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A turbomachine component, particularly a gas turbine engine component with a cooled wall and a method of manufacturing the same

A technology of turbine components and gas turbines, which is applied in the direction of engine manufacturing, engine components, combustion methods, etc., and can solve the problems of reduced efficiency and reduced efficiency of gas turbine engines, etc.

Active Publication Date: 2017-05-24
SIEMENS ENERGY GLOBAL GMBH & CO KG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] On the other hand, the provision of cooling function reduces the efficiency of the gas turbine engine
Therefore, the goal is to limit cooling as much as possible without loss of efficiency and to maximize

Method used

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  • A turbomachine component, particularly a gas turbine engine component with a cooled wall and a method of manufacturing the same
  • A turbomachine component, particularly a gas turbine engine component with a cooled wall and a method of manufacturing the same
  • A turbomachine component, particularly a gas turbine engine component with a cooled wall and a method of manufacturing the same

Examples

Experimental program
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Embodiment Construction

[0048] A gas turbine engine may serve as one example of a rotating machine. A gas turbine (short for a gas turbine engine) comprises at one end an air inlet followed by a compressor stage in which the incoming air is compressed for application to one or more combustion chambers as combustion equipment, These combustion devices can be annular or so-called can-annular or can-shaped, the latter being distributed circumferentially around the turbine shaft. The fuel is introduced into the combustion chamber where it is mixed with the majority of the compressed air taken from the compressor. The high velocity hot gases as a result of combustion in the combustor are directed to a set of turbine blades which are directed (ie redirected) by a set of vanes into the turbine section. The turbine blades and the shaft to which the turbine blades are fixed form a rotor and rotate about the shaft as a result of the influence of the hot gas flow. Rotating the rotor (or another rotor) also ro...

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PUM

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Abstract

The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal. The part (2) comprises a plurality of cooling channels (3) via which a cooling fluid (5), particularly air, is guidable, wherein at least one of the plurality of cooling channels (3) has a continuously tapered section (8). The at least one of the plurality of cooling channels (3) has a single inlet port (1) from a first surface (15) of the panel (11) and a single outlet port (7) for the cooling fluid (5) to another surface (16), particularly a surface opposite to the first surface (15), or to the first surface (15). Further the panel (11) is built via laser sintering or laser melting or direct laser deposition. The invention furthermore is directed to a gas turbine engine equipped with the component and a method of manufacturing the same.

Description

technical field [0001] The present invention relates to a turbomachine (or rotating machine) assembly, in particular to a gas turbine engine assembly in the hot region of the gas turbine engine, in which there are cooling channels for cooling the hot surfaces. Background technique [0002] Gas turbine engines, like other rotating machines, include sections that direct cold fluid and other regions that direct hot fluid through the engine. In a gas turbine engine, ambient air, usually a fairly cool fluid, can be compressed by the compressor section and supplied to the combustor where a large volume of cold fluid (at least cooler than the operating conditions inside the combustor) will be along with the fuel Combustion, to provide the driving force for the subsequent turbine section, where the hot fluid from the combustion chamber will drive the rotor blades of the turbine to drive the shaft again. [0003] In the combustor or in the downstream section through the combustor, h...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D25/12F02K1/82F23R3/00
CPCF01D25/12F02K1/822F23R3/002F23R3/005F23R2900/03041F23R2900/03042F05D2230/22F05D2250/292F05D2260/202F05D2230/54F05D2260/203F01D9/023Y02P10/25Y02T50/60B23K26/21F01D25/08F01D25/14F01D25/24F02K1/82F05D2260/20
Inventor D·罗斯塔德T·奥弗维斯特德特
Owner SIEMENS ENERGY GLOBAL GMBH & CO KG