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Turbine blade and method for producing turbine blade

A technology for turbine blades and manufacturing methods, applied in the directions of blade support elements, manufacturing tools, machines/engines, etc., can solve problems such as efficiency degradation

Inactive Publication Date: 2002-11-06
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This leads to a loss of efficiency, since the cooling medium must in many cases be delivered at relatively high pressure from the compressor, which must be driven by the turbine

Method used

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  • Turbine blade and method for producing turbine blade
  • Turbine blade and method for producing turbine blade
  • Turbine blade and method for producing turbine blade

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Experimental program
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Embodiment Construction

[0029] figure 1 Shown is a longitudinal sectional view of a gas turbine 10 with a housing 11 and a rotor 12 . There are multiple rows of guide blades 13 on the housing 11 and multiple rows of rotor blades 14 on the rotor 12 . Hot gas flows through the gas turbine 10 in the direction of the arrow 15 , causing the rotor 12 to rotate about its axis of rotation 16 in the direction of the arrow 17 .

[0030] figure 2 A sectional view of one guide vane 13 is shown. However, the invention is not limited to guide blades 13 , but can also be used for rotor blades 14 .

[0031] The outside of the guide vanes 13 is formed by a suction-side partition 28 and a compressor-side partition 29 . The interior defined by the partitions 28 , 29 is divided overall into four chambers 18 , 19 , 20 , 21 which are separated by partitions 22 , 23 , 24 . In order to cool the guide vanes 13, the cavities 18, 19, 20, 21 are all filled with cooling medium. The cooling medium is discharged from the ch...

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PUM

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Abstract

The invention relates to a turbine blade, in particular a turbine blade for a gas turbine (10), which has at least one chamber (18; 19; 20; 21) which can be filled with a cooling medium, and on a trailing edge (26) According to the invention, at least one of said partitions (28, 29) is finished to change the gap (25) section (A). As a result, the section (A) can be adapted to the corresponding boundary conditions, thereby reducing the consumption of cooling medium. Furthermore, the invention relates to a method (13; 14) for producing such a turbine blade.

Description

technical field [0001] The invention relates to a turbine blade, in particular a turbine blade for a gas turbine, which has at least one cavity which can be filled with a cooling medium, and a gap on the trailing edge for the discharge of the cooling medium which is delimited by two partitions . Furthermore, the invention relates to a method for producing such a turbine blade. Background technique [0002] Such turbine blades and their manufacturing methods have been disclosed, for example, in US patent document US5419039 and international patent document WO99 / 59748. The turbine blades are usually manufactured by casting. In many cases it is produced using one or more cores of ceramic material embedded in a wax pattern. After the turbine blade has been cast from the desired material, the core is removed, in particular by leaching. Due to the shrinkage coefficients of the materials used for the core, wax, outer core shell and turbine blades, it ...

Claims

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Application Information

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IPC IPC(8): B23P15/04B22C9/24B23P15/02F01D5/18F01D25/00F02C7/00
CPCB23P15/02F01D5/187F05D2230/10Y10T29/49218Y10T29/49341
Inventor 彼得·蒂曼
Owner SIEMENS AG