CN113878189B - Vacuum brazing process for honeycomb assembly of aircraft engine - Google Patents
Vacuum brazing process for honeycomb assembly of aircraft engine Download PDFInfo
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- CN113878189B CN113878189B CN202111055414.0A CN202111055414A CN113878189B CN 113878189 B CN113878189 B CN 113878189B CN 202111055414 A CN202111055414 A CN 202111055414A CN 113878189 B CN113878189 B CN 113878189B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
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Abstract
The invention discloses a vacuum brazing process for an aircraft engine honeycomb assembly, which comprises the following steps: s1, preparing a honeycomb ring, and filling adhesive band brazing filler metal into the honeycomb ring; s2, enabling the brazing surface of the honeycomb ring and the outer ring to comprise a nickel plating area and a non-nickel plating area, protecting the non-nickel plating area of the outer ring by using a protection piece, enabling the brazing surface, close to the outer end surface, of the outer ring to be the nickel plating area, and performing sand blowing treatment on the nickel plating area; s3, brushing special nickel on the outer ring nickel plating area, brushing rapid nickel, and removing the protection piece; s4, combining the honeycomb ring filled with the adhesive brazing filler metal with an outer ring; s5, spot welding positioning is carried out on the honeycomb ring; s6, filling paste-like brazing filler metal into the joint of the outer end face of the honeycomb ring and the nickel plating area of the outer ring to obtain a pre-brazed part; and S7, carrying out vacuum brazing treatment on the pre-brazed part. According to the vacuum brazing process for the honeycomb assembly of the aero-engine, the outer ring is locally brushed and plated with nickel, and the problems that the spot welding of the honeycomb assembly made of a difficult-to-weld material is not firm and the surface of a brazing seam is discontinuous are solved.
Description
Technical Field
The invention relates to the field of aero-engine brazing, in particular to a vacuum brazing process for an aero-engine honeycomb assembly.
Background
Honeycomb assemblies for aircraft engines are typically formed by vacuum brazing a honeycomb to an outer ring, some of which are formed of a cast superalloy, such as K477 or the like. Because the high-temperature alloy base cast by K477 has high content of elements such as aluminum, titanium and the like, the brazing filler metal has poor wettability and spreadability on the surface during brazing, and the outer ring brazing surface can be subjected to brush nickel plating to improve the brazing performance. However, after the outer ring brazing surface is brushed with nickel, due to the blocking effect of the nickel layer, effective welding spots cannot be formed among the honeycomb, the nickel layer and the matrix during spot welding, and therefore the phenomenon of infirm energy storage spot welding occurs. The weak spot welding causes the local brazing part to be not welded, thereby affecting the welding rate of the parts. If the nickel brushing is omitted from the surface of the part, the spot welding of the honeycomb and the outer ring can be firm during the energy storage spot welding positioning, the welding rate of the part is ensured, but due to poor wettability of the brazing filler metal, the appearance defects of discontinuity of the side surface of the honeycomb after welding, brazing seam cracking and the like are easy to appear, and the acceptance requirement is not met.
Disclosure of Invention
The invention provides a vacuum brazing process for an aeroengine honeycomb assembly, which aims to solve the technical problems that the appearance is unqualified because the energy storage spot welding positioning is not firm after an outer ring cast by a cast high-temperature alloy material is nickel-plated and the brazed joint between a nickel-plated honeycomb brush and the outer ring is not continuous.
The technical scheme adopted by the invention is as follows:
a vacuum brazing process for an aircraft engine honeycomb assembly, the honeycomb assembly including a honeycomb ring and an outer ring, comprising the steps of:
s1, preparing a honeycomb ring, and filling adhesive band brazing filler metal into the honeycomb ring;
s2, enabling brazing surfaces of the honeycomb ring and the outer ring to comprise a nickel plating area and a non-nickel plating area, protecting the non-nickel plating area of the outer ring by using a protection piece, enabling the brazing surface, close to the outer end surface, on the outer ring to be the nickel plating area, carrying out sand blowing treatment on the nickel plating area, and cleaning the surface of the outer ring after sand blowing;
s3, brushing special nickel on the outer ring nickel plating area, brushing rapid nickel, and removing the protection piece;
s4, combining the honeycomb ring filled with the adhesive tape brazing filler metal in the step S1 with the outer ring in the step S3 to sleeve the outer ring on the outer wall surface of the honeycomb ring;
s5, spot welding positioning is carried out on the honeycomb ring in the step S4;
s6, filling a paste solder into the joint of the outer end face of the honeycomb ring and the inner wall face of the outer ring in the step S5 to obtain a pre-brazing part;
and S7, performing vacuum brazing treatment on the pre-brazed part in the step S6.
Further, the nickel plating area in the step S2 is a torus which is distributed along the circumferential direction of the brazing surface of the outer ring, the axial size of the torus is 2 mm-3 mm, and one side of the torus is flush with the outer end surface of the outer ring.
Further, the spot welding positioning of step S4 includes the steps of: and continuously spot-welding the middle ring on the inner wall surface of the honeycomb ring for a circle by adopting an energy storage spot welding machine, continuously spot-welding the bottom ring on the inner wall surface of the honeycomb ring for a circle, and finally continuously spot-welding the outer ring on the inner wall surface of the honeycomb ring for two circles.
Further, the voltage of the continuous spot welding is 140V-160V.
Further, the axial height of the outer end face of the outer ring is larger than that of the outer end face of the honeycomb ring, so that the outer end face of the honeycomb ring and the inner wall face of the outer ring form an annular step cavity for containing the paste brazing filler metal.
Further, after the step S6 of filling the paste-like brazing filler metal, the method further includes: and heating and drying the paste solder at the temperature of 95-105 ℃ for 20-40 min, cooling, and adhering the adhesive tape solder on the surface of the paste solder to form an adhesive tape solder layer to obtain the pre-brazed part.
Furthermore, the diameter of the paste solder is phi 0.7-0.9 mm; the thickness of the adhesive tape brazing filler metal layer is 0.2 mm-0.3 mm.
Further, the forward voltage of the brush plating of the special nickel in the step S3 is 10V-15V, and the brush plating time is 30S-50S; the forward voltage of the brush plating rapid nickel is 10V-15V, and the brush plating time is 30 s-50 s.
Further, the pressure of the compressed air for blowing sand in the sand blowing treatment in the step S2 is less than or equal to 0.25MPa.
Further, the honeycomb ring in step S1 is formed by spot welding of honeycomb bars.
Further, after the vacuum brazing process of step S7, the method further includes: the honeycomb assembly after the vacuum brazing treatment was subjected to a freon inspection and an appearance inspection.
The invention has the following beneficial effects:
according to the vacuum brazing process for the honeycomb assembly of the aircraft engine, the nickel plating area is positioned on the brazing surface of the outer ring and the honeycomb ring and close to the outer end surface of the outer ring, and the area, on which nickel plating is not carried out, of the brazing surface is a non-nickel plating area, so that local nickel brushing is carried out on the brazing surface of the outer ring. The brazing surface of the honeycomb ring and the outer ring is only close to the outer side and is a nickel plating area, other areas of the brazing surface of the honeycomb ring and the outer ring are non-nickel plating areas, so that the brazing position of the honeycomb ring is free of nickel layers, spot welding is guaranteed to be firm, the brazing surface, close to the outer end face, on the outer ring is a nickel plating area, the brazing filler metal at the connecting position of the outer end face of the honeycomb ring and the nickel plating area of the outer ring is guaranteed to have good wettability, and then energy storage spot welding positioning is conducted. When energy storage spot welding positioning is carried out, the non-nickel-plated area of the outer ring can ensure that the honeycomb ring is firmly positioned by energy storage spot welding, the nickel-plated area of the outer ring can ensure that the brazing filler metal has better wettability and spreadability, and brazing seams between the honeycomb and the outer ring are better filled during brazing, so that the continuity of the brazing seams meets the requirements. The vacuum brazing process for the honeycomb assembly of the aero-engine solves the problems that the spot welding of the honeycomb assembly made of difficult-to-weld materials such as cast high-temperature alloy and the like is not firm and the surface of a brazing seam is discontinuous, reduces the vacuum brazing repair welding rate when the outer ring and the honeycomb are brazed, improves the production efficiency and saves the manufacturing cost.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a cross-sectional view of a honeycomb assembly structure of a preferred embodiment of the present invention; and
fig. 2 is a cross-sectional view of an outer ring structure of a preferred embodiment of the present invention.
The reference numbers illustrate:
1. a honeycomb ring; 2. an outer ring; A. and (4) a nickel plating area.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a cross-sectional view of a honeycomb assembly structure of a preferred embodiment of the present invention; fig. 2 is a cross-sectional view of an outer ring structure of a preferred embodiment of the present invention.
As shown in fig. 1 and 2, the vacuum brazing process for the aero-engine honeycomb assembly of the present embodiment, the honeycomb assembly including a honeycomb ring 1 and an outer ring 2, comprises the steps of:
s1, preparing a honeycomb ring 1, and filling adhesive tape brazing filler metal into the honeycomb ring 1;
s2, the brazing surface of the honeycomb ring 1 and the outer ring 2 comprises a nickel plating area and a non-nickel plating area, the non-nickel plating area of the outer ring 2 is protected by a protection piece, the brazing surface, close to the outer end face, of the outer ring 2 is the nickel plating area, sand blowing treatment is carried out on the nickel plating area, and the surface of the outer ring 2 is cleaned after sand blowing;
s3, brushing special nickel on the nickel plating area of the outer ring 2, brushing quick nickel, and removing the protection piece;
s4, combining the honeycomb ring 1 filled with the adhesive tape brazing filler metal in the step S1 with the outer ring 2 in the step S3 to sleeve the outer ring 2 on the outer wall surface of the honeycomb ring 1;
s5, spot welding positioning is carried out on the honeycomb ring 1 in the step S4;
s6, filling a paste solder into the joint of the outer end face of the honeycomb ring 1 and the inner wall face of the outer ring 2 in the step S5 to obtain a pre-brazing part;
and S7, performing vacuum brazing treatment on the pre-brazed part in the step S6.
According to the vacuum brazing process for the honeycomb assembly of the aircraft engine, the nickel plating area is positioned on the brazing surface of the outer ring and the honeycomb ring and is close to the outer end surface of the outer ring, and the area, on which the nickel plating is not carried out, of the brazing surface is the non-nickel plating area, so that the local nickel brushing and plating can be carried out on the brazing surface of the outer ring. The brazing surface of the honeycomb ring and the outer ring is only close to the outer side and is a nickel plating area, other areas of the brazing surface of the honeycomb ring and the outer ring are non-nickel plating areas, so that the brazing position of the honeycomb ring is free of nickel layers, spot welding is guaranteed to be firm, the brazing surface, close to the outer end face, on the outer ring is a nickel plating area, the brazing filler metal at the connecting position of the outer end face of the honeycomb ring and the nickel plating area of the outer ring is guaranteed to have good wettability, and then energy storage spot welding positioning is conducted. When energy storage spot welding positioning is carried out, the non-nickel-plated area of the outer ring can ensure that the honeycomb ring is positioned firmly by energy storage spot welding, the nickel-plated area of the outer ring can ensure that the brazing filler metal has better wettability and spreadability, and the brazing seam between the honeycomb and the outer ring is filled better during brazing, so that the continuity of the brazing seam meets the requirement. The vacuum brazing process for the honeycomb assembly of the aero-engine solves the problems that the spot welding of the honeycomb assembly made of difficult-to-weld materials such as cast high-temperature alloy and the like is not firm and the surface of a brazing seam is discontinuous, reduces the vacuum brazing repair welding rate when the outer ring and the honeycomb are brazed, improves the production efficiency and saves the manufacturing cost.
As shown in fig. 2, preferably, the nickel plating region in step S2 is a torus distributed along the circumferential direction of the brazing surface of the outer ring 2, the axial dimension of the torus is 2mm to 3mm, and one side of the torus is flush with the outer end surface of the outer ring 2. The height of each core grid of the honeycomb ring is 0.8mm, 2-4 honeycomb core grids are arranged in the width of 2-3 mm, if the width is less than 2mm, nickel brushing on a nickel plating area corresponding to enough core grids on the honeycomb ring cannot be guaranteed, after brazing filler metal is added, the brazing filler metal cannot be well spread to form brazing seams, and the brazing seams are discontinuous after brazing. If the thickness is larger than 3mm, more nickel brushing areas corresponding to the honeycomb core grids are plated with nickel, the proportion of the nickel brushing areas on the whole brazing surface is increased, the strength of the honeycomb energy storage spot after welding is reduced, and a brazing seam is cracked after brazing.
In this embodiment, the spot welding positioning in step S4 includes the following steps: and continuously spot-welding the middle ring on the inner wall surface of the honeycomb ring 1 for one circle by adopting an energy storage spot welding machine, continuously spot-welding the bottom ring on the inner wall surface of the honeycomb ring 1 for one circle, and finally continuously spot-welding the outer ring on the inner wall surface of the honeycomb ring 1 for two circles. According to the spot welding positioning method, spot welding positioning is firstly carried out on the middle ring of the inner wall surface of the honeycomb ring 1, spot welding positioning is carried out on the bottom rings and the outer rings on two sides of the honeycomb ring, wherein the outer rings are continuously subjected to spot welding for two weeks, the number of the spot welding turns is increased, the spot welding density is increased, the spot welding strength is further increased, and the spot welding firmness of the outer rings is ensured, so that the positioning firmness of the outer rings 2 and the honeycomb ring 1 is ensured, the brazing gap is reduced, the wettability and the spreadability of brazing filler metal are facilitated, and brazing is facilitated.
In this embodiment, the voltage for continuous spot welding is 140V to 160V. Preferably, the voltage for continuous spot welding is 150V. The voltage of continuous spot welding is higher than 160V, and when energy storage spot welding tack welding is carried out along the honeycomb axial direction, the honeycomb surface burns seriously, and the burn depth exceeds the reserved machining allowance of 1 mm. The voltage of continuous spot welding is less than 140V, which can cause the spot welding of the honeycomb to be not firm, and the honeycomb is easy to loosen in the vacuum brazing process, thereby influencing the honeycomb brazing quality.
Preferably, the outer end face of the outer ring 2 has an axial height greater than that of the outer end face of the honeycomb ring 1, so that the outer end face of the honeycomb ring 1 and the inner wall face of the outer ring 2 form an annular step cavity for accommodating the cream solder. More preferably, the outer end face of the outer ring 2 has an axial height 0.5mm greater than the height of the outer end face of the socket ring 1.
In this embodiment, after the step S6 of filling the paste solder, the method further includes: and heating and drying the paste solder at the temperature of 95-105 ℃ for 20-40 min, cooling, and adhering the adhesive tape solder on the surface of the paste solder to form an adhesive tape solder layer to obtain the pre-brazed part. The paste brazing filler metal is filled in the annular step cavity, so that the paste brazing filler metal is effectively prevented from falling. Firstly: the paste solder is heated and dried, water in the paste solder is evaporated by heating and drying, the paste solder is solidified, and the paste solder is favorable for adhering the adhesive tape solder, however, the paste solder is not heated and dried and is soft, and the adhesive tape solder cannot be adhered on the paste solder. Secondly, the method comprises the following steps: the adhesive tape brazing filler metal has poor liquidity compared with the paste brazing filler metal, and on one hand, the adhesive tape brazing filler metal fixes the paste brazing filler metal so as to prevent the paste brazing filler metal from running off at other non-brazing seam parts after brazing; on the other hand, the brazing seam is blocked by adopting the sticky brazing filler metal, so that the discontinuity defect of the brazing seam is reduced, and the brazing seam is beneficial to continuous formation after brazing.
In this embodiment, the diameter of the paste solder is 0.7 to 0.9mm. The thickness of the adhesive tape brazing filler metal layer is 0.2 mm-0.3 mm. The paste solder and the adhesive tape solder are used together to form the brazing seam feeding amount. If the feeding amount is too low, less than phi 0.7 and the thickness is 0.2mm, enough brazing filler metal cannot be ensured, and the defects of discontinuous brazing seam surface, pits and the like are caused after brazing. If the feeding amount is too high and is higher than 0.9mm and the thickness is 0.3mm, brazing filler metal is accumulated, the R angle of a brazing seam becomes large, polishing and repairing are needed, and the production efficiency is influenced. Honeycomb erosion can also occur, resulting in scrap parts. The defect that the brazing filler metal blocks the honeycomb core cells is generated.
In the embodiment, the forward voltage of the brush plating of the special nickel in the step S3 is 10V-15V, and the brush plating time is 30S-50S; the forward voltage of the brush plating rapid nickel is 10V-15V, and the brush plating time is 30 s-50 s. The special nickel liquid is SDY201 of Wuhan material protection research institute. The rapid nickel liquid is SDY202 of Wuhan material protection research institute. The special nickel brush is mainly prepared for subsequent quick nickel brushing, so that the surface of the material is modified, and the quick nickel adhesion is facilitated. The forward voltage of the special nickel for brush plating is 10V-15V, which is the power voltage of the brush plating machine, the brush plating time is 30 s-50 s, and the thickness of the nickel layer is very thin, usually several micrometers, so that the brush plating is only required to be 30 s-50 s.
In this embodiment, the pressure of the compressed air for blowing sand in the sand blowing process in step S2 is not more than 0.25MPa. The sand blowing treatment adopts corundum sand blowing, the pressure of sand blowing compressed air is less than or equal to 0.25MPa until the sand blowing part is grey and uniform, no metal reflection bright spot exists in light inspection, and sand grains on the surface of the part are cleaned by clean compressed air after sand blowing.
Preferably, the honeycomb ring 1 in step S1 is formed by spot welding honeycomb bars to form the honeycomb ring 1.
In this embodiment, after the vacuum brazing process in step S7, the method further includes: the honeycomb assembly after the vacuum brazing treatment was subjected to freon inspection and appearance inspection. The Freon inspection is carried out, and the requirement that the welding rate is more than or equal to 75 percent is met. And performing appearance inspection to meet the requirements that the continuity of the appearance of the brazing seam is not less than 98%, the length of each discontinuity is not more than 5mm, and the distance between discontinuity defects is not less than 200 mm.
In this embodiment, the vacuum brazing process for the aircraft engine honeycomb assembly specifically includes the following steps:
s1, filling a tape-bonding brazing filler metal into a honeycomb ring 1 formed by honeycomb strip energy storage spot welding, wherein the tape-bonding brazing filler metal is AMS4777 tape-bonding brazing filler metal, each layer is 0.15mm thick, and after the first layer of tape-bonding brazing filler metal is filled, filling a second layer of tape-bonding brazing filler metal, and adding two layers of tape-bonding brazing filler metals;
s2, the brazing surface of the honeycomb ring 1 and the outer ring 2 comprises a nickel plating area and a non-nickel plating area, the non-nickel plating area of the outer ring 2 is protected by an adhesive tape, the nickel plating area is a circular ring surface arranged along the circumferential direction of the inner wall surface of the outer ring 2, the axial size of the circular ring surface is 2mm, one side of the circular ring surface is flush with the outer end surface of the outer ring 2, sand blowing is performed on the nickel plating area, emery blowing is performed on the sand blowing, the pressure of compressed air for the sand blowing is less than or equal to 0.25MPa until the sand blowing is grey and uniform, and the surface of the outer ring 2 is cleaned after the sand blowing;
s3, brush plating the nickel plating area of the outer ring 2 by using special nickel liquid of SDY201 through a brush plating machine, wherein the power voltage is 12V, the brush plating temperature is room temperature, the brush plating time is 40S, special nickel is brush plated, then, quick nickel liquid of SDY202 is used for brush plating, the power voltage is 12V, the brush plating temperature is room temperature, the brush plating time is 40S, cleaning is carried out through acetone, and then an adhesive tape is removed;
s4, combining the honeycomb ring 1 filled with the adhesive tape brazing filler metal in the step S1 with the outer ring 2 in the step S3 to enable the outer ring 2 to be sleeved on the outer wall surface of the honeycomb ring 1, wherein the axial height of the outer end surface of the outer ring 2 is larger than that of the outer end surface of the honeycomb ring 1, and an annular step cavity used for containing the paste brazing filler metal is formed between the outer end surface of the honeycomb ring 1 and the inner wall surface of the outer ring 2;
s5, performing spot welding positioning on the honeycomb ring 1 in the step S4 by adopting a CG1200 energy storage spot welding machine, continuously spot-welding the middle ring of the inner wall surface of the honeycomb ring 1 for one circle, continuously spot-welding the bottom ring of the inner wall surface of the honeycomb ring 1 for one circle, and continuously spot-welding the outer ring of the inner wall surface of the honeycomb ring 1 for two circles, wherein the voltage of the continuous spot welding is 150V;
s6, filling paste BNi82CrSiB solder into an annular step cavity of the outer end face of the honeycomb ring 1 and the inner wall face of the outer ring 2 in the step S5, wherein the paste BNi82CrSiB solder has the diameter of phi 0.8, putting the paste BNi82CrSiB solder into a 100 ℃ oven, baking for 30min to dry and cool the paste BNi82CrSiB solder, and adhering the AMS4777 sticky solder to the surface of the paste solder to form a sticky solder layer of 0.25mm to obtain a pre-brazed part;
and S7, performing vacuum brazing treatment on the pre-brazed part obtained in the step S6, performing Freon inspection on the honeycomb assembly subjected to the vacuum brazing treatment to meet the requirement that the welding rate is more than or equal to 75%, performing appearance inspection to meet the requirements that the appearance continuity of a brazing seam is not less than 98%, the discontinuous length of each part is not more than 5mm, and the interval of discontinuous defects is not less than 200 mm.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A vacuum brazing process for an aircraft engine honeycomb assembly comprising a honeycomb ring (1) and an outer ring (2), characterized by comprising the following steps:
s1, preparing a honeycomb ring (1), and filling adhesive tape brazing filler metal into the honeycomb ring (1);
s2, the brazing surface of the honeycomb ring (1) and the outer ring (2) comprises a nickel plating area and a non-nickel plating area, the non-nickel plating area of the outer ring (2) is protected by a protection piece, the brazing surface, close to the outer end face, of the outer ring (2) is the nickel plating area, sand blowing treatment is carried out on the nickel plating area, and the surface of the outer ring (2) is cleaned after sand blowing;
s3, brushing special nickel on the nickel plating area of the outer ring (2), brushing quick nickel, and removing the protection piece;
s4, combining the honeycomb ring (1) filled with the adhesive tape brazing filler metal in the step S1 with the outer ring (2) in the step S3, and sleeving the outer ring (2) on the outer wall surface of the honeycomb ring (1);
s5, performing spot welding positioning on the honeycomb ring (1) in the step S4;
s6, filling a paste solder into the joint of the outer end face of the honeycomb ring (1) and the inner wall face of the outer ring (2) in the step S5 to obtain a pre-soldering part;
and S7, performing vacuum brazing treatment on the pre-brazed part in the step S6.
2. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
the nickel plating area in the step S2 is a torus which is circumferentially distributed along the brazing surface of the outer ring (2), the axial size of the torus is 2-3 mm, and one side of the torus is flush with the outer end surface of the outer ring (2).
3. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
the spot welding positioning of the step S4 comprises the following steps:
and continuously spot-welding the middle ring positioned on the inner wall surface of the honeycomb ring (1) for one circle by adopting an energy storage spot welding machine, continuously spot-welding the bottom ring positioned on the inner wall surface of the honeycomb ring (1) for one circle, and finally continuously spot-welding the outer ring positioned on the inner wall surface of the honeycomb ring (1) for two circles.
4. The aircraft engine honeycomb assembly vacuum brazing process according to claim 3,
the voltage of the continuous spot welding is 140V-160V.
5. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
the axial height of the outer end face of the outer ring (2) is larger than that of the outer end face of the honeycomb ring (1), so that an annular step cavity for containing the paste brazing filler metal is formed by the outer end face of the honeycomb ring (1) and the inner wall face of the outer ring (2).
6. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
after the step S6, filling the paste solder, the method also comprises the following steps: and heating and drying the paste solder at the temperature of 95-105 ℃ for 20-40 min, cooling, and adhering the adhesive tape solder on the surface of the paste solder to form an adhesive tape solder layer to obtain the pre-brazed part.
7. The aircraft engine honeycomb assembly vacuum brazing process according to claim 6,
the diameter of the paste solder is phi 0.7-0.9 mm;
the thickness of the sticky brazing filler metal layer is 0.2 mm-0.3 mm.
8. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
in the step S3, the forward voltage of the brush plating of the special nickel is 10V-15V, and the brush plating time is 30S-50S;
the forward voltage of the brush plating rapid nickel is 10V-15V, and the brush plating time is 30 s-50 s.
9. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
in the step S1, the honeycomb ring (1) is formed by spot welding of honeycomb strips;
the pressure of the compressed air for sand blowing in the sand blowing treatment in the step S2 is less than or equal to 0.25MPa.
10. The aircraft engine honeycomb assembly vacuum brazing process according to claim 1,
after the vacuum brazing treatment of step S7, the method further includes: the honeycomb assembly after the vacuum brazing treatment was subjected to freon inspection and appearance inspection.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4293089A (en) * | 1979-05-08 | 1981-10-06 | The United States Of America As Represented By The United States Department Of Energy | Brazing method |
| CN101015875A (en) * | 2007-02-07 | 2007-08-15 | 顺特电气有限公司 | Brazing procedure of aluminium electric-magnetic wires and Guinea gold |
| CN101697396A (en) * | 2009-10-19 | 2010-04-21 | 宁波兴瑞电子有限公司 | Manufacturing method of F-type connector for exoticmetal contact |
| CN102416726A (en) * | 2011-08-22 | 2012-04-18 | 厦门华联电子有限公司 | Production process of single-layer mirror-surface light transmitting panel |
| CN109332837A (en) * | 2018-11-21 | 2019-02-15 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of vacuum brazing method with thin-wall part structure |
| CN109500531A (en) * | 2018-11-28 | 2019-03-22 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of low inner ring weld assembly of leading of thin-walled replaces cellular method |
| CN112958866A (en) * | 2021-03-17 | 2021-06-15 | 中国航发动力股份有限公司 | Method for vacuum brazing of large-size outer ring welded assembly |
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2021
- 2021-09-09 CN CN202111055414.0A patent/CN113878189B/en active Active
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| US4293089A (en) * | 1979-05-08 | 1981-10-06 | The United States Of America As Represented By The United States Department Of Energy | Brazing method |
| CN101015875A (en) * | 2007-02-07 | 2007-08-15 | 顺特电气有限公司 | Brazing procedure of aluminium electric-magnetic wires and Guinea gold |
| CN101697396A (en) * | 2009-10-19 | 2010-04-21 | 宁波兴瑞电子有限公司 | Manufacturing method of F-type connector for exoticmetal contact |
| CN102416726A (en) * | 2011-08-22 | 2012-04-18 | 厦门华联电子有限公司 | Production process of single-layer mirror-surface light transmitting panel |
| CN109332837A (en) * | 2018-11-21 | 2019-02-15 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of vacuum brazing method with thin-wall part structure |
| CN109500531A (en) * | 2018-11-28 | 2019-03-22 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of low inner ring weld assembly of leading of thin-walled replaces cellular method |
| CN112958866A (en) * | 2021-03-17 | 2021-06-15 | 中国航发动力股份有限公司 | Method for vacuum brazing of large-size outer ring welded assembly |
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| CN113878189A (en) | 2022-01-04 |
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