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Crack Relief for Welds

A technology for crack arrest and cracking, which is applied to vehicle parts, welding equipment, arc welding equipment, etc.

Active Publication Date: 2021-07-09
GKN AEROSPACE SWEDEN AB
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Possibility to detect and repair cracks that develop and propagate due to LCF during regular inspection and maintenance intervals

Method used

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  • Crack Relief for Welds
  • Crack Relief for Welds
  • Crack Relief for Welds

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0070] exist figure 1 An aircraft engine 1 is schematically shown in . The aircraft engine extends around a central axis 2 .

[0071] The main parts of the aircraft engine 1 are the fan casing 4 surrounding the fan 6, the low pressure compressor 8, the compressor structure 10, the high pressure compressor 12, the combustor 14, the high pressure turbine 16, the low pressure turbine 18 arranged in the following order along the axis 2 And the turbine mechanism 20.

[0072] The compression section comprising the low-pressure compressor 8 after the high-pressure compressor 12 compresses at least part of the air entering the engine through the inlet 3 before entering the combustor 14 . A portion of the air entering via the inlet may be directed through a bypass flow path (not shown) such that forward thrust is generated. In the combustion section, combustion occurs by ignition and combustion of a mixture of air and fuel. The turbines are rotated about axis 2 by expanding the co...

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PUM

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Abstract

A method of joining two structural elements (26, 28) by welding, in particular by butt welding, is disclosed. The method comprises the steps of: - forming a weld (30) joining two structural elements; - adding material (32) across the weld (30), thereby forming one or more crack reliefs (34) for Limit crack growth along the weld line. The one or more crack arresters (34) each have a limited extension along the weld line (30) when viewed relative to the length of the weld line. A structural system comprising two structural elements joined by this method is disclosed. In particular, the method can be applied to components of aircraft engines.

Description

technical field [0001] The present disclosure relates to preventing or limiting the propagation of cracks along welds. In particular, a welding method and a weld formed by the method are disclosed. A particularly important application is the field of aircraft, in particular jet engines and mounting structures for jet engines. Background technique [0002] Different parts of an aircraft, in particular parts of the engine structure and components in the load path between the engine and the aircraft structure, such as the wings, are exposed to high stresses during flight. [0003] Engine components and components within the load path are usually manufactured by casting parts thereof or by using sheet metal or forgings and subsequently welding the different parts together. Any weld lines connecting different structures may have initial defects from manufacturing, such as air holes. Such defects may develop into cracks under stress, in particular due to the thermal and mechani...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23K9/04B23K26/342B23K31/02B23K31/12F01D25/28F02K1/78
CPCB23K26/342B23K9/04B23K9/042B23K9/044B23K31/02B23K31/12F01D25/28F02K1/78F05D2250/183F05D2250/182F05D2230/232B23K2101/006B23K2101/18Y02T50/60B33Y10/00B33Y80/00B23K9/025B23K26/26B23K33/00B23P6/045B23K2103/10B23K2101/001B23K2103/08B23K2103/14B23K11/04B23P6/04B64C1/12
Inventor 罗伯特·赖默斯
Owner GKN AEROSPACE SWEDEN AB