公开(公告)号：US20230349298A1

公开(公告)日：2023-11-02

申请号：US18344144

申请日：2023-06-29

Applicant: General Electric Company

Inventor： Nicholas William Rathay ,  Thomas Earl Dyson ,  Brian Brzek

IPC: F01D5/18

CPC classification number: F01D5/189 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/304 ,  F05D2250/711 ,  F05D2260/202 ,  F05D2260/2212

Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

公开(公告)号：US11499434B2

公开(公告)日：2022-11-15

申请号：US17262399

申请日：2018-07-31

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Thomas Earl Dyson ,  Brian Brzek ,  Fred Willett, Jr. ,  Paul Dimascio

IPC: F01D5/18 ,  B33Y80/00

Abstract: In one embodiment, an airfoil includes an airfoil body portion, an airfoil tip portion disposed radially outward of the airfoil body portion, an airfoil root portion, and a plurality of radial cooling passages extending through the airfoil body portion from the root portion to the tip airfoil portion. The airfoil body portion and the airfoil tip portion are joined at a braze interface or a weld interface. The airfoil tip portion includes at least one manifold fluidly connecting at least one radial cooling passage to at least one other radial cooling passage.

公开(公告)号：US20210156265A1

公开(公告)日：2021-05-27

申请号：US16697242

申请日：2019-11-27

Applicant: General Electric Company

Inventor： Nicholas William Rathay ,  Thomas Earl Dyson ,  Brian Brzek

IPC: F01D5/18

Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

公开(公告)号：US11732594B2

公开(公告)日：2023-08-22

申请号：US16697242

申请日：2019-11-27

Applicant: General Electric Company

Inventor： Nicholas William Rathay ,  Thomas Earl Dyson ,  Brian Brzek

IPC: F01D5/18

CPC classification number: F01D5/189 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/304 ,  F05D2250/711 ,  F05D2260/202 ,  F05D2260/2212

Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

公开(公告)号：US20150064019A1

公开(公告)日：2015-03-05

申请号：US14014528

申请日：2013-08-30

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  Brian Brzek ,  David Edward Schick

IPC: F01D5/18

CPC classification number: F01D5/186 ,  B22F3/1055 ,  B22F5/04 ,  B22F5/10 ,  B22F7/004 ,  F01D5/183 ,  F01D5/187 ,  F05D2300/514 ,  F05D2300/612 ,  Y02P10/295

Abstract: The present application provides a hot gas path component for use with a gas turbine engine. The hot gas path component may include an airfoil, an internal cooling cavity, and a porous section created by a direct metal laser melting technique. The porous section may be built into the airfoil or the airfoil may be built separately and attached to the airfoil.

Abstract translation: 本申请提供了一种与燃气涡轮发动机一起使用的热气路径部件。 热气体路径部件可以包括翼型件，内部冷却腔和通过直接金属激光熔化技术产生的多孔部分。 多孔部分可以内置在翼型件中，或者翼型件可以单独构建并附接到翼型件。