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1. 发明申请

WO2013011126A2 HEAT SHIELD ELEMENT, GAS TURBINE 审中-公开
标题翻译：热风元件，气体涡轮
公开(公告)号：WO2013011126A2
公开(公告)日：2013-01-24
申请号：PCT/EP2012/064286
申请日：2012-07-20
申请人： SIEMENS AKTIENGESELLSCHAFT , SZIJARTO, Janos , GRANBERG, Per , UTRIAINEN, Esa
发明人： SZIJARTO, Janos , GRANBERG, Per , UTRIAINEN, Esa
IPC分类号： F01D11/08 , F01D25/14
CPC分类号： F01D11/08 , F05C2201/0463 , F05C2201/0466 , F05D2230/13 , F05D2230/22 , F05D2240/11 , F05D2250/185 , F05D2250/25 , F05D2260/221
摘要： The invention relates to a heat shield element (HS) for a gas turbine (GT) comprising an areal wall section (WS), which extends with regard to a central axis (CA) in an axial direction and a circumferential direction (CD), said wall section (WS) being defined by limiting edges of the heat shield element (HS), said wall section (WS) is of a defined thickness (TH), said thickness depending on the axial and circumferential position extending radially from an inner surface (IS) to an outer surface (OS) said inner surface (IS) is exposed to a hot gas path (HGP) and said outer surface (OS) is exposed to a coolant (CO) contained in a cavity (CV), wherein the heat shield element (HS) is provided with mounting elements (ME) suitable for mounting on a supporting structure (SP). To improve cooling efficiency it is proposed that cooling channels (CC) are provided through the wall of said wall section (WS) said cooling channels (CC) comprising a first section (S1) starting at the inner surface (IS), further comprising a second section (S2) extending between the inner surface (IS) and the outer surface (OS) along a length of at least three times the thickness (TH) of the wall section (WS) at that specific area of the second section and comprising a third section (S3) joining the hot gas path through the inner surface (IS) or through a limiting edge so that said cooling channels (CC) connect said cavity (CV) with the hot gas path (HGP).
摘要翻译：本发明涉及一种用于燃气轮机（GT）的隔热元件（HS），其包括相对于中心轴线（CA）在轴向和圆周方向（CD）上延伸的面壁部分（WS）所述壁部分（WS）由所述隔热元件（HS）的限制边限定，所述壁部分（WS）具有限定的厚度（TH），所述厚度取决于从内表面径向延伸的轴向和周向位置（IS）到外表面（OS），所述内表面（IS）暴露于热气路径（HGP），并且所述外表面（OS）暴露于包含在空腔（CV）中的冷却剂（CO），其中隔热元件（HS）设置有适于安装在支撑结构（SP）上的安装元件（ME）。为了提高冷却效率，提出通过所述壁部（WS）的壁提供冷却通道（CC），所述冷却通道（CC）包括从内表面（IS）开始的第一部分（S1），还包括所述第二部分（S2）在所述第二部分的所述特定区域处沿所述壁部分（WS）的厚度（TH）的至少三倍的长度在所述内表面（IS）和所述外表面（OS）之间延伸，并且包括第三部分（S3），其通过内表面（IS）或通过限制边缘接合热气路径，使得所述冷却通道（CC）将所述空腔（CV）与热气路径（HGP）连接。

2. 发明申请

WO2013041451A1 STATOR RING FOR A TURBOMACHINE AND A METHOD FOR OPERATION OF THE STATOR RING 审中-公开
标题翻译：用于涡轮机的定子环和定子环的操作方法
公开(公告)号：WO2013041451A1
公开(公告)日：2013-03-28
申请号：PCT/EP2012/068035
申请日：2012-09-14
申请人： SIEMENS AKTIENGESELLSCHAFT , SZIJARTO, Janos
发明人： SZIJARTO, Janos
IPC分类号： F01D9/04 , F01D25/06 , F01D25/24
CPC分类号： F01D9/041 , F01D25/06 , F01D25/246 , F05D2260/96
摘要： The invention relates to a stator ring (150) for a turbo machine (10) and a method for operation of the stator ring (150). The stator ring (150) is coupled with a vane (155) by means of a coupling means. An adjustment means (170) is provided on the stator ring (150) in a manner such that it interacts with the vane (155). The actuation of the adjusting means (170) influences the vibrations of the vane (155) during the operation of the turbomachine (10).
摘要翻译：本发明涉及一种用于涡轮机（10）的定子环（150）和定子环（150）的操作方法。定子环（150）通过联接装置与叶片（155）联接。调节装置（170）以与叶片（155）相互作用的方式设置在定子环（150）上。在涡轮机（10）的操作期间，调节装置（170）的致动影响叶片（155）的振动。

3. 发明申请

WO2013011126A3 HEAT SHIELD ELEMENT FOR A GAS TURBINE 审中-公开
标题翻译：燃气轮机热风元件
公开(公告)号：WO2013011126A3
公开(公告)日：2013-05-30
申请号：PCT/EP2012064286
申请日：2012-07-20
申请人： SIEMENS AG , SZIJARTO JANOS , GRANBERG PER , UTRIAINEN ESA
发明人： SZIJARTO JANOS , GRANBERG PER , UTRIAINEN ESA
IPC分类号： F01D11/08 , F01D25/14
CPC分类号： F01D11/08 , F05C2201/0463 , F05C2201/0466 , F05D2230/13 , F05D2230/22 , F05D2240/11 , F05D2250/185 , F05D2250/25 , F05D2260/221
摘要： Heat shield element (HS) for a gas turbine (GT) comprising an areal wall section (WS), said wall section (WS) being defined by limiting edges of the heat shield element (HS), and having a defined thickness (TH) extending radially from an inner surface (IS) to an outer surface (OS) said inner surface (IS) is exposed to a hot gas path (HGP) and said outer surface (OS) is exposed to a coolant (CO). To improve cooling efficiency, cooling channels (CC) are provided through the wall of said wall section (WS) said cooling channels (CC) comprising a first section (SI) starting at the inner surface (IS), further comprising a second section (S2) extending between the inner surface (IS) and the outer surface (OS) along a length of at least three times the thickness (TH) of the wall section (WS) at that specific area of the second section and comprising a third section (S3) joining the hot gas path so that said cooling channels (CC) connect said cavity (CV) with the hot gas path (HGP).
摘要翻译：一种用于燃气轮机（GT）的隔热元件（HS），其包括一个侧壁部分（WS），所述壁部分（WS）由限制边缘限定，并具有限定的厚度（TH）从内表面（IS）径向延伸到外表面（OS），所述内表面（IS）暴露于热气路径（HGP），所述外表面（OS）暴露于冷却剂（CO）。为了提高冷却效率，通过所述壁部分（WS）的壁提供冷却通道（CC），所述冷却通道（CC）包括从内表面（IS）开始的第一部分（SI），还包括第二部分 S2）在所述第二部分的所述特定区域处沿着所述壁部分（WS）的厚度（TH）的至少三倍的长度在所述内表面（IS）和所述外表面（OS）之间延伸，并且包括第三部分（S3）接合热气路径，使得所述冷却通道（CC）将所述空腔（CV）与热气路径（HGP）连接。

4. 发明申请

WO2012019975A1 GAS TURBINE VANE 审中-公开
标题翻译：气体涡轮风扇
公开(公告)号：WO2012019975A1
公开(公告)日：2012-02-16
申请号：PCT/EP2011/063557
申请日：2011-08-05
申请人： SIEMENS AKTIENGESELLSCHAFT , SZIJARTO, Janos
发明人： SZIJARTO, Janos
IPC分类号： F01D5/18
CPC分类号： F01D5/189
摘要： The invention relates to a gas turbine vane (GTV) comprising an airfoil (AF) extending along a central axis (X) comprising a top platform (PLT) and further comprising a bottom platform (PLB) of a basic body (BB) both attached to said airfoil (AF) through a transition portion (TR), wherein said top platform (PLT) and said bottom platform (PLB) are both provided with a cavity (CV, TCV, BCV) connected by an airfoil cavity (AFCV) provided in said airfoil (AF), wherein said cavities (AFCV, TCV, BCV) are supplied with cooling air (A) for cooling said basic body (BB), wherein an airfoil insert (AFINS) is provided in the airfoil cavity (AFCV), said airfoil insert (AFINS) channels the cooling air (A) basically along said central axis (X) and is furnished with impingement holes (IH) facing an inner surface (IS) of the basic body (BB) to cool said basic body (BB) by a jet of cooling air (A). To improve secondary air efficiency the invention proposes that said inner surface (IS) of said basic body (BB) is provided with a defined convex radius (RADI) in at least one of said transition portions (TR, TTR, BTR) that an insert ( INS ) extends along said inner surface (IS) of said transition portion (TR) and that the insert (INS) is provided with impingement holes (IH) facing said inner surface (IS) to cool said basic body (BB) by a jet of cooling air (A).
摘要翻译：本发明涉及一种燃气轮机叶片（GTV），其包括沿着包括顶部平台（PLT）的中心轴线（X）延伸的翼型件（AF），并且还包括基本主体（BB）的底部平台（PLB）通过过渡部分（TR）到所述翼型件（AF），其中所述顶部平台（PLT）和所述底部平台（PLB）均设置有通过提供的翼型腔（AFCV）连接的空腔（CV，TCV，BCV）在所述翼型（AF）中，其中所述空腔（AFCV，TCV，BCV）被供应有用于冷却所述基体（BB）的冷却空气（A），其中翼型插入件（AFINS）设置在翼型腔（AFCV）所述翼型插入件（AFINS）基本上沿着所述中心轴线（X）通道冷却空气（A），并且配有面向基体（BB）的内表面（IS）的冲击孔（IH），以冷却所述基体（BB）由冷却空气（A）喷射。为了提高二次空气效率，本发明提出，所述基体（BB）的所述内表面（IS）在所述过渡部分（TR，TTR，BTR）中的至少一个中设置有限定的凸半径（RADI）（INS）沿着所述过渡部分（TR）的所述内表面（IS）延伸，并且插入件（INS）设置有面向所述内表面（IS）的冲击孔（IH），以使所述基体（BB）冷却所述基体喷气冷却空气（A）。

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