公开(公告)号：US20160258302A1

公开(公告)日：2016-09-08

申请号：US14639374

申请日：2015-03-05

Applicant: General Electric Company

Inventor： Adebukola Oluwaseun Benson ,  Lisa De Bellis ,  Xiuzhang James Zhang

IPC: F01D5/20 ,  F01D5/02 ,  F01D5/30 ,  F01D5/18

CPC classification number: F01D5/20 ,  F01D5/02 ,  F01D5/187 ,  F01D5/3007 ,  F05D2220/31 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/307 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/20

Abstract: An airfoil includes a squealer tip at an outer radial end of the airfoil. A squealer tip pocket of the squealer tip has a convex side and a concave side, and a tip plate. A divider extends across the tip plate from the concave side to the convex side to divide the squealer tip pocket into a first pocket and a second pocket. At least one cooling passage through the tip plate in the second pocket provides fluid communication through the tip plate from an interior of the airfoil to the second pocket. The first pocket is fluidically disconnected from the interior of the airfoil.

Abstract translation: 机翼包括在翼型件的外径向端部处的尖叫尖端。 尖叫尖端的尖叫尖端口具有凸面和凹面，以及尖端板。 分隔件从凹入侧延伸穿过顶板至凸侧，以将尖叫尖端口分成第一口袋和第二口袋。 通过第二口袋中的顶板的至少一个冷却通道提供从翼型件的内部到第二口袋的通过顶板的流体连通。 第一口袋与翼型件的内部在流体上断开连接。

公开(公告)号：US20150252673A1

公开(公告)日：2015-09-10

申请号：US14198659

申请日：2014-03-06

Applicant: General Electric Company

Inventor： Brad Wilson VanTassel ,  James Ryan Connor ,  Bryan David Lewis ,  Adebukola Oluwaseun Benson

IPC: F01D5/08 ,  B23P15/02

CPC classification number: F01D5/082 ,  B23P15/02 ,  F01D5/187 ,  F01D11/24 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676 ,  Y10T29/49341

Abstract: Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.

Abstract translation: 涡轮转子叶片中的平台冷却装置包括从吸入侧斜面向内部冷却通道延伸的进料孔，以及一个或多个分支孔，每个分支孔从进料孔延伸到吸入侧斜面，使得冷却剂从 内部冷却通道，通过进料孔到达一个或多个分支孔，并沿吸力侧斜面离开平台。

公开(公告)号：US20140161625A1

公开(公告)日：2014-06-12

申请号：US13711241

申请日：2012-12-11

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xiuzhang James Zhang ,  Adebukola Oluwaseun Benson ,  Richard Ryan Pilson ,  Stephen William Tesh

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2230/11 ,  F05D2250/232 ,  F05D2250/25 ,  F05D2250/323

Abstract: Systems and devices configured to cool turbine components in a turbine by passing a cooling flow through the turbine component via a cooling passage with a variable diameter are disclosed. In one embodiment, a turbine component includes: at least one elongated cooling passage extending from a root of the bucket to a tip of the bucket, wherein the elongated cooling passage has a variable diameter along a length of the bucket.

Abstract translation: 公开了通过使冷却流通过涡轮机部件经由具有可变直径的冷却通道来冷却涡轮机中的涡轮机部件的系统和装置。 在一个实施例中，涡轮机部件包括：从铲斗的根部延伸到铲斗的尖端的至少一个细长的冷却通道，其中细长的冷却通道沿铲斗的长度具有可变的直径。