A kind of welding method of aero-engine axial diffuser
An aero-engine and welding method technology, which is applied in the field of aero-engines, can solve problems such as discontinuous brazing seam on the flow channel surface, product scrapping, and brazing seam leakage, so as to achieve discontinuous brazing seam, avoid brazing seam leakage, and avoid deformation Effect
Active Publication Date: 2019-04-16
CHINA HANGFA SOUTH IND CO LTD
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Problems solved by technology
[0003] In actual production, since the first support plate 1 and the second support plate 2 are both ring-shaped, and the side walls are arc-shaped, the pass rate of vacuum brazing is very low, and gaps between welding surfaces are prone to occur. Excessive brazing seam leakage caused by too large, the fillet of the blade root on the runner surface is greater than 0.8mm, the brazing seam on the runner surface is discontinuous, and the parts are seriously deformed, etc.
Need to repair welding many times, even cause the product to be scrapped
Method used
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[0022] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.
[0023] Figure 1a It is a partial structural schematic diagram of the first support plate of the axial diffuser of an aero-engine; Figure 1b It is a partial structural schematic diagram of the second support plate of the axial diffuser of an aero-engine; Figure 1c for Figure 1a The first support plate and Figure 1b The schematic diagram of the structure principle of the second support plate; figure 2 It is a schematic diagram of the assembly structure of an axial diffuser of an aero-engine axial diffuser welding method according to a specific embodiment of the present invention; see Figure 1a , 1b , 1c, and 2, the present invention provides an aeroengine axial di...
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Abstract
The invention discloses a welding method for an axial pressure expander of an aero-engine. The welding method is characterized by comprising the following steps: step A, assembling a first supporting plate, a second supporting plate and a blade, and carrying out argon-arc welding positioning in an argon filling box; step B, cleaning a part which is subjected to positioned welding in the step A, and measuring the sizes of gaps among assembly parts of the blade, the first supporting plate and the second supporting plate; step C, filling the gaps of the assembly parts with the gap sizes greater than or equal to 0.1mm, which is measured in the step B, in a runner surface with paste nickel powder, drying and smoothing; adding paste brazing filler metal with diameter being phi 1.2 to into the assembly part in a through hole, adding paste brazing filler metal with diameter being phi 0.5 into to the gaps, with 1 / 3-3 / 4 of the gap length of the assembly parts, of the assembly parts in the runner surface towards a gas inlet side from a gas outlet side, and carrying out vacuum braze welding, thereby completing welding of the axial pressure expander. The welding method for the axial pressure expander of the aero-engine provided by the invention can avoid brazing seam leakage caused by too great gaps of a non-polar braze welding surface; and moreover, the circular bead of a blade root of the runner surface can be guaranteed to be smaller than 0.8mm.
Description
technical field [0001] The invention relates to the technical field of aero-engines, in particular to a welding method for vacuum brazing an axial diffuser of an aero-engine. Background technique [0002] Figure 1a It is a schematic diagram of the local structure of the first support plate of the axial diffuser of an aero-engine, Figure 1b It is a schematic diagram of the partial structure of the second support plate of the axial diffuser of an aero-engine, Figure 1c for Figure 1a The first support plate and Figure 1b Schematic diagram of the structure principle of the second support plate, see Figure 1a , 1b As shown, an existing axial diffuser of an aero-engine includes a first support plate 1 and a second support plate 2 and multiple leaves (not shown in the figure), see Figure 1c As shown, both the first support plate 1 and the second support plate 2 are annular frustum-shaped thin-walled parts with curved side walls, and the wall thickness is usually 2-5mm, a...
Claims
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IPC IPC(8): B23K28/02
CPCB23K28/02
Inventor 夏蓉许小虎尚延涛邹旸刘柏铄
Owner CHINA HANGFA SOUTH IND CO LTD