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Arrangement of cooling channels in a turbine blade

A technology for turbine blades and cooling passages, applied in the direction of blade support components, mechanical equipment, engine components, etc., to achieve the effect of loss reduction

Inactive Publication Date: 2016-05-18
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

This often results in damaged blades having to be replaced quickly

Method used

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  • Arrangement of cooling channels in a turbine blade

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Embodiment Construction

[0031] At the bottom is the blade root 2 by means of which the turbine blade is attached to the rotor. Leading edge 3 is shown on the left. The leading edge 3 is the area that first encounters the gas mixture driving the turbine blades. The blade airfoil tip 4 is shown at the top. The trailing edge 5 is arranged on the right. Turbine blades are not flat, but curved. In this case, the leading edge 3 and the trailing edge 5 can be straight, but also curved. In contrast, the blade root 2 and the blade airfoil tip are always curved, like the rest of the blade area. The curvature is attributed to the aerodynamic shape of the turbine blade.

[0032] The turbine blade has a front wall (not shown) extending from a leading edge to a trailing edge, and a rear wall extending a distance from the front wall and leading again from the trailing edge to the leading edge. In general, the distance between the front and rear walls is very small in the area of ​​the leading edge 3 and trail...

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PUM

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Abstract

The invention relates to an arrangement (1) of a plurality of cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) within a turbine blade for conveying cooling fluid, wherein the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) lead through the turbine blade, which comprises a blade root (2), a blade tip (4), a leading edge (3), and a trailing edge (5), to one or more cooling-fluid outlets (18, 19a-19g), wherein the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) are connected to each other at selected locations (8, 10) and extend separately from each other in other regions in such a way that, in the event of damage to the turbine blade in the region of one cooling channel (6, 7, 9, 11, 12, 13, 14, 15, 16, 17), the cooling by the other cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) remains largely unimpaired, wherein at least one cooling channel begins in a region (8) near the leading edge (3) and near the blade root (2) and leads as a diagonal channel (9) through the turbine blade into a region (10) near the trailing edge (5) and near the blade tip (4).

Description

technical field [0001] The invention relates to the arrangement of cooling channels in a turbine blade. Background technique [0002] Turbine blades, especially gas turbine blades, are highly loaded components. In operation, rotation occurs at high rotational speeds. Therefore, high mechanical strength is necessary. Furthermore, especially in the case of gas turbine blades, high temperatures are generated during operation. It is generally the case that the higher temperature of the gas mixture driving the turbine blades has a positive effect on the efficiency of the gas turbine. In this case, the turbine blades are cooled in order to prevent excessive turbine blade temperatures. For this purpose, cooling channels are often arranged inside the turbine blade. [0003] Occasionally, turbine blades are damaged by striking foreign objects. A consequence of this damage can be problems with the air from the cooling passages and sometimes substantially impair the cooling of th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/188F05D2260/201F01D5/187F05D2220/32F05D2260/202
Inventor F·阿玛德T·布尔兹驰E·哈梅尔G·E·昆泽F·普罗腾T·A·施奈德H·特伊伯
Owner SIEMENS AG