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    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL
    1.
    发明公开
    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL 有权
    涡轮叶片和燃气轮机这样的涡轮叶片

    公开(公告)号：EP1706593A1

    公开(公告)日：2006-10-04

    申请号：EP05706868.6

    申请日：2005-01-12

    申请人： SIEMENS AKTIENGESELLSCHAFT

    发明人： BALDAUF, Stefan ,  BOLMS, Hans-Thomas ,  HÄNDLER, Michael ,  LERNER, Christian

    IPC分类号： F01D5/22 ,  F01D11/00

    CPC分类号： F01D5/22 ,  F01D11/008 ,  F05D2240/80

    摘要： The invention relates to a turbine blade (63, 65) comprising a vane (67, 69) that runs along a blade axis (73, 75) and a platform region (61), which is located at the root of the vane (67, 69) and has a platform (71) that extends transversally to the blade axis (73, 75). The aim of the invention is to configure a delimitation (87) of a flow channel (5) of a gas turbine (1) in the simplest possible manner. To achieve this, the platform (71) is configured by an elastic sheet metal part (77, 79) that rests on the vane (67, 69). Said part leads to a gas turbine (1) comprising a flow conduit (5) that runs along an axis (3) of the gas turbine (1), said conduit having an annular cross-section for a working medium (M) and a second (9, 13) vane stage (7, 9, 11, 13) that is situated downstream of a first (7, 11) vane stage, which runs along the axis (3). According to the invention, a vane stage comprises a number of turbine blades (63, 65) that are arranged in a ring and extend radially into the flow channel (5) in accordance with the inventive concept.

    TURBINENSCHAUFEL SOWIE DEREN VERWENDUNG IN EINER GASTURBINENANLAGE
    2.
    发明公开
    TURBINENSCHAUFEL SOWIE DEREN VERWENDUNG IN EINER GASTURBINENANLAGE 失效
    涡轮叶片与它们在燃气涡轮机系统

    公开(公告)号：EP0964981A1

    公开(公告)日：1999-12-22

    申请号：EP98914796.0

    申请日：1998-02-20

    申请人： SIEMENS AKTIENGESELLSCHAFT

    发明人： SCHEURLEN, Michael ,  HÄNDLER, Michael

    IPC分类号： F01D5

    CPC分类号： F01D5/186

    摘要： The invention relates to a turbine blade (1) comprising an input flow area (8), an output flow area (9), a pressing side (10) and aspiration side (11) situated opposite each other and between said areas, and a wall structure (2) around which a fluid (18) is able to circulate. The wall structure (2) consists of an outer wall (3) which surrounds an inner chamber (21) for guiding cooling fluid (6) and has an outlet (16) for said cooling fluid (6). The outlet (16) has a thickening (14) pointing towards the inner chamber (21). The invention further relates to the use of a turbine blade (1) in a gas turbine.

    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL
    4.
    发明授权
    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL 有权
    涡轮叶片和燃气轮机这样的涡轮叶片

    公开(公告)号：EP1706592B1

    公开(公告)日：2011-03-09

    申请号：EP05700848.4

    申请日：2005-01-12

    申请人： SIEMENS AKTIENGESELLSCHAFT

    发明人： BALDAUF, Stefan ,  BOLMS, Hans-Thomas ,  HÄNDLER, Michael ,  LERNER, Christian

    IPC分类号： F01D5/22 ,  F01D11/00

    CPC分类号： F01D11/008 ,  F01D5/22 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

    摘要： The invention relates to a turbine blade (67) comprising a vane (67) that runs along a blade axis (73) and a platform region (61), which is located at the root of the vane (67) and has a platform (71) that extends transversally to the blade axis (73). The aim of the invention is to guarantee the improved cooling of a platform region and the transition region (65) from a turbine blade (67) to a platform (71) of a turbine blade (63), thus ensuring the cooling of the delimitation of a flow channel (5) in a gas turbine (1). To achieve this, the platform (71) comprises a first platform wall (70) that does not support the vane (67) and a second platform wall (69) that supports said vane (67). According to the inventive concept, at the root of the vane (67) and over the course of the transition region (65) from the turbine blade (67) to the platform (71), said first platform wall is aerodynamically curved (104) and the course of the second platform wall (69) has a receding shoulder (103) in relation to the first platform wall (70), as a continuation of the vane (67).

    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL
    5.
    发明公开
    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL 有权

    公开(公告)号：EP1706592A1

    公开(公告)日：2006-10-04

    申请号：EP05700848.4

    申请日：2005-01-12

    申请人： SIEMENS AKTIENGESELLSCHAFT

    发明人： BALDAUF, Stefan ,  BOLMS, Hans-Thomas ,  HÄNDLER, Michael ,  LERNER, Christian

    IPC分类号： F01D5/22 ,  F01D11/00

    CPC分类号： F01D11/008 ,  F01D5/22 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

    摘要： The invention relates to a turbine blade (67) comprising a vane (67) that runs along a blade axis (73) and a platform region (61), which is located at the root of the vane (67) and has a platform (71) that extends transversally to the blade axis (73). The aim of the invention is to guarantee the improved cooling of a platform region and the transition region (65) from a turbine blade (67) to a platform (71) of a turbine blade (63), thus ensuring the cooling of the delimitation of a flow channel (5) in a gas turbine (1). To achieve this, the platform (71) comprises a first platform wall (70) that does not support the vane (67) and a second platform wall (69) that supports said vane (67). According to the inventive concept, at the root of the vane (67) and over the course of the transition region (65) from the turbine blade (67) to the platform (71), said first platform wall is aerodynamically curved (104) and the course of the second platform wall (69) has a receding shoulder (103) in relation to the first platform wall (70), as a continuation of the vane (67).

    摘要翻译： 本发明涉及一种涡轮机叶片（67），该涡轮机叶片包括沿着叶片轴线（73）延伸的叶片（67）和位于叶片（67）的根部且具有平台（61）的平台区域（61） 71），其横向于叶片轴线（73）延伸。 本发明的目的是保证从涡轮机叶片（67）到涡轮机叶片（63）的平台（71）的平台区域和过渡区域（65）的改进的冷却，从而确保冷却界限 在燃气轮机（1）中的流动通道（5）中。 为了实现该目的，平台71包括不支撑叶片67的第一平台壁70和支撑所述叶片67的第二平台壁69。 根据本发明构思，在叶片（67）的根部和过渡区域（65）从涡轮机叶片（67）到平台（71）的过程之上，所述第一平台壁是空气动力学弯曲的（104） 并且第二平台壁69的路线相对于第一平台壁70具有作为叶片67的延续部的后退肩部103。

    EINSATZELEMENT, RINGSEGMENT, GASTURBINE, MONTAGEVERFAHREN
    6.
    发明公开
    EINSATZELEMENT, RINGSEGMENT, GASTURBINE, MONTAGEVERFAHREN 有权
    EINSATZELEMENT，RINGSEGMENT，GASTURBINE，MONTAGEVERFAHREN

    公开(公告)号：EP3004562A1

    公开(公告)日：2016-04-13

    申请号：EP14752585.1

    申请日：2014-08-05

    申请人： Siemens Aktiengesellschaft

    发明人： AHMAD, Fathi ,  HÄNDLER, Michael ,  KAMPKA, Kevin ,  KOWALSKI, Christian ,  KOWALZIK, Christian ,  KURT, Nihal ,  SCHMITT, Stefan ,  SCHRÖDER, Peter

    IPC分类号： F01D11/08 ,  F01D11/14 ,  F01D25/28 ,  F01D11/12

    CPC分类号： F01D11/14 ,  F01D11/08 ,  F01D11/12 ,  F01D25/28 ,  F02C3/04 ,  F05D2220/32

    摘要： The invention relates to an insert element (14) for covering a recess (23) of a ring segment body (25) of a turbine (11) of a gas turbine (10). The ring segment body (25) has a recess (23) on a hot-gas side (27). The insert element (14) has a concavely shaped front face (15) and a rear face (16) with a rear face profile (17), and the rear face profile (17) corresponds to a negative shape of a profile (22) of the recess (23). The invention additionally relates to a ring segment (13) comprising the insert element (14), to a gas turbine (10) comprising the insert element (14), and to an assembly method for assembling the insert element (14).

    摘要翻译： 本发明涉及一种用于覆盖燃气涡轮机（10）的涡轮机（11）的环段本体（25）的凹部（23）的插入元件（14）。 环段本体（25）在热气侧（27）上具有凹部（23）。 插入元件14具有凹形的前表面15和具有后表面形状17的后表面16，并且后表面形状17对应于轮廓22的负形状， 的凹槽（23）。 本发明还涉及包括插入元件（14）的环段（13），包括插入元件（14）的燃气涡轮机（10）以及用于组装插入元件（14）的组装方法。

    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL
    7.
    发明授权
    TURBINENSCHAUFEL UND GASTURBINE MIT EINER SOLCHEN TURBINENSCHAUFEL 有权

    公开(公告)号：EP1706593B1

    公开(公告)日：2011-08-17

    申请号：EP05706868.6

    申请日：2005-01-12

    申请人： SIEMENS AKTIENGESELLSCHAFT

    发明人： BALDAUF, Stefan ,  BOLMS, Hans-Thomas ,  HÄNDLER, Michael ,  LERNER, Christian

    IPC分类号： F01D5/22 ,  F01D11/00

    CPC分类号： F01D5/22 ,  F01D11/008 ,  F05D2240/80

    摘要： The invention relates to a turbine blade (63, 65) comprising a vane (67, 69) that runs along a blade axis (73, 75) and a platform region (61), which is located at the root of the vane (67, 69) and has a platform (71) that extends transversally to the blade axis (73, 75). The aim of the invention is to configure a delimitation (87) of a flow channel (5) of a gas turbine (1) in the simplest possible manner. To achieve this, the platform (71) is configured by an elastic sheet metal part (77, 79) that rests on the vane (67, 69). Said part leads to a gas turbine (1) comprising a flow conduit (5) that runs along an axis (3) of the gas turbine (1), said conduit having an annular cross-section for a working medium (M) and a second (9, 13) vane stage (7, 9, 11, 13) that is situated downstream of a first (7, 11) vane stage, which runs along the axis (3). According to the invention, a vane stage comprises a number of turbine blades (63, 65) that are arranged in a ring and extend radially into the flow channel (5) in accordance with the inventive concept.

    摘要翻译： 本发明涉及一种涡轮叶片（63,65），其包括沿着叶片轴线（73,75）延伸的叶片（67,69）和位于叶片根部处的平台区域（61） ，69）并且具有横向于叶片轴线（73,75）延伸的平台（71）。 本发明的目的是以最简单的可能方式构造燃气涡轮机（1）的流动通道（5）的界限（87）。 为了实现这一点，平台71由搁置在叶片67,69上的弹性金属片部件77,79构成。 所述部分通向包括沿着燃气涡轮机（1）的轴线（3）延伸的流动导管（5）的燃气轮机（1），所述导管具有用于工作介质（M）的环形横截面和 第二（9,13）叶片级（7,9,11,13），其位于沿轴线（3）延伸的第一（7,11）叶片级的下游。 根据本发明，根据本发明构思，叶片级包括多个涡轮叶片（63,65），所述多个涡轮叶片排列成环形并径向延伸到流动通道（5）中。