公开(公告)号：US20150004001A1

公开(公告)日：2015-01-01

申请号：US14490813

申请日：2014-09-19

Applicant: ALSTOM Technology Ltd

Inventor： Martin SCHNIEDER ,  Sergey SHCHUKIN

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F05C2251/02 ,  F05D2250/71 ,  F05D2300/501

Abstract: A turbine vane for a rotary turbomachine is described having a turbine blade which is delimited by a concave pressure-side wall and a convex suction-side wall which are connected in the region of a vane front edge which can be assigned to the turbine blade and enclose a cavity which extends in the longitudinal extent of the vane front edge and is delimited on the inner wall by the pressure-side wall and the suction-side wall in the region of the vane front edge and by an intermediate wall which extends in the longitudinal direction to the vane front edge and connects the suction-side wall and the pressure-side wall on the inner wall. The disclosed vane is distinguished by the fact that the intermediate wall has a perforation at least in sections in the connecting region to the suction-side wall and/or pressure-side wall, in order to increase the elasticity of the intermediate wall.

Abstract translation: 描述了一种用于旋转涡轮机的涡轮叶片，其具有涡轮叶片，该涡轮叶片由可被分配给涡轮叶片的叶片前缘区域中连接的凹压力侧壁和凸形吸入侧壁限定， 包围在叶片前缘的纵向延伸部分延伸的空腔，并且在叶片前缘的区域中的压力侧壁和吸力侧壁以及在内壁上延伸的中间壁在内壁上限定 并且连接吸入侧壁和内壁上的压力侧壁。 所公开的叶片的特征在于中间壁在与吸入侧壁和/或压力侧壁的连接区域中至少具有穿孔，以增加中间壁的弹性。

公开(公告)号：US20150003975A1

公开(公告)日：2015-01-01

申请号：US14491040

申请日：2014-09-19

Applicant: ALSTOM Technology Ltd

Inventor： Sergey SHCHUKIN ,  Robert MARMILIC

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F01D5/18 ,  F01D5/187 ,  F01D25/12 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: The disclosure pertains to a cooled wall for separating a hot gas flow path of a gas turbine from a cooling flow including at least one turbulator rib extending from the wall into the cooling flow, and having a height, a width for providing heat transfer enhancement for the cooled wall. The turbulator rib has filets at its root with a filet radius. In order to increase the heat transfer enhancement of the turbulator rib, the filet at the downstream side of turbulator rib is extending into the cooled wall with a penetration depth. Further, the disclosure relates to specific embodiments in which the cooled wall with turbulator ribs is configured as the sidewall of an airfoil, a combustor wall or a heat shield.

Abstract translation: 本发明涉及一种用于将燃气涡轮机的热气体流路与冷却流分离的冷却壁，所述冷却流包括从壁延伸到冷却流中的至少一个湍流肋，并且具有高度，用于提供热传递增强的宽度 冷却的墙壁。 湍流肋在其根部具有锉刀半径。 为了增加湍流肋的传热增强，在湍流肋的下游侧的file口延伸到具有穿透深度的冷却壁中。 此外，本公开涉及其中具有湍流肋的冷却壁被构造为翼型，燃烧器壁或隔热罩的侧壁的具体实施例。

公开(公告)号：US20160090847A1

公开(公告)日：2016-03-31

申请号：US14858285

申请日：2015-09-18

Applicant: ALSTOM Technology Ltd

Inventor： Sergey SHCHUKIN

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2250/38 ,  F05D2250/71 ,  F05D2260/201

Abstract: A turbine blade of a gas turbine includes a radially extending airfoil with a suction side and pressure side, which extend each in axial direction between a leading edge and a trailing edge of the airfoil. The leading edge is cooled by means of impingement cooling with rows of radially distributed jets of a cooling medium impinging on the inner side of the leading edge. The row of radially distributed jets is generated at an internal web, which divides the hollow interior of the airfoil into first and second cavities, with the second cavity being arranged at the leading edge. An enhanced cooling is achieved by the internal web that includes two rows of radially distributed cooling medium supply holes, through which cooling medium enters the second cavity in form of impinging jets. The cooling medium supply holes are oriented such that the directions of the jets of one row cross the directions of the jets of the other row.

Abstract translation: 燃气涡轮机的涡轮机叶片包括具有吸力侧和压力侧的径向延伸的翼型件，其在轴向方向上在翼型的前缘和后缘之间延伸。 引导边缘通过冲击冷却而被冷却，这些冲击冷却具有冲击在前缘内侧的冷却介质的径向分布的射流。 径向分布的射流排在内部腹板处产生，内部腹板将翼型件的中空内部分成第一和第二空腔，第二空腔布置在前缘。 通过包括两排径向分布的冷却介质供应孔的内部网来实现增强的冷却，冷却介质通过该供应孔以冲击射流的形式进入第二空腔。 冷却介质供给孔的取向为使一排的喷流的方向与另一排的喷流的方向交叉。

公开(公告)号：US20160076390A1

公开(公告)日：2016-03-17

申请号：US14837078

申请日：2015-08-27

Applicant: ALSTOM Technology Ltd

Inventor： Robert MARMILIC ,  Sergey SHCHUKIN

IPC: F01D9/04 ,  F01D25/12

CPC classification number: F01D9/042 ,  F01D5/14 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/189 ,  F01D5/28 ,  F01D9/041 ,  F01D11/005 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2260/201

Abstract: The invention relates to a mounting and sealing arrangement for a guide vane of a gas turbine, which includes a vane carrier for carrying said vanes in a ring-like arrangement, whereby the vanes each comprise an airfoil and an outer diameter platform. The thermal stress is reduced and lifetime improved by providing a separate intermediate mounting element between the vane carrier and the outer diameter platform of each of the vanes, and mounting the intermediate mounting element with an outer side on the vane carrier, whereby the intermediate mounting element abuts with an inner side on the outer diameter platform in a sealing fashion.

Abstract translation: 本发明涉及一种用于燃气轮机的导向叶片的安装和密封装置，其包括用于将所述叶片以环状装置承载的叶片载体，由此叶片各自包括翼型件和外径平台。 通过在叶片承载件和每个叶片的外径平台之间设置单独的中间安装元件，并将中间安装元件安装在叶片承载件上的外侧，从而降低了热应力并提高了使用寿命，从而中间安装元件 以密封方式与外径平台上的内侧邻接。

公开(公告)号：US20150050125A1

公开(公告)日：2015-02-19

申请号：US14341264

申请日：2014-07-25

Applicant: ALSTOM Technology Ltd

Inventor： Carlos SIMON-DELGADO ,  Vasileios STEFANIS ,  Sergey SHCHUKIN ,  Joerg KRUECKELS

IPC: F01D11/10 ,  F16J15/40

CPC classification number: F01D11/10 ,  F16J15/162 ,  F16J15/40 ,  F16J15/444 ,  F16J15/4472

Abstract: The invention refers to a fluid seal arrangement for constricting a leakage flow directed through a leakage gap bordered by a rotational and a stationary component including at least one nozzle opening in the rotating and/or stationary component facing towards the rotating or stationary component of an opposite side of the leakage gap respectively in order for injecting a liquid or gaseous fluid flow through the nozzle opening into the leakage gap. The at least one nozzle opening is fluidly connected to a cooling channel inside said rotating and/or stationary component, so that said fluid flow emanating at the nozzle opening consists of a cooling fluid of the rotating and/or stationary component exclusively.

Abstract translation: 本发明涉及一种流体密封装置，用于限制通过由旋转和静止部件界定的泄漏间隙的泄漏流动，所述泄漏间隙包括旋转和/或固定部件中的至少一个喷嘴开口，所述喷嘴开口面向相对的旋转部件或固定部件 以便将液体或气体流体流经喷嘴开口注入到泄漏间隙中。 至少一个喷嘴开口流体地连接到所述旋转和/或固定部件内的冷却通道，使得在喷嘴开口处发出的所述流体流由仅旋转和/或静止部件的冷却流体组成。