(公告)日：2010-09-01
申请号：EP07726757.3
申请日：2007-03-09
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： BEECK, Alexander Ralph , HOFFMANN, Stefan
IPC分类号： F02C3/16 , F01D5/18 , F02K3/08 , F02K3/10 , F01D9/06 , F23R3/28
CPC分类号： F23R3/14 , F01D5/18 , F01D9/065 , F02C3/16 , F02K3/08 , F02K3/10 , F23C2900/07001 , F23R3/286
摘要： The invention relates to a blade (20) for a turbine comprising a blade wall (30, 32), a first channel (36) for guiding a first medium (M1) and a second channel (38) for guiding a second medium (M2) that can be supplied to the turbine blade (20) separately from the first medium (M1). In order to combine both media (M1, M2), which are supplied separately, into one mixture, the turbine blade (20) has least one chamber (40) which is arranged in the interior or in the blade wall (32, 34) and said chamber is connected to said channels (36, 38) via a respective connection line (42, 44). In order to provide a particularly simple component that is eco

7. 发明公开

EP2010757A1 TURBINENSCHAUFEL 有权
标题翻译：涡轮叶片
公开(公告)号：EP2010757A1
公开(公告)日：2009-01-07
申请号：EP07726359.8
申请日：2007-02-13
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： BEECK, Alexander Ralph , HOFFMANN, Stefan
IPC分类号： F01D5/18 , F02K3/08 , F01D9/06 , F02C3/16 , F01D5/14
CPC分类号： F01D5/145 , F01D5/186 , F01D5/187 , F01D5/189 , F01D9/065 , F02C3/16 , F02K3/08 , F05D2240/122 , F05D2240/124 , F05D2250/25 , F05D2260/204
摘要： The invention relates to a turbine blade (10) comprising a profiled vane (16) around which working gas (22) can flow. Said vane has a front edge (18) which can be cross-flown by the working gas (22) and a rear edge (20) on which the working gas can flow away from, and a first channel system (30) and a second channel system (40) for guiding two different guideable media (M1, M2) which are separated from the turbine blade (10). The first channel system (30) has an outlet (48) which is arranged in at least one first area of the rear edge (20) in order to blow the first media (M1) into the working gas. The aim of the invention is to provide a turbine blade (10) for a gas turbine. Combustion taking place inside is reduced in a safe manner in order to maintain the service life of the turbine blade (10) and to prevent damage in the gas turbine, such that the first outlets (48) connected to the first channel system are arranged in the region of the rear edge (20) and at least one second outlet (52) which is arranged in the region of the rear edge (20) and which is used to blow out the second medium (M2) is connected to the second channel system (40).

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