CN210141598U - Precision pipeline of aircraft engine and fuel nozzle of aircraft engine - Google Patents
Precision pipeline of aircraft engine and fuel nozzle of aircraft engine Download PDFInfo
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- CN210141598U CN210141598U CN202020123844.6U CN202020123844U CN210141598U CN 210141598 U CN210141598 U CN 210141598U CN 202020123844 U CN202020123844 U CN 202020123844U CN 210141598 U CN210141598 U CN 210141598U
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Abstract
The utility model provides an aircraft engine precision pipeline and aircraft engine fuel nozzle thereof, the aircraft engine precision pipeline comprises a first pipeline main body, a second pipeline main body, an inner nested pipe and a plurality of brazing filling pieces, one end of the inner nested pipe is installed in the second pipeline main body, and the brazing filling pieces are sleeved outside the inner nested pipe; the other end of the inner nested pipe is installed in the first pipeline main body, the first pipeline main body and the second pipeline main body are buckled up and down, the brazing filling piece is clamped between the first pipeline main body and the second pipeline main body to form an assembly gap, and brazing filler metal is filled in the assembly gap to weld the first pipeline main body and the second pipeline main body into a whole. The utility model discloses a this kind of filling structure can realize filling completely of brazing filler metal to the welding seam, and the brazing seam does not have defects such as hole and not seam, has guaranteed that the brazing seam quality accords with design operation requirement, provides technical support for the application of accurate pipeline welded structure in aeroengine.
Description
Technical Field
The utility model relates to an aeroengine field, in particular to aeroengine precision pipeline and aeroengine fuel nozzle thereof.
Background
In the field of aeroengines, the brazing technology is widely applied to manufacturing and assembling of high-temperature alloy precision parts of the aeroengines, and has the advantages of high welding precision, small influence on base metals, weldable complex structures and the like. For example, the additive manufacturing fuel nozzle assembly needs to be connected with multiple oil passages and multiple air passages, and different parts are provided with multiple parallel internal pipelines which are connected through a brazing process.
At present, an embedded sleeve structure is generally used, and a brazing process is adopted to connect multiple pipelines inside different parts. FIG. 1 is a perspective view of a precision pipeline of an aircraft engine in the prior art. Fig. 2 is a schematic diagram of the internal structure of a precision pipeline of an aircraft engine in the prior art. Fig. 3 is an enlarged view of a portion a in fig. 2.
As shown in fig. 1 to 3, the inner nested tube 10 is assembled in the lower part 20 before brazing, brazing filler metal is placed at the assembling surface between the lower part 20 and the upper part 30, and then the upper part 30 is assembled and brazed, and the welded structure is shown in a cross-sectional view in fig. 2.
The qualification rate of parts brazed by using the welding structure is low, and as shown in figure 3, the welding seam 11 between the inner nested pipe 10 and the pipeline is often partially not welded and the like.
The main reasons for the above problems are: the smaller assembly gap between the upper part 30 and the lower part 20 will accommodate a smaller amount of solder, while the larger number of inner nested tubes will provide an insufficient amount of solder to completely fill the solder joints between the inner nested tubes and the tubing. If the fitting clearance between the upper part 30 and the lower part 20 is increased, the capillary force is reduced, thereby reducing the fluidity of the brazing filler metal.
In the fuel nozzle of the aircraft engine, a brazing process is adopted to connect a plurality of parallel pipelines in two parts. As shown in fig. 2, a pipe line connecting an upper member 30 and a lower member 20 is generally formed by using an inner nested pipe 10, and after brazing filler metal is put into an assembly gap between the upper member 30 and the lower member 20, the assembly members are brazed in a furnace. And the brazing filler metal flows into the gap to realize the connection of the inner nested pipe and the pipeline through the capillary action of the gap between the inner nested pipe and the pipeline.
However, due to the small assembly gap between the upper part 30 and the lower part 20, the pre-positioned brazing filler metal is often not sufficient to fill the weld. In addition, the welding structure is positioned in the part, the temperature rise is slow, the actual temperature is possibly lower than the set brazing temperature, and the flowability of the brazing filler metal is poor. Therefore, the weld joint often has the defects of non-welding and the like, and the welding quality requirement is difficult to meet.
In view of the above, those skilled in the art have developed brazing connection structures for precision pipelines of aircraft engines in order to overcome the above-mentioned technical problems.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is that the structure qualification rate of brazing in order to overcome the accurate pipeline of aeroengine among the prior art is lower, and the defect that local not welded together appears in the welding seam easily, provides an accurate pipeline of aeroengine and aeroengine fuel nozzle thereof.
The utility model discloses a solve above-mentioned technical problem through following technical scheme:
the precise pipeline of the aero-engine is characterized by comprising a first pipeline main body, a second pipeline main body, an inner nested pipe and a plurality of brazing fillers, wherein one end of the inner nested pipe is installed in the second pipeline main body, and the brazing fillers are sleeved outside the inner nested pipe;
the other end of the inner nested pipe is installed in the first pipeline main body, the first pipeline main body is buckled with the second pipeline main body vertically, the brazing filling piece is clamped between the first pipeline main body and the second pipeline main body to form an assembly gap, and brazing filler metal is filled in the assembly gap to weld the first pipeline main body and the second pipeline main body into a whole.
According to an embodiment of the invention, the brazing filler is a plurality of individual circular ring segments.
According to an embodiment of the invention, the brazing filler is a plurality of individual square ring segments.
According to an embodiment of the present invention, the brazing filler is a plurality of tandem structures, each of which is formed by a plurality of annular sheets connected in series in sequence.
According to an embodiment of the invention, the brazing filler piece is at least one multi-row tandem structure, which is formed by a plurality of said tandem structures in parallel.
According to an embodiment of the invention, the brazing filler is a mesh structure.
According to an embodiment of the present invention, the mesh structure comprises two semicircular sides, the two semicircular sides being opposite and connected by a straight side;
or the reticular structure comprises four semicircular edges, the semicircular edges are opposite in pairs and are respectively connected through straight edges, and the straight edges are mutually crossed;
the openings of the semicircular edges of the net-shaped structure are outward and used for clamping the outer surface of the inner nested pipe.
According to the utility model discloses an embodiment, the one end of interior nested pipe with pipeline intercommunication in the second pipeline main part, the other end of interior nested pipe with pipeline intercommunication in the first pipeline main part.
According to an embodiment of the present invention, the brazing filler metal is a paste-like brazing filler metal, or the brazing filler metal is a rapidly cooled foil strip or a rolled strip.
The utility model also provides an aeroengine fuel nozzle, a serial communication port, aeroengine fuel nozzle include as above the accurate pipeline of aeroengine.
The utility model discloses an actively advance the effect and lie in:
the utility model discloses aeroengine precision line has designed a filling structure of brazing, and this filling structure helps treating the clearance control of welding the part, and the guide brazing filler metal gets into the brazing seam of regulation to filling structure is various, easily make.
The filling structure can realize the complete filling of the solder to the welding seam, the welding seam has no defects of holes, no welding and the like, the quality of the welding seam is ensured to meet the design and use requirements, and the technical support is provided for the application of the precision pipeline welding structure in the aeroengine.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which like reference numerals refer to like features throughout, and in which:
FIG. 1 is a perspective view of a precision pipeline of an aircraft engine in the prior art.
Fig. 2 is a schematic diagram of the internal structure of a precision pipeline of an aircraft engine in the prior art.
Fig. 3 is an enlarged view of a portion a in fig. 2.
Fig. 4 is a perspective view of the precision pipeline of the aero-engine of the present invention after the first pipeline main body is removed.
Fig. 5 is the internal structure schematic diagram of the precise pipeline of the aero-engine of the present invention.
Fig. 6 is a first schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
FIG. 7 is a second schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
Fig. 8 is a third schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
Fig. 9 is a fourth schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
Fig. 10 is a fifth schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
Fig. 11 is a six schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
[ reference numerals ]
Internally nested tubes 10, 300
Weld seam 11
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
Fig. 4 is a perspective view of the precision pipeline of the aero-engine of the present invention after the first pipeline main body is removed. Fig. 5 is the internal structure schematic diagram of the precise pipeline of the aero-engine of the present invention.
As shown in fig. 4 and 5, the utility model discloses an aeroengine precision pipeline, it includes first pipeline main part 100, second pipeline main part 200, interior nested pipe 300 and a plurality of filler 400 of brazing, installs the one end of interior nested pipe 300 in second pipeline main part 200, and the outside of nested pipe 300 including filler 400 of brazing is established to the cover. The other end of the inner nested pipe 300 is installed in the first pipeline main body 100, the first pipeline main body 100 and the second pipeline main body 200 are buckled up and down, the brazing filler part 400 is clamped between the first pipeline main body 100 and the second pipeline main body 200 to form an assembly gap, and brazing filler metal is filled in the assembly gap to weld the first pipeline main body 100 and the second pipeline main body 200 into a whole. The brazing filler metal is preferably paste-like brazing filler metal, or the brazing filler metal is quenched foil strip or rolled strip, and other materials that can be used as the brazing filler metal can be used, and the above examples are only illustrative and not limiting.
Here, one end of the inner nesting pipe 300 communicates with the pipeline in the second pipeline body 200, and the other end of the inner nesting pipe 300 communicates with the pipeline in the first pipeline body 100.
Fig. 6 is a first schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention. FIG. 7 is a second schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention. Fig. 8 is a third schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention. Fig. 9 is a fourth schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention. Fig. 10 is a fifth schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention. Fig. 11 is a six schematic structural diagram of the brazing filler part in the precision pipeline of the aero-engine of the present invention.
As shown in fig. 6 to 11, the brazing filler metal in the precision pipeline of the aero-engine according to the present invention may have various structural forms. For example, the brazing filler piece 400 may be provided as a plurality of independent circular ring pieces (as shown in fig. 6), or the brazing filler piece 400 may be provided as a plurality of independent square ring pieces (as shown in fig. 7), or the brazing filler piece 400 may be provided as a plurality of tandem structures each formed by sequentially connecting a plurality of annular pieces 410 in series (as shown in fig. 8), or the brazing filler piece 400 may be provided as at least one multi-row tandem structure formed by connecting a plurality of the tandem structures in parallel (as shown in fig. 9), or the brazing filler piece 400 may be provided as a mesh structure.
The mesh structure may be configured to include two semicircular edges 420, where the two semicircular edges 420 are opposite and connected by a straight edge 430, or the mesh structure includes four semicircular edges 420, where the semicircular edges 420 are opposite in pairs and connected by straight edges 430, respectively, and the two straight edges 430 are intersected with each other to form the mesh structure (as shown in fig. 10 and 11). At the same time, the openings of the semicircular edges 420 are all arranged to face outward for snap-fitting to the outer surface of the inner nested tube 300.
According to the structure description, the utility model discloses the accurate pipeline of aeroengine is to the connection of brazing of the accurate pipeline of nested pipe in containing, has designed a filling structure of brazing, overlaps outside the nested pipe in to make the fit-up gap increase of part.
The precise pipeline of the aero-engine is designed with a brazing filling structure which can be an annular structure, a square structure, a serial structure, a multi-row serial structure, a reticular structure and the like. The filling structure is sleeved outside the inner nested pipe and enables the assembly gap between the first pipeline body and the second pipeline body to be increased.
In addition, in the present embodiment, the brazing filler member is of an annular filling structure, for example, as shown in fig. 4, 5, and 6, before brazing, the inner nest pipe 300 and the brazing filler member 400 are assembled on the second pipe body 200, brazing filler metal is placed, and then the first pipe body 100 and the second pipe body 200 are assembled. By adopting the welding structure, the quality of the brazing seam can be improved by combining proper brazing temperature and heat preservation time.
The main reasons are as follows: on the one hand, the brazing filler metal which can be accommodated in the fitting gap between the first pipe body 100 and the second pipe body 200 is increased, and the amount of the brazing filler metal which can be filled in the brazing gap between the inner nested pipe and the component is ensured. On the other hand, the gap between the brazing filler metal 400 and the first and second pipe bodies 100 and 200 is small, which facilitates the flow of the brazing filler metal to the brazing seam between the inner nested tube 300 and the first and second pipe bodies 100 and 200.
The improved pipeline welding structure is adopted for carrying out a brazing test, the problems of local non-welding, holes and the like are not found after the welding line is dissected, the appearance of the welding line is good, and the design and use requirements are met.
The utility model discloses the accurate pipeline of aeroengine adopts the vacuum brazing technology to weld the accurate pipeline of multichannel of different parts in the aeroengine, carries out welded concrete step and is:
cleaning before welding, namely cleaning a first pipeline main body 100, a second pipeline main body 200, an inner nested pipe 300 and a brazing filler piece 400 to be welded by adopting absolute ethyl alcohol, confirming that the cleanliness of the surface to be welded meets the requirement, and drying for later use;
step two, assembling, namely assembling the inner nested pipe 300, the brazing filler piece 400 and the second pipeline body 200 according to the attached figure 4;
step three: coating a brazing filler metal, which is applied to the surface of the second pipe body 200 using a paste-like brazing filler metal (e.g., AMS4777 brazing filler metal) to completely fill the assembly gap between the second pipe body 200 and the first pipe body 100;
step four: assembling, namely assembling the first pipeline main body 100 and other components according to the figure 5;
step five: placing the precision pipeline of the assembled aero-engine on a substrate in a furnace, and using a tool clamp according to the situation;
step six: performing brazing thermal circulation, heating to brazing temperature, preserving heat, cooling to be lower than 80 ℃, and discharging;
step seven: and (4) post-welding inspection, wherein the surface of the part is visually inspected, the metal luster is not oxidized, and the pipeline tightness is analyzed through flow inspection.
The brazing refers to a welding method for wetting and filling a gap of a workpiece by using brazing filler metal with a melting point lower than that of a base metal through capillary action. In the brazing process, brazing filler metal is placed in the middle or at the periphery of a weld joint, heat preservation is carried out for a short time at the brazing temperature, the brazing filler metal is enabled to be completely melted and fill the weld joint, and then a welded assembly is cooled down from the brazing temperature and the brazing filler metal is enabled to solidify.
The utility model also provides an aeroengine fuel nozzle, it includes as above the accurate pipeline of aeroengine.
To sum up, the utility model discloses aeroengine precision line has designed a filling structure of brazing, and this filling structure helps treating the clearance control of welding the part, and guide brazing filler metal gets into the brazing seam of regulation to filling structure is various, easily makes. The filling structure can realize the complete filling of the solder to the welding seam, the welding seam has no defects of holes, no welding and the like, the quality of the welding seam is ensured to meet the design and use requirements, and the technical support is provided for the application of the precision pipeline welding structure in the aeroengine.
Although particular embodiments of the present invention have been described above, it will be appreciated by those skilled in the art that these are examples only and that the scope of the present invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are all within the scope of the invention.
Claims (10)
1. An aircraft engine precision pipeline is characterized by comprising a first pipeline main body, a second pipeline main body, an inner nested pipe and a plurality of brazing fillers, wherein one end of the inner nested pipe is installed in the second pipeline main body, and the brazing fillers are sleeved outside the inner nested pipe;
the other end of the inner nested pipe is installed in the first pipeline main body, the first pipeline main body is buckled with the second pipeline main body vertically, the brazing filling piece is clamped between the first pipeline main body and the second pipeline main body to form an assembly gap, and brazing filler metal is filled in the assembly gap to weld the first pipeline main body and the second pipeline main body into a whole.
2. The aircraft engine precision pipeline according to claim 1, wherein the brazing filler piece is a plurality of independent circular ring sheets.
3. The aircraft engine precision pipeline of claim 1, wherein the brazing filler piece is a plurality of individual square ring pieces.
4. An aircraft engine precision pipeline according to claim 1, wherein the brazing filler element is a plurality of tandem structures, each tandem structure being formed by a plurality of annular sheets connected in series in sequence.
5. An aircraft engine precision tube according to claim 4, wherein the brazing filler element is at least one multi-row tandem structure formed by a plurality of said tandem structures in parallel.
6. The aircraft engine precision pipeline according to claim 1, wherein the brazing filler piece is of a net structure.
7. An aircraft engine precision pipeline according to claim 6, wherein the mesh structure comprises two semi-circular sides, the two semi-circular sides being opposed and connected by a straight side;
or the reticular structure comprises four semicircular edges, the semicircular edges are opposite in pairs and are respectively connected through straight edges, and the straight edges are mutually crossed;
the openings of the semicircular edges of the net-shaped structure are outward and used for clamping the outer surface of the inner nested pipe.
8. An aircraft engine precision pipeline according to claim 1, wherein one end of the inner nested tube communicates with the pipeline in the second pipeline body and the other end of the inner nested tube communicates with the pipeline in the first pipeline body.
9. The aircraft engine precision pipeline according to claim 1, wherein the brazing filler metal is paste brazing filler metal, or the brazing filler metal is quenched foil strip or rolled strip.
10. An aircraft engine fuel nozzle, characterised in that it comprises an aircraft engine precision line according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020123844.6U CN210141598U (en) | 2020-01-20 | 2020-01-20 | Precision pipeline of aircraft engine and fuel nozzle of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020123844.6U CN210141598U (en) | 2020-01-20 | 2020-01-20 | Precision pipeline of aircraft engine and fuel nozzle of aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN210141598U true CN210141598U (en) | 2020-03-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020123844.6U Active CN210141598U (en) | 2020-01-20 | 2020-01-20 | Precision pipeline of aircraft engine and fuel nozzle of aircraft engine |
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| CN (1) | CN210141598U (en) |
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