A turbine blade inert gas welding positioning device
An inert gas and welding positioning technology, applied in positioning devices, welding equipment, auxiliary devices, etc., can solve problems affecting the processing quality of parts, welding cracks, poor welding operability, etc., and achieve the effect of increasing versatility
Active Publication Date: 2019-06-04
AECC AVIATION POWER CO LTD
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Problems solved by technology
At present, when welding, the parts are naturally placed on the workbench, and there is an angle between the welding position and the natural position of the parts, and the welding operability is poor; the heat generated by the instantaneous high temperature cannot be released quickly, and the heat gathers around the welding part of the parts, forming a relatively tight welding position. Large area of heat-affected zone, and surface oxidation occurs, welding cracks are prone to appear after welding, which affects the processing quality of parts
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[0028] In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it may be mechanically connected or electrically connected; it may be directly connected or indirectly connected through an intermediary, and it may be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.
[0029] The invention provides a positioning device for inert gas welding of turbine blades. In order to facilitate the rapid transfer of heat during part welding, the tooling is made of red copper. Fix the tenon of the turbine blade on the positioning block, and place the part to be welded on the heat dissipation block 3 made of cop...
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The invention discloses an inert-gas welding positioning device for turbine blades. The inert-gas welding positioning device comprises a side support and a supporting base, wherein the side support and the supporting base are sequentially arranged on a base; the side support is provided with a heat radiating block with a complex blade-canopy profile, the supporting base is provided with a V-shapedgroove which is fit with an angle structure of a blade lower margin plate, and a low-pressure turbine blade is arranged between the side support and the supporting base; and a blade-canopy to-be-welded part of the low-pressure turbine blade is attached to the heat radiating block, and the lower margin plate and a tenon part of the low-pressure turbine blade are arranged in the V-shaped groove. The inert-gas welding positioning device for the turbine blades is convenient to operate in use, and when a blade basin and a blade back need to be replaced in the welding process, the blade basin and the blade back only need to be reversely turned and clamped; and the inert-gas welding positioning device is good in part welding effect, compact in structure, low in manufacturing cost and particularsuitable for welding of blades with similar structures.
Description
technical field [0001] The invention belongs to the technical field of inert gas welding, and in particular relates to an inert gas welding positioning device for low-pressure turbine blades of aeroengines. Background technique [0002] Aeroengine turbine blades are required to have good wear resistance, corrosion resistance and high temperature resistance due to their special working environment, and surfacing welding technology is one of the important ways to improve the surface performance of parts machining, and it is more and more used for the surface modification process of parts. [0003] Turbine working blades can be repaired by fusion welding method for blade tip and sawtooth crown wear, and the surface modification treatment of blade crown can also be carried out. At this stage, almost all low-pressure turbine blades will add shockproof shoulders formed by hard alloy surfacing welding on the blade crown, and the thickness of the surfacing layer is more than 2mm. ...
Claims
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IPC IPC(8): B23Q3/00B23K37/04
Inventor 白变琴钱勇温学兵崔保卫高敏雀苏瑾兰小刚邸利
Owner AECC AVIATION POWER CO LTD