公开(公告)号：US20160186575A1

公开(公告)日：2016-06-30

申请号：US14584442

申请日：2014-12-29

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  Christopher Donald Porter ,  David Edward Schick

IPC: F01D5/18 ,  F01D5/14

CPC classification number: B33Y80/00 ,  B22F3/1055 ,  B22F5/009 ,  B22F7/062 ,  B22F2999/00 ,  B33Y10/00 ,  F01D5/225 ,  F01D11/24 ,  F01D25/12 ,  F05D2230/31 ,  F05D2230/51 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/202 ,  Y02P10/295 ,  B22F2203/05

Abstract: Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.

Abstract translation: 本公开的各种实施例包括涡轮机组件。 以及形成这种组分的方法。 一些实施例包括涡轮机组件，包括：包括不锈钢或合金钢中的至少一种的第一部分; 以及与所述第一部分连接的第二部分，所述第二部分包括包含延伸穿过其中的弧形冷却特征的镍合金，所述第二部分具有基本上类似于所述第一部分的热膨胀系数的热膨胀系数，其中所述弧形冷却特征 位于第二部分内，以将冷却剂的一部分引导到涡轮机组件的泄漏区域。

公开(公告)号：US20140341720A1

公开(公告)日：2014-11-20

申请号：US13893729

申请日：2013-05-14

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Dipankar Pal ,  Robert Walter Coign ,  Gary Michael Itzel ,  Kevin Thomas McGovern ,  Christopher Donald Porter

IPC: F01D25/00

CPC classification number: F01D11/005 ,  F01D11/006 ,  F05D2240/57

Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.

Abstract translation: 公开了被配置为密封涡轮机的固定部件之间的接口/间隙并且在涡轮机操作期间操纵涡轮机部分周围的冷却剂流的系统和装置。 在一个实施例中，密封元件包括：成形为朝向涡轮的加压腔定向的第一表面; 第二表面，其定向成基本上与第一表面相对并且成形为密封地接合静态部件的接触表面; 以及设置在所述第二表面中的第一组角特征，所述第一组角特征将所述加压腔和所述涡轮的流路流体连接。