阅读说明：本技术 一种飞机发动机管状支架整体连接工艺 (Integral connection process for tubular support of aircraft engine ) 是由 张鹏 于 2020-12-24 设计创作，主要内容包括：本发明公开的属于飞机零部件加工技术领域,具体为一种飞机发动机管状支架整体连接工艺,步骤1：对支架管与支架接头进行表面处理,清除表面的水、油污、氧化物、毛刺与杂物；步骤2：对步骤1中的支架管与支架接头连接处的表面进行打磨,使得支架管的表面光滑,将打磨完成后的支架管插入支架接头的插接孔中,本发明采用了氩弧焊的方式对支架管与支架接头进行点焊,对焊接的位置进行初步定位后采用了激光焊接的方式进行二次焊接,提高了焊接的牢固性,焊接的强度高,相比较与普通的焊接方式,激光焊接更为美观,不存在焊接点,且相比较普通的焊接更加牢固,操作更加精细,能够使得支架管与支架接头之间连接更加可靠。(The invention discloses an integral connection process of a tubular support of an aircraft engine, belonging to the technical field of aircraft part processing, and comprising the following steps of: carrying out surface treatment on the bracket pipe and the bracket joint, and removing water, oil stains, oxides, burrs and sundries on the surface; step 2: the surface of the joint of the support pipe and the support joint in the step 1 is polished to enable the surface of the support pipe to be smooth, the polished support pipe is inserted into the inserting hole of the support joint, the argon arc welding mode is adopted to carry out spot welding on the support pipe and the support joint, the welding position is preliminarily positioned, and then secondary welding is carried out in a laser welding mode, so that the welding firmness is improved, the welding strength is high, compared with a common welding mode, the laser welding is more attractive, no welding point exists, compared with a common welding mode, the common welding is firmer, the operation is finer, and the connection between the support pipe and the support joint can be more reliable.)

1. The integral connection process of the tubular support of the aircraft engine is characterized in that: the method comprises the following steps:

step 1: and (4) carrying out surface treatment on the support pipe and the support joint, and removing water, oil stains, oxides, burrs and impurities on the surface.

Step 2: polishing the surface of the joint of the support pipe and the support joint in the step 1 to ensure that the surface of the support pipe is smooth, inserting the polished support pipe into an inserting hole of the support joint, and adjusting the axial angle deviation of the support pipe and the support joint to ensure that the gap between the support pipe and the inserting hole is less than 0.3 mm;

and step 3: preheating the support pipe and the support joint in the step 2, wherein the preheating temperature is 300-400 ℃, selecting a tungsten electrode with the diameter of 2.4mm, cleaning burrs and impurities on the surface of the tungsten electrode, and adjusting the current response range to 150-250A;

and 4, step 4: selecting a nozzle matched with the box according to the diameter of the tungsten electrode in the step 3, and selecting corresponding gas flow according to the inner diameter of the nozzle, wherein the gas flow is 0.8-1.2 times of the inner diameter of the nozzle;

and 5: spot welding is carried out on the splicing position of the bracket pipe and the bracket joint in an argon arc welding mode, and the surfaces of the bracket pipe and the bracket joint which are subjected to spot welding are cleaned;

step 6: performing sand blasting treatment on the surface of the bracket pipe and the bracket joint in the step 5, and welding the spliced part of the bracket pipe and the bracket joint after sand blasting in a laser welding mode under protective gas;

and 7: and (4) cooling the whole welded aircraft engine tubular support in the step (6) to room temperature, removing sundries on the surface of a weldment and preventing the surface from being corroded to generate the patina.

2. An aircraft engine tubular bracket integral connection process according to claim 1, characterized in that: in the step 6, the pulse width of the laser welding laser is 6ms, and the laser welding power is 3-4 kw.

3. An aircraft engine tubular bracket integral connection process according to claim 1, characterized in that: the laser welding in the step 6 comprises a plurality of laser emitters, and the speed of the laser welding is 2.1 mm/s.

4. An aircraft engine tubular bracket integral connection process according to claim 1, characterized in that: in the step 1, oxides of the bracket pipe and the bracket joint are wiped off by fine gauze, and a towel is used for wiping.

5. An aircraft engine tubular bracket integral connection process according to claim 1, characterized in that: and the protective gas in the step 6 is one or more of helium, neon and argon.

6. An aircraft engine tubular bracket integral connection process according to claim 1, characterized in that: the inner diameter of the nozzle in the step 4 is 2.5-3.5 times of the diameter of the tungsten electrode.

7. An aircraft engine tubular bracket integral connection process according to claim 1, characterized in that: and 6, the flow of the protective gas is 10-15L/min, and the distance between the laser welding nozzle and the welding line is 8mm in the laser welding process.

Technical Field

The invention relates to the technical field of airplane part processing, in particular to an integral connection process of a tubular support of an airplane engine.

Background

The strength requirement on the engine support in the aircraft production is very high, at present, the existing aircraft engine support production and processing technology is formed by directly welding a plurality of supports, a certain welding blind area exists, the existing aircraft engine support welding technology is mostly welded by adopting an argon arc welding mode, and the welding is not firm enough.

Disclosure of Invention

The invention aims to provide an integral connection process of an aircraft engine tubular support, which aims to solve the problem that welding is not firm enough due to the fact that a certain welding blind area exists and the welding is carried out in an argon arc welding mode in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme: an integral connection process of an aircraft engine tubular support comprises the following steps:

step 1: carrying out surface treatment on the bracket pipe and the bracket joint, and removing water, oil stains, oxides, burrs and sundries on the surface;

step 2: polishing the surface of the joint of the support pipe and the support joint in the step 1 to ensure that the surface of the support pipe is smooth, inserting the polished support pipe into an inserting hole of the support joint, and adjusting the axial angle deviation of the support pipe and the support joint to ensure that the gap between the support pipe and the inserting hole is less than 0.3 mm;

and step 3: preheating the support pipe and the support joint in the step 2, wherein the preheating temperature is 300-400 ℃, selecting a tungsten electrode with the diameter of 2.4mm, cleaning burrs and impurities on the surface of the tungsten electrode, and adjusting the current response range to 150-250A;

and 4, step 4: selecting a nozzle matched with the box according to the diameter of the tungsten electrode in the step 3, and selecting corresponding gas flow according to the inner diameter of the nozzle, wherein the gas flow is 0.8-1.2 times of the inner diameter of the nozzle;

and 5: spot welding is carried out on the splicing position of the bracket pipe and the bracket joint in an argon arc welding mode, and the surfaces of the bracket pipe and the bracket joint which are subjected to spot welding are cleaned;

step 6: performing sand blasting treatment on the surface of the bracket pipe and the bracket joint in the step 5, and welding the spliced part of the bracket pipe and the bracket joint after sand blasting in a laser welding mode under protective gas;

and 7: and (4) cooling the whole welded aircraft engine tubular support in the step (6) to room temperature, removing sundries on the surface of a weldment and preventing the surface from being corroded to generate the patina.

Preferably, the pulse width of the laser welding laser in the step 6 is 6ms, and the power of the laser welding is 3-4 kw.

Preferably, the laser welding in the step 6 comprises a plurality of laser emitters, and the speed of the laser welding is 2.1 mm/s.

Preferably, in the step 1, oxides of the stent tube and the stent joint are wiped off by using fine gauze, and the dry is wiped by using a towel.

Preferably, the protective gas in step 6 is one or more of helium, neon and argon.

Preferably, the inner diameter of the nozzle in the step 4 is 2.5 to 3.5 times of the diameter of the tungsten electrode.

Preferably, the flow rate of the protective gas in the step 6 is 10-15L/min, and the distance between the laser welding tip and the welding seam is 8mm in the laser welding process.

Compared with the prior art, the invention has the beneficial effects that:

1) according to the invention, the argon arc welding mode is adopted to carry out spot welding on the support pipe and the support joint, the welding position is preliminarily positioned, and then the secondary welding is carried out by adopting the laser welding mode, so that the welding firmness is improved, and the welding strength is high.

2) Compared with the common welding mode, the laser welding method is more attractive in laser welding, free of welding points, firmer in welding and finer in operation compared with the common welding method, and the connection between the support pipe and the support joint can be more reliable.

Drawings

FIG. 1 is a flow chart of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

Referring to fig. 1, the present invention provides a technical solution:

example 1:

an integral connection process of an aircraft engine tubular support comprises the following steps:

step 1: carrying out surface treatment on the bracket pipe and the bracket joint, and removing water, oil stains, oxides, burrs and sundries on the surface;

step 2: polishing the surface of the joint of the support pipe and the support joint in the step 1 to ensure that the surface of the support pipe is smooth, inserting the polished support pipe into an inserting hole of the support joint, and adjusting the axial angle deviation of the support pipe and the support joint to ensure that the gap between the support pipe and the inserting hole is less than 0.3 mm;

and step 3: preheating the support pipe and the support joint in the step 2, wherein the preheating temperature is 400 ℃, selecting a tungsten electrode with the diameter of 2.4mm, cleaning burrs and impurities on the surface of the tungsten electrode, and adjusting the current stress range to 150A;

and 4, step 4: selecting a nozzle matched with the box according to the diameter of the tungsten electrode in the step 3, and selecting corresponding gas flow according to the inner diameter of the nozzle, wherein the gas flow is 0.8 time of the inner diameter of the nozzle;

and 5: spot welding is carried out on the splicing position of the bracket pipe and the bracket joint in an argon arc welding mode, and the surfaces of the bracket pipe and the bracket joint which are subjected to spot welding are cleaned;

step 6: performing sand blasting treatment on the surface of the bracket pipe and the bracket joint in the step 5, and welding the spliced part of the bracket pipe and the bracket joint after sand blasting in a laser welding mode under protective gas;

and 7: and (4) cooling the whole welded aircraft engine tubular support in the step (6) to room temperature, removing sundries on the surface of a weldment and preventing the surface from being corroded to generate the patina.

In the step 6, the pulse width of the laser welding laser is 6ms, and the laser welding power is 3 kw.

The laser welding in the step 6 comprises a plurality of laser emitters, and the speed of the laser welding is 2.1 mm/s.

In the step 1, oxides of the bracket pipe and the bracket joint are wiped off by fine gauze, and a towel is used for wiping.

And the protective gas in the step 6 is one or more of helium, neon and argon.

The inner diameter of the nozzle in the step 4 is 2.5 times of the diameter of the tungsten electrode.

And 6, the flow of the protective gas is 10L/min, and the distance between the laser welding nozzle and the welding line is 8mm in the laser welding process.

Example 2:

an integral connection process of an aircraft engine tubular support comprises the following steps:

step 1: carrying out surface treatment on the bracket pipe and the bracket joint, and removing water, oil stains, oxides, burrs and sundries on the surface;

step 2: polishing the surface of the joint of the support pipe and the support joint in the step 1 to ensure that the surface of the support pipe is smooth, inserting the polished support pipe into an inserting hole of the support joint, and adjusting the axial angle deviation of the support pipe and the support joint to ensure that the gap between the support pipe and the inserting hole is less than 0.3 mm;

and step 3: preheating the support pipe and the support joint in the step 2, wherein the preheating temperature is 400 ℃, selecting a tungsten electrode with the diameter of 2.4mm, cleaning burrs and impurities on the surface of the tungsten electrode, and adjusting the current stress range to 200A;

and 4, step 4: selecting a nozzle matched with the box according to the diameter of the tungsten electrode in the step 3, and selecting corresponding gas flow according to the inner diameter of the nozzle, wherein the gas flow is 1 time of the inner diameter of the nozzle;

and 5: spot welding is carried out on the splicing position of the bracket pipe and the bracket joint in an argon arc welding mode, and the surfaces of the bracket pipe and the bracket joint which are subjected to spot welding are cleaned;

step 6: performing sand blasting treatment on the surface of the bracket pipe and the bracket joint in the step 5, and welding the spliced part of the bracket pipe and the bracket joint after sand blasting in a laser welding mode under protective gas;

and 7: and (4) cooling the whole welded aircraft engine tubular support in the step (6) to room temperature, removing sundries on the surface of a weldment and preventing the surface from being corroded to generate the patina.

In the step 6, the pulse width of the laser welding laser is 6ms, and the laser welding power is 4 kw.

The laser welding in the step 6 comprises a plurality of laser emitters, and the speed of the laser welding is 2.1 mm/s.

In the step 1, oxides of the bracket pipe and the bracket joint are wiped off by fine gauze, and a towel is used for wiping.

And the protective gas in the step 6 is one or more of helium, neon and argon.

The inner diameter of the nozzle in the step 4 is 3 times of the diameter of the tungsten electrode.

And 6, the flow of the protective gas is 15L/min, and the distance between the laser welding nozzle and the welding line is 8mm in the laser welding process.

Example 3:

an integral connection process of an aircraft engine tubular support comprises the following steps:

step 1: carrying out surface treatment on the bracket pipe and the bracket joint, and removing water, oil stains, oxides, burrs and sundries on the surface;

step 2: polishing the surface of the joint of the support pipe and the support joint in the step 1 to ensure that the surface of the support pipe is smooth, inserting the polished support pipe into an inserting hole of the support joint, and adjusting the axial angle deviation of the support pipe and the support joint to ensure that the gap between the support pipe and the inserting hole is less than 0.3 mm;

and step 3: preheating the support pipe and the support joint in the step 2, wherein the preheating temperature is 400 ℃, selecting a tungsten electrode with the diameter of 2.4mm, cleaning burrs and impurities on the surface of the tungsten electrode, and adjusting the current stress range to 250A;

and 4, step 4: selecting a nozzle matched with the box according to the diameter of the tungsten electrode in the step 3, and selecting corresponding gas flow according to the inner diameter of the nozzle, wherein the gas flow is 1.2 times of the inner diameter of the nozzle;

and 5: spot welding is carried out on the splicing position of the bracket pipe and the bracket joint in an argon arc welding mode, and the surfaces of the bracket pipe and the bracket joint which are subjected to spot welding are cleaned;

step 6: performing sand blasting treatment on the surface of the bracket pipe and the bracket joint in the step 5, and welding the spliced part of the bracket pipe and the bracket joint after sand blasting in a laser welding mode under protective gas;

and 7: and (4) cooling the whole welded aircraft engine tubular support in the step (6) to room temperature, removing sundries on the surface of a weldment and preventing the surface from being corroded to generate the patina.

In the step 6, the pulse width of the laser welding laser is 6ms, and the laser welding power is 4 kw.

The laser welding in the step 6 comprises a plurality of laser emitters, and the speed of the laser welding is 2.1 mm/s.

In the step 1, oxides of the bracket pipe and the bracket joint are wiped off by fine gauze, and a towel is used for wiping.

And the protective gas in the step 6 is one or more of helium, neon and argon.

The inner diameter of the nozzle in the step 4 is 3.5 times of the diameter of the tungsten electrode.

And 6, the flow of the protective gas is 15L/min, and the distance between the laser welding nozzle and the welding line is 8mm in the laser welding process.

The welding process has the advantages that the welding blind area cannot be generated, secondary welding is performed by adopting a laser welding mode, the welding firmness is improved, the welding strength is high, the laser welding is more attractive, no welding point exists, compared with common welding, the welding process is firmer, the operation is finer, the connection between the support pipe and the support joint can be more reliable, in addition, in the welding process, the surfaces of the support pipe and the support joint are repeatedly cleaned, and therefore, the influence of surface impurities on the welding firmness performance is avoided.

While there have been shown and described the fundamental principles and essential features of the invention and advantages thereof, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof; the present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.