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1. 发明申请

WO2017171763A1 TURBINE AIRFOIL WITH TURBULATING FEATURE ON A COLD WALL 审中-公开
标题翻译：涡轮机翼型与冷却壁上的湍流特征
公开(公告)号：WO2017171763A1
公开(公告)日：2017-10-05
申请号：PCT/US2016/025122
申请日：2016-03-31
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MARSH, Jan H. , SANDERS, Paul A.
IPC分类号： F01D5/18
摘要： A turbine airfoil (10) includes a flow blocking body (26) positioned an internal cavity (40). A first near-wall cooling channel (72) is defined between the flow blocking body (26) and an airfoil pressure sidewall (16). A second near-wall cooling channel (74) is defined between the flow blocking body (26) and an airfoil suction sidewall (18). A connecting channel (76) is defined between the flow blocking body (26) an internal partition wall (24) that connects the airfoil pressure (16) and suction (18) sidewalls. The connecting channel (76) is connected to the first (72) and second (74) near-wall cooling channels along a radial extent. Turbulating features (90, 90a-b) are located in the connecting channel (76) and are formed on the flow blocking body (26) and/or on the partition wall (24). The turbulating features (90, 90a-b) are effective to produce a higher coolant flow rate through the first (72) and second (74) near-wall cooling channels in comparison to the connecting channel (76).
摘要翻译：涡轮翼型件（10）包括位于内腔（40）内的阻流体（26）。第一近壁冷却通道（72）被限定在阻流体（26）和翼型压力侧壁（16）之间。第二近壁冷却通道（74）限定在阻流体（26）和翼型吸入侧壁（18）之间。连接通道（76）限定在阻流体（26）和连接翼型压力（16）和抽吸（18）侧壁的内部分隔壁（24）之间。连接通道（76）沿径向延伸与第一（72）和第二（74）近壁冷却通道连接。涡流特征（90,90a-b）位于连接通道（76）中并形成在阻流体（26）上和/或分隔壁（24）上。与连接通道（76）相比，湍流部件（90,90a-b）有效地产生通过第一（72）和第二（74）近壁冷却通道的较高冷却剂流率。

2. 发明申请

WO2017039572A1 TURBINE AIRFOIL HAVING FLOW DISPLACEMENT FEATURE WITH PARTIALLY SEALED RADIAL PASSAGES 审中-公开
标题翻译：具有部分密封径向通道的流量变化特征的涡轮机
公开(公告)号：WO2017039572A1
公开(公告)日：2017-03-09
申请号：PCT/US2015/047335
申请日：2015-08-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MARSH, Jan H. , SANDERS, Paul A.
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/18 , F01D5/147 , F01D5/188
摘要： A turbine airfoil (10) includes a flow displacement element (26A-B, 26A'-B') positioned in an interior portion (11) of an airfoil body (12) between a pair of adjacent partition walls (24) and comprising a radially extending elongated main body (28). The main body (28) is spaced from the pressure and suction side walls (16, 18) and further spaced from one or both of the adjacent partition walls (24), whereby a first near wall passage (72) is defined between the main body (28) and the pressure side wall (16), a second near wall passage (74) is defined between the main body (28) and the pressure side wall (18) and a central channel (76) is defined between the main body (28) and a respective one of the adjacent partition walls (24). The central channel (76) is connected to the near wall passages (72, 74) along a radial extent. One or more radial ribs (64) are positioned in the central channel (76) that extend partially across the central channel (76) between the main body (28) and the respective adjacent partition wall (24).
摘要翻译：涡轮机翼（10）包括位于一对相邻分隔壁（24）之间的翼型件本体（12）的内部部分（11）中的流动位移元件（26A-B，26A'-B'），径向延伸的细长主体（28）。主体（28）与压力和吸力侧壁（16,18）间隔开并且与一个或两个相邻隔壁（24）进一步间隔开，由此第一近壁通道（72）被限定在主体主体（28）和压力侧壁（16）之间，第二近壁通道（74）被限定在主体（28）和压力侧壁（18）之间，并且中心通道（76）被限定在主体主体（28）和相邻的间隔壁（24）中的相应的一个。中心通道（76）沿径向延伸连接到近壁通道（72,74）。一个或多个径向肋（64）定位在中心通道（76）中，该中心通道（76）部分地跨过主体（28）和相应的相邻分隔壁（24）之间的中心通道（76）延伸。

3. 发明申请

WO2017039569A1 TURBINE AIRFOIL WITH INTERNAL IMPINGEMENT COOLING FEATURE 审中-公开
标题翻译：具有内部冷却功能的涡轮机空气
公开(公告)号：WO2017039569A1
公开(公告)日：2017-03-09
申请号：PCT/US2015/047328
申请日：2015-08-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MARSH, Jan H. , SANDERS, Paul A.
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F05D2260/201
摘要： A turbine airfoil (10) includes an impingement structure (26A, 26B) comprising a hollow elongated main body (28) positioned in an interior portion (11) of an airfoil body (12). The main body (28) extends lengthwise along a radial direction and defines coolant cavity (64) therewithin that receives a cooling fluid (60). The main body (28) is spaced from a pressure side wall (16) and a suction side wall (18) of the airfoil body (12) and may be spaced from an airfoil tip (52), to define respective passages (72, 74, 77) therebetween. A plurality of impingement openings (25) are formed through the main body (28) that connect the coolant cavity (64) with one or more of the respective passages (72, 74, 77). The impingement openings (25) direct the cooling fluid (60) flowing in the coolant cavity (64) to impinge on the pressure and/or suction side walls (16, 18) and/or the airfoil tip (52).
摘要翻译：涡轮机翼（10）包括冲击结构（26A，26B），该冲击结构包括定位在翼型体（12）的内部部分（11）中的中空细长主体（28）。主体（28）沿着径向方向纵向地延伸并且限定其中容纳冷却流体（60）的冷却剂腔（64）。主体（28）与机翼主体（12）的压力侧壁（16）和吸力侧壁（18）间隔开，并且可与翼型件末端（52）间隔开，以限定相应的通道 74,77）。多个冲击开口（25）穿过连接冷却剂腔（64）与一个或多个相应通道（72,74,77）的主体（28）形成。冲击开口（25）引导在冷却剂腔（64）中流动的冷却流体（60）撞击压力和/或吸力侧壁（16,18）和/或翼型端头（52）。

4. 发明申请

WO2016024007A1 GAS TURBINE SYSTEM 审中-公开
标题翻译：气体涡轮机系统
公开(公告)号：WO2016024007A1
公开(公告)日：2016-02-18
申请号：PCT/EP2015/068720
申请日：2015-08-14
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： HASE, Matthias , KRISHNAN, Vaidyanathan , SANDERS, Paul A.
IPC分类号： F23R3/00 , F01D9/02
CPC分类号： F01D9/023 , F01D25/12 , F02C7/18 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R3/005 , F23R3/02 , F23R3/04 , F23R3/06 , F23R3/08 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： The present invention relates to a gas turbine system comprising a burner arrangement having a tubular combustion chamber, a turbine and a transition duct (7) connecting the combustion chamber and the turbine, wherein the transition duct (7) is provided with an axially extending cooling air channel (11), wherein the transition duct (7) is provided with a plurality of axially extending cooling air channels (11), and wherein largely each cooling air channel (11) is provided with one single inlet opened to the outside of the transition duct (7) and with one single outlet opened to the inside of the transition duct (7).
摘要翻译：本发明涉及一种燃气轮机系统，其包括具有管状燃烧室，涡轮和连接燃烧室和涡轮机的过渡管道（7）的燃烧器装置，其中过渡管道（7）设置有轴向延伸的冷却空气通道（11），其中所述过渡管道（7）设置有多个轴向延伸的冷却空气通道（11），并且其中大部分每个冷却空气通道（11）设置有一个单独的入口，其通向所述空气通道过渡管道（7）和一个单个出口向过渡管道（7）的内部开口。

5. 发明申请

WO2018080416A1 TURBINE AIRFOIL WITH NEAR WALL PASSAGES WITHOUT CONNECTING RIBS 审中-公开
标题翻译：涡轮机叶片与附近的墙壁通过没有连接RIBS
公开(公告)号：WO2018080416A1
公开(公告)日：2018-05-03
申请号：PCT/US2016/058365
申请日：2016-10-24
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SANDERS, Paul A. , TORRES GONZALEZ, Denis , GOLSEN, Matthew J.
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/187 , F01D5/147 , F01D5/18 , F01D5/188 , F05D2230/21 , F05D2230/22 , F05D2230/232 , F05D2230/237
摘要： A turbine airfoil (10) includes a radially extending hollow rib (26) positioned in a radial cavity (40) defined between chord-wise spaced partition walls (24). The hollow rib (26) is spaced from a pressure sidewall (16) and from a suction sidewall (18) to define first and second near wall passages (72, 74) respectively, and is further spaced from a respective adjacent partition wall (24) on chord-wise opposite sides to define first and second connecting passages (76, 78) respectively. The hollow rib (26) forms a first radial coolant channel (B, D) therewithin, in communication with a coolant source. The hollow rib (26) is mechanically connected to the turbine airfoil (10) at a base (50) of the hollow rib (26). The first and second near wall passages (72, 74) and the first and second connecting passages (76, 78) are interconnected along a radial extent to form a second radial coolant channel (C, E), which surrounds the first radial coolant channel (B, D) and is fluidically connected in series with the first radial coolant channel (B, D).
摘要翻译：涡轮机翼（10）包括位于径向空腔（40）中的径向延伸的中空肋（26），所述径向空腔（40）限定在弦向间隔分隔壁（24）之间。中空肋26与压力侧壁16和吸气侧壁18分隔开以分别限定第一和第二近壁通路72,74并且还与相应的相邻分隔壁24隔开）在弦向相对侧上分别限定第一和第二连接通道（76,78）。中空肋（26）在其内部形成与冷却剂源连通的第一径向冷却剂通道（B，D）。中空肋（26）在中空肋（26）的基部（50）处机械连接到涡轮翼型（10）。第一和第二近壁通道（72,74）以及第一和第二连接通道（76,78）沿径向延伸互连以形成第二径向冷却剂通道（C，E），该第二径向冷却剂通道围绕第一径向冷却剂通道（B，D）并且与第一径向冷却剂通道（B，D）串联流体连接。

6. 发明申请

WO2017171764A1 TURBINE AIRFOIL WITH INTERNAL COOLING CHANNELS HAVING FLOW SPLITTER FEATURE 审中-公开
标题翻译：具有内部冷却通道的涡轮机叶片具有流动分流器特征
公开(公告)号：WO2017171764A1
公开(公告)日：2017-10-05
申请号：PCT/US2016/025128
申请日：2016-03-31
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MARSH, Jan H. , SANDERS, Paul A. , LANDRUM, Evan C.
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/186 , F01D5/188 , F01D9/041 , F05D2220/32 , F05D2240/121 , F05D2240/122 , F05D2240/127 , F05D2240/24 , F05D2250/185 , F05D2260/202 , F05D2260/221 , F05D2260/2212
摘要： An airfoil (10) includes at least one internal cooling channel (A-F) extending in the radial direction and adjoined on opposite sides by an airfoil pressure sidewall (16) and an airfoil suction sidewall (18). An internal surface (16a) of the airfoil pressure sidewall (16) and an internal surface (18a) of the airfoil suction sidewall (18) define heat transfer surfaces in relation to a coolant flowing through the internal cooling channel (A-F). A flow splitter feature (90) is located in a flow path of the coolant in the internal cooling channel (A-F) between the pressure and suction sidewalls (16, 18). The flow splitter feature (90) is effective to create a flow separation region downstream of the flow splitter feature (90), whereby coolant flow velocity is locally increased along the internal surfaces (16a, 18a) of the pressure and suction sidewalls (16, 18).
摘要翻译：翼型（10）包括至少一个沿径向方向延伸且通过翼型压力侧壁（16）和翼型吸入侧壁（18）在相对侧上邻接的至少一个内部冷却通道（A-F）。翼型压力侧壁16的内表面16a和翼型吸入侧壁18的内表面18a限定了相对于流经内部冷却通道A-F的冷却剂的传热表面。分流器特征（90）位于压力和抽吸侧壁（16,18）之间的内部冷却通道（A-F）中的冷却剂的流动路径中。分流器特征（90）有效地在分流器特征（90）的下游形成流分离区域，由此冷却剂流动速度沿着压力和吸入侧壁（16,16）的内表面（16a，18a）局部地增加， 18）。

7. 发明申请

WO2017039571A1 INTERNALLY COOLED TURBINE AIRFOIL WITH FLOW DISPLACEMENT FEATURE 审中-公开
标题翻译：内部冷却涡轮机空气流量特性
公开(公告)号：WO2017039571A1
公开(公告)日：2017-03-09
申请号：PCT/US2015/047332
申请日：2015-08-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LANDRUM, Evan C. , MARSH, Jan H. , SANDERS, Paul A.
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/189 , F05D2250/185
摘要： A turbine airfoil (10) includes a flow displacement element (26) occupying a space between a pair of adjacent partition walls (24) in an interior portion (11) of a generally hollow airfoil body (12). The flow displacement element (26) includes an elongated main body (28) extending lengthwise in a radial direction and a pair of connector ribs (32, 34) respectively connecting the main body (28) to pressure and suction sides (16, 18) of the airfoil (10). A pair of adjacent radial flow passes (43-44, 45-46) of symmetrically opposed flow cross-sections are defined on chordally opposite sides of the flow displacement element (26). The radial flow passes (43-44, 45-46) conduct cooling fluid in opposite radial directions and are connected in series via a chordal passage (50a, 50c) defined in the interior portion (11) between the flow displacement element (26) and a radial end face (52) of the airfoil body (12), to form a serpentine cooling path (60a, 60b).
摘要翻译：涡轮机翼（10）包括位于大致中空的翼型体（12）的内部部分（11）中的一对相邻分隔壁（24）之间的空间的流动位移元件（26）。流量位移元件（26）包括沿径向纵向延伸的细长主体（28）和分别将主体（28）连接到压力侧和吸力侧（16,18）的一对连接肋（32,34）的翼型件（10）。对称相对的流动横截面的一对相邻的径向流动通道（43-44,45-46）限定在流量位移元件（26）的弦向相对侧上。径向流动通过（43-44,45-46）沿相反的径向传导冷却流体，并且经由限定在流量位移元件（26）内的内部部分（11）中的弦道（50a，50c）串联连接，和翼型件本体（12）的径向端面（52），以形成蛇形冷却通道（60a，60b）。

8. 发明申请

WO2016039716A1 INSULATING SYSTEM FOR SURFACE OF GAS TURBINE ENGINE COMPONENT 审中-公开
标题翻译：气体涡轮发动机部件表面绝缘系统
公开(公告)号：WO2016039716A1
公开(公告)日：2016-03-17
申请号：PCT/US2014/054467
申请日：2014-09-08
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： BRUNELLI, Marco Claudio Pio , MARSH, Jan H. , SANDERS, Paul A. , MATTHEWS, Ralph W. , LANDIS, Kenneth K. , RODRIGUEZ, Jose L. , MERRILL, Gary B. , MILLER, Samuel R., Jr.
IPC分类号： F01D5/18 , F01D25/08 , B64C21/10
CPC分类号： F01D5/187 , F01D25/08 , F02C7/24 , F02K1/822 , F05D2240/127 , F05D2250/294 , F05D2260/20 , F05D2260/231 , F05D2270/17 , Y02T50/675
摘要： An insulating system (10) for a gas turbine engine (12) configured to insulate a surface (14) to reduce thermal gradients within components (18) in the engine (12) is disclosed. The insulating system (10) may include one or more insulating components (18) positioned on a surface (14) of the component (18) within the gas turbine engine (12). The surface (14) may be on a component (18) within an internal cooling system in an airfoil or other appropriate location in the engine (12). The insulating component (18) may include one or more structures (24) configured to locally restrict flow of cooling fluid at the surface (14) of the component (18) within the engine (12), thereby isolating the surface (14) from the mainstream flow and effectively insulating it. Restricting the flow of fluids past the surface (14) will reduce the effective heat transfer at that location where the heating load is less than another location exposed to a cooling system, thereby reducing the thermal gradient and thermal stress and increasing the component life.
摘要翻译：公开了一种用于燃气涡轮发动机（12）的绝缘系统（10），其被配置为使表面（14）绝缘以减少发动机（12）中的部件（18）内的热梯度。绝缘系统（10）可以包括位于燃气涡轮发动机（12）内的部件（18）的表面（14）上的一个或多个绝缘部件（18）。表面（14）可以位于发动机（12）内的翼型件或其他适当位置内的内部冷却系统内的部件（18）上。绝缘部件（18）可以包括一个或多个结构（24），其构造成局部地限制在发动机（12）内的部件（18）的表面（14）处的冷却流体的流动，从而将表面（14）从主流流动并有效地保温。限制液体流过表面（14）的流动将减少加热负载小于暴露于冷却系统的另一位置的位置处的有效热传递，从而降低热梯度和热应力并增加部件寿命。

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