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Turbine blade and method for producing turbine blade

A technology for turbine blades and manufacturing methods, applied in the direction of engine manufacturing, blade support elements, manufacturing tools, etc., capable of solving problems such as efficiency degradation

Inactive Publication Date: 2008-10-29
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

Examples

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

Turbine blade, especially for a gas turbine, comprises at least one chamber impinged upon by a coolant and at a rear edge (26) a gap (25) defined by two walls (28, 29) for exiting coolant. At least one of the walls is post-treated to reduce the cross-section of the gap. The cross-section of the gap is altered by changing the length (L) of at least one of the walls, preferably the wall on the pressure side. An Independent claim is also included for a process for producing the above 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 is not possible to achieve ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18B23P15/02B23P15/04B22C9/24F01D25/00F02C7/00
CPCB23P15/02F05D2230/10F01D5/187F05B2230/10Y10T29/49218Y10T29/49341
Inventor 彼得·蒂曼
Owner SIEMENS AG