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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

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）。

4. 发明申请

WO2016206944A1 TURBINE ASSEMBLY 审中-公开
标题翻译：涡轮总成
公开(公告)号：WO2016206944A1
公开(公告)日：2016-12-29
申请号：PCT/EP2016/062581
申请日：2016-06-03
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： HULL, Henrik , SZIJARTO, Janos
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/211 , F05D2240/122 , F05D2240/126 , F05D2240/127 , F05D2240/304
摘要： The present invention relates to a turbine assembly (10) comprising at least one basically hollow aerofoil (12) with at least one trailing edge (14) comprising at least two wall segments (16, 18) that each comprises an inner surface (20, 22), wherein the inner surfaces (20, 22) face each other, and wherein the inner surfaces (20, 22) enclose at least one exit aperture (24) extending basically in span wise direction (26) of the at least one basically hollow aerofoil (12), wherein at least one of the inner surfaces (20, 22) of the at least two wall segments (16, 18) of the trailing edge (14) comprises at least one surface increasing structure (28, 28') extending partially into the at least one exit aperture (24) from one inner surface (20, 22) to the other inner surface (20, 22), wherein the turbine assembly further comprises at least one cooling passage (32, 32') for a cooling medium (34) discharging in the at least one exit aperture (24) and wherein the at least one cooling passage (32, 32') has an exit opening (40) and wherein the at least one exit aperture (24) has a depth (D) in a direction (42) basically perpendicular to a span wise direction (26) of the basically hollow aerofoil (12) and wherein the at least one surface increasing structure (28, 28') has a longitudinal extension (44) with a forward end (46) and a rear end (48) and wherein the at least one surface increasing structure (28, 28') extends from its forward end (46) to its rear end (48) along the depth (D) of the at least one exit aperture (24) and wherein the forward end (46) of the at least one surface increasing structure (28, 28') is arranged in the exit opening (40) of the at least one cooling passage ( 32, 32 ') · This provides a sufficient heat transfer and thus cooling of the turbine assembly (10).
摘要翻译：本发明涉及一种涡轮机组件（10），其包括至少一个基本上是中空的机翼（12），至少一个后缘（14）包括至少两个壁段（16,18），每个壁段包括一个内表面 22），其中所述内表面（20,22）彼此面对，并且其中所述内表面（20,22）包围至少一个基本上沿所述至少一个的跨度方向（26）延伸的出口孔（24）中空翼型件（12），其中后缘（14）的至少两个壁段（16,18）的至少一个内表面（20,22）包括至少一个表面增加结构（28,28' ）从一个内表面（20,22）部分地延伸到所述至少一个出口孔（24）到另一个内表面（20,22），其中所述涡轮机组件还包括至少一个冷却通道（32,32'），对于在所述至少一个出口孔（24）中排放的冷却介质（34），并且其中所述至少一个冷却通道，32'）具有出口开口（40），并且其中所述至少一个出口孔（24）在基本上垂直于所述基本上中空的机翼的跨度方向（26）的方向（42）上具有深度（D） 12），并且其中所述至少一个表面增加结构（28,28'）具有带有前端（46）和后端（48）的纵向延伸部（44），并且其中所述至少一个表面增加结构（28， 28'）沿着所述至少一个出口孔（24）的深度（D）从其前端（46）延伸到其后端（48），并且其中所述至少一个表面增大结构（28,28'）布置在所述至少一个冷却通道（32,32'）的出口（40）中。这提供了足够的热传递并且因此冷却涡轮组件（10）。

5. 发明申请

WO2014146827A1 A TURBOMACHINE COMPONENT WITH A STRESS RELIEF CAVITY 审中-公开
标题翻译：具有应力消除空气的涡轮机组件
公开(公告)号：WO2014146827A1
公开(公告)日：2014-09-25
申请号：PCT/EP2014/052547
申请日：2014-02-10
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： HÄGGMARK, Anders , SZIJARTO, Janos
IPC分类号： F01D11/00
CPC分类号： F01D5/18 , B23H9/10 , F01D9/041 , F01D11/006 , F05D2220/30 , F05D2230/10 , F05D2240/12 , F05D2240/122 , F05D2240/30 , F05D2240/304 , F05D2240/80 , F05D2260/94 , F05D2260/941
摘要： A turbomachine component with a stress relief cavity A turbomachine component (1) with a stress relief cavity (30) is provided. The turbomachine component contains an airfoil (10) and a platform (20). The airfoil contains a trailing edge (28). The platform contains a trailing edge region (25), a seal strip slot (40) and a stress relief cavity (30). The trailing edge region (25) supports at least a part of the trailing edge (28). The stress relief cavity (30) extends inside the platform into the trailing edge region (25) and is an extension of the seal strip slot (40).
摘要翻译：具有应力消除腔的涡轮机组件提供具有应力消除腔（30）的涡轮机组件（1）。涡轮机组件包含翼型件（10）和平台（20）。机翼包含后缘（28）。平台包括后缘区域（25），密封条槽（40）和应力消除腔（30）。后缘区域（25）支撑后缘（28）的至少一部分。应力消除腔（30）在平台内延伸到后缘区域（25）内，并且是密封条槽（40）的延伸部分。

6. 发明申请

WO2018036719A1 A TURBOMACHINE ARRANGEMENT WITH A PLATFORM COOLING DEVICE FOR A BLADE OF A TURBOMACHINE 审中-公开
标题翻译：一种用于涡轮机叶片的平台式冷却装置的涡轮机装置
公开(公告)号：WO2018036719A1
公开(公告)日：2018-03-01
申请号：PCT/EP2017/067909
申请日：2017-07-14
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： HJALMARSSON, Christer , JOHANSSON, Martina , SZIJARTO, Janos
IPC分类号： F01D5/08 , F02C7/18
摘要： A turbomachine arrangement with a platform cooling device for a blade of a turbomachine The invention is directed to a turbomachine arrangement comprising a blade (1) of a turbomachine and a platform cooling device (10) for the blade (1) configured to be positioned at a platform (9) of the blade (1). The platform cooling device (10) comprises a peripheral edge (11) configured to be in contact with the platform (9); a first surface portion (31) configured to form a first cavity (41) between the platform cooling device (10) and the platform (9), the first surface portion (31) comprising a plurality of impingement holes (20) configured to impinge onto the platform (9) during operation of the turbomachine; a second surface portion (32) configured to form a second cavity (42) between the platform cooling device (10) and the platform (9); and a barrier (14) configured to be in contact with the platform (9), the barrier (14) forming a connection between two sections (15, 16) of the edge (11) and separating the first cavity (41) from the second cavity (42) fluidically. The platform cooling device (10) and the blade (1) are separately manufactured components, and the platform cooling device (10) is connected at the edge (11) to the blade (1), such that the first cavity (41) and the second cavity (42) are formed between the platform cooling device (10) and the blade (1). The blade (1) comprises a cooling fluid supply passage (17), connecting a hollow blade core (26) and the second cavity (42), for supplying of cooling fluid to the second cavity (42) during operation, and the first cavity (41) is supplied, during operation, with cooling fluid via the impingement holes (20) of the first surface portion (31).
摘要翻译：具有用于涡轮机叶片的平台冷却装置的涡轮机装置技术领域本发明涉及一种涡轮机装置，其包括涡轮机叶片（1）和用于叶片的平台冷却装置（10）（1）构造成定位在所述叶片（1）的平台（9）处。平台冷却装置（10）包括构造成与平台（9）接触的外围边缘（11）; （31），所述第一表面部分（31）构造成在所述平台冷却装置（10）与所述平台（9）之间形成第一腔体（41），所述第一表面部分（31）包括多个冲击孔（20）在涡轮机运行期间到平台（9）上; 第二表面部分（32），其被配置为在所述平台冷却装置（10）和所述平台（9）之间形成第二腔体（42）; 以及构造成与所述平台（9）接触的障碍物（14），所述障碍物（14）在所述边缘（11）的两个区段（15,16）之间形成连接并且将所述第一空腔（41）与所述平台第二空腔（42）。平台冷却装置（10）和叶片（1）是分开制造的部件，平台冷却装置（10）在边缘（11）处连接到叶片（1），使得第一腔室（41）和第二腔体（42）形成在平台冷却装置（10）和刀片（1）之间。叶片（1）包括连接中空叶片芯（26）和第二空腔（42）的冷却流体供应通道（17），用于在操作期间向第二空腔（42）供应冷却流体，并且第一空腔（41）在操作期间经由第一表面部分（31）的冲击孔（20）供应冷却流体。

7. 发明申请

WO2015180945A1 TURBOMACHINE WITH A SEAL FOR SEPARATING WORKING FLUID AND COOLANT FLUID OF THE TURBOMACHINE AND USE OF THE TURBOMACHINE 审中-公开
标题翻译：涡轮发动机用于分离涡轮机的工作流体和冷却剂流体和涡轮发动机的使用
公开(公告)号：WO2015180945A1
公开(公告)日：2015-12-03
申请号：PCT/EP2015/060182
申请日：2015-05-08
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： GRANBERG, Per , SZIJARTO, Janos
IPC分类号： F01D9/04 , F02C7/28
CPC分类号： F01D11/003 , F01D5/02 , F01D9/041 , F01D15/10 , F01D25/12 , F02C7/28 , F05D2220/31 , F05D2220/32
摘要： Subject matter of the invention is a turbomachine as well as a use of the turbomachine. The turbomachine, for instance a gas turbine or a steam turbine, comprises a stator with at least one stator component, a rotor with at least one rotor component, at least one cavity between the rotor and the stator and at least one working fluid channel for channeling a working fluid for driving the rotor, wherein the working fluid channel is bordered by the stator component and the rotor component. The stator component comprises at least one coolant fluid channel for cooling the stator component with the aid of a coolant fluid and at least one separation barrier is arranged between the cavity and the coolant fluid channel for separating the working fluid channel and the coolant fluid channel from each other. The separation barrier comprises at least two piston rings, the two piston rings are axially arranged to each other defining a piston ring space between the piston rings. The piston ring space is a part of the coolant fluid channel and the piston rings are in sliding contact with a first one of the stator component.
摘要翻译：本发明的主题是涡轮机以及涡轮机的用途。涡轮机械，例如燃气轮机或汽轮机，包括具有至少一个定子部件的定子，具有至少一个转子部件的转子，转子和定子之间的至少一个腔，以及至少一个工作流体通道，用于引导用于驱动转子的工作流体，其中工作流体通道由定子部件和转子部件界定。定子部件包括至少一个冷却剂流体通道，用于借助于冷却剂流体冷却定子部件，并且至少一个分离屏障布置在腔体和冷却剂流体通道之间，用于将工作流体通道和冷却剂流体通道从彼此。隔离层包括至少两个活塞环，两个活塞环彼此轴向布置，限定活塞环之间的活塞环空间。活塞环空间是冷却剂流体通道的一部分，并且活塞环与定子部件中的第一个滑动接触。

8. 发明申请

WO2014184302A1 A SEAL FOR A TURBOMACHINE AND A METHOD FOR CONSTRUCTION THEREOF 审中-公开
标题翻译：一种涡轮发动机的密封及其构造方法
公开(公告)号：WO2014184302A1
公开(公告)日：2014-11-20
申请号：PCT/EP2014/059978
申请日：2014-05-15
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SZIJARTO, Janos
IPC分类号： F01D11/00 , F16J15/06 , F01D9/04 , F01D25/24 , F16J15/08
CPC分类号： F01D11/005 , F01D9/041 , F01D25/246 , F05D2240/11 , F16J15/0887
摘要： A seal (80, 85) for a turbomachine and method for construction thereof is elucidated in the present invention. The seal (80, 85) and the embodiments elucidated thereof is for the purpose of sealing gaps (90) between a vane (35) and a stator ring (15) of the turbomachine. The seal (80, 85) comprises a first portion (93, 94) and a second portion (95, 96). A first sealing surface (102, 104) of the first portion (93, 94) contacts a stator ring surface (30) of the stator ring (15). A second sealing surface (106, 108) of the second portion (95, 96) contacts a vane surface (40) of the vane (35), and the second sealing surface (106) is located at a tip (160) of the second portion (95). One of the portions (95, 96) is more flexible compared to the other portion (93, 94). The flexible portion (95, 96) conforms to the relative displacement of the vane (35) and the stator ring (15) during the operation of the turbomachine such that the aforementioned contacts for sealing are maintained.
摘要翻译：在本发明中阐述了用于涡轮机的密封件（80,85）及其构造方法。密封件（80,85）及其阐述的实施例是为了密封涡轮机的叶片（35）和定子环（15）之间的间隙（90）。密封件（80,85）包括第一部分（93,94）和第二部分（95,96）。第一部分（93,94）的第一密封表面（102,104）接触定子环（15）的定子环表面（30）。第二部分（95,96）的第二密封表面（106,108）接触叶片（35）的叶片表面（40），并且第二密封表面（106）位于叶片第二部分（95）。部分（95,96）中的一个比其他部分（93,94）更灵活。柔性部分（95,96）在涡轮机操作期间符合叶片（35）和定子环（15）的相对位移，使得保持上述用于密封的接触件。

9. 发明申请

WO2014106598A1 BLADE FOR A TURBOMACHINE 审中-公开
标题翻译：用于涡轮机的叶片
公开(公告)号：WO2014106598A1
公开(公告)日：2014-07-10
申请号：PCT/EP2013/077812
申请日：2013-12-20
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SZIJARTO, Janos , UTRIAINEN, Esa , ALMROTH, Per , HASSELQVIST, Magnus , WANG, Lieke
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B22C9/04 , B22C9/10 , F01D5/186 , F05D2230/211
摘要： A blade (1) of a turbomachine is presented. The blade (1) includes an airfoil portion (2) and a root portion (3), the airfoil portion (2) comprising a pressure side (6) and a suction side (7) extending between a leading edge (4) and a trailing edge (5) of the airfoil portion (2), characterized in that the airfoil portion (2) comprises a cooling arrangement having an inlet system (28) for introducing cooling fluid (26) into the airfoil (2) for cooling the airfoil (2), at least one first cooling passage (20, 40, 68) for conducting cooling fluid in a direction from the trailing edge (5) to the leading edge (4) on the suction side (7), wherein the first cooling passage (20, 40, 68) is fluidly connected to the inlet system (28), at least one second cooling passage (31, 50, 69) for conducting cooling fluid in a direction from the leading edge (4) to the trailing edge (5) on the pressure side (6), wherein the second cooling passage (31, 50, 69) is fluidly connected to the inlet system (28) and wherein the cooling fluid (26) flowing in the second cooling passage (31, 50, 69) is directed out of the airfoil portion (2) through an opening (13) at the trailing edge (5).
摘要翻译：提出了一种涡轮机的叶片（1）。叶片（1）包括翼型部分（2）和根部部分（3），翼型部分（2）包括压力侧（6）和吸引侧（7），其在前缘（4）和机翼部分（2）的后缘（5），其特征在于，翼型部分（2）包括具有用于将冷却流体（26）引入翼型件（2）中以冷却翼型件的入口系统（28）的冷却装置（2），至少一个第一冷却通道（20,40,68），用于沿着从后缘（5）到吸入侧（7）上的前缘（4）的方向传导冷却流体，其中第一冷却通道（20,40,68）流体连接到入口系统（28），至少一个第二冷却通道（31,50,69），用于在从前缘（4）到后缘（4）的方向上传导冷却流体（5）在所述压力侧（6）上，其中所述第二冷却通道（31,50,69）流体地连接到所述入口系统（28），并且其中所述冷却流体（26）流入第二冷却通道（31,50,69）通过在后缘（5）处的开口（13）从翼型部分（2）引出。

10. 发明申请

WO2014075895A1 TURBINE BLADE WITH COOLING ARRANGEMENT 审中-公开
标题翻译：涡轮叶片与冷却布置
公开(公告)号：WO2014075895A1
公开(公告)日：2014-05-22
申请号：PCT/EP2013/072377
申请日：2013-10-25
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SZIJARTO, Janos , UTRIAINEN, Esa
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2260/201
摘要： A turbine blade (100) with a cooling arrangement is disclosed. The turbine blade (100) includes at least one supply chamber (202, 202') and at least one impingement cavity (CI, CI'). The supply chamber (202, 202') includes multiple impingement channels (204) configured to direct a cooling fluid from within the supply chamber (202, 202') to the impingement cavity (CI, CI'). The supply chamber (202, 202') also includes one or more collector channels (206) such that the cooling fluid from the impingement cavity (CI, CI') is directed to a collector cavity (CC) within the turbine blade (100).
摘要翻译：公开了具有冷却装置的涡轮叶片（100）。涡轮叶片（100）包括至少一个供应室（202,202'）和至少一个冲击腔（CI，CI'）。供应室（202,202'）包括多个冲击通道（204），其构造成将冷却流体从供给室（202,202'）内引导到冲击腔（CI，CI'）。供应室（202,202'）还包括一个或多个收集器通道（206），使得来自冲击腔（CI，CI'）的冷却流体被引导到涡轮叶片（100）内的收集器空腔（CC）。

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