Welding tool and welding method for intermediate case supporting plate and inner case of aero-engine

Abstract

The invention belongs to the technical field of aero-engine intermediate case machining and manufacturing, and particularly relates to a welding tool and a welding method for aero-engine intermediate case supporting plates and an inner case, which are used for welding each supporting plate and the inner case, can effectively guarantee the welding precision, avoids the problems of dislocation of welding matching surfaces, deformation after welding and the like, and improves the welding quality. And therefore, the performance and the service life of the intermediate case can be guaranteed, and technical support is provided for development of a large-bypass-ratio aero-engine.

Description

Technical Field

[0001] This application belongs to the technical field of machining and manufacturing of the intermediate casing of an aero-engine, and particularly relates to a welding tooling and a welding method for the struts and the inner casing of the intermediate casing of an aero-engine. Background Art

[0002] The intermediate casing is the main load-bearing frame of the engine, mainly bearing the thrust load of the engine. It is a centrally bifurcated annular casing, mainly including an outer casing, an inner casing arranged inside the outer casing, a plurality of struts circumferentially supported between the outer casing and the inner casing, and a splitter ring arranged between the outer casing and the inner casing. The splitter ring is connected to the leading edge of each strut.

[0003] The intermediate casing as a whole is a thin-walled shell structure. The diameter of a low-bypass ratio aero-engine is about 1 meter, and its intermediate casing is usually formed by integral casting technology. While the diameter of a high-bypass ratio aero-engine is more than 2 meters, and its intermediate casing is formed by integral casting technology. During the casting process, casting defects cannot be controlled, and it is difficult to meet the use requirements of the thin-walled load-bearing structure.

[0004] Currently, for the machining and manufacturing of the intermediate casing of a high-bypass ratio aero-engine, each component is processed separately. According to technical requirements, integral casting or machining can be used, and then each component is assembled together to form the intermediate casing. Among them, argon arc welding is usually used for welding between each strut and the inner casing. However, since both the strut and the inner casing are thin-walled shell structures and the component sizes are large, argon arc welding cannot meet the high-precision welding requirements, and there are problems such as misalignment of the welding mating surface and deformation after welding, which seriously affect the performance and service life of the intermediate casing and severely restrict the development level of high-bypass ratio aero-engines.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide a welding tooling and a welding method for the struts and the inner casing of the intermediate casing of an aero-engine to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows:

[0008] On the one hand, a welding tooling for the struts and the inner casing of the intermediate casing of an aero-engine is provided, including a support positioning ring, support positioning brackets, and telescopic struts;

[0009] There are a plurality of support positioning brackets, which are equal in number to the struts and are circumferentially connected to the support positioning ring. The positions of the respective support positioning brackets in the circumferential direction of the support positioning ring correspond to the positions of the respective struts in the circumferential direction of the inner casing;

[0010] There are multiple sets of telescopic struts, with three in each set. Each set of telescopic struts is connected to each support positioning bracket. Among them, two telescopic struts are used to top against the two side walls of the corresponding support plate, and one telescopic strut is used to top against the top of the corresponding support plate, so as to realize the support and positioning of the support plate in the form of three-point support, and align the root of the support plate with the welding mating surface outside the inner casing.

[0011] Each support positioning bracket has a support positioning notch. Two telescopic struts of the corresponding group are relatively connected to the two side walls of the support positioning notch, and the remaining one telescopic strut is connected to the bottom wall of the support positioning notch.

[0012] Optionally, in the above-mentioned welding tooling for the intermediate casing support plate and the inner casing of the aero-engine, each support positioning bracket and the support positioning ring are connected by bolts.

[0013] Optionally, in the above-mentioned welding tooling for the intermediate casing support plate and the inner casing of the aero-engine, the telescopic strut adopts an electric telescopic rod, which can be telescoped by electric control, or adopts a two-section structure, and the two sections are connected by threads and can be telescoped by screwing.

[0014] Optionally, in the above-mentioned welding tooling for the intermediate casing support plate and the inner casing of the aero-engine, support positioning bosses are formed on the two side walls of each support plate;

[0015] When each support positioning bracket supports and positions the corresponding support plate, the two telescopic struts on it are topped against the support positioning bosses on the two sides of the support plate.

[0016] Optionally, in the above-mentioned welding tooling for the intermediate casing support plate and the inner casing of the aero-engine, there are multiple welding joints on the outside of the inner casing for welding with the roots of each support plate.

[0017] On the other hand, a welding method for the intermediate casing support plate and the inner casing of the aero-engine is provided, which is implemented based on the above-mentioned welding tooling for the intermediate casing support plate and the inner casing of the aero-engine, and includes:

[0018] Connect each support positioning bracket together with the telescopic struts to the support positioning ring;

[0019] Use the two telescopic struts on each support positioning bracket to top against the support positioning bosses on the two side walls of the corresponding support plate, and one to top against the top of the corresponding support plate to support and position the corresponding support plate, so that the roots of each support plate are aligned with the corresponding welding joints on the outside of the inner casing;

[0020] Weld the roots of each support plate and the corresponding welding joints on the outside of the inner casing by electron beam welding;

[0021] Heat-treat each strut, the inner casing together with the welding tooling. Then remove the welding tooling and grind off the support positioning bosses on both sides of each strut to complete the assembly between each strut and the inner casing.

[0022] The present application has at least the following beneficial technical effects:

[0023] Provide a welding tooling and a welding method for the struts and the inner casing of the intermediate casing of an aero-engine, used for welding between each strut and the inner casing, which can effectively ensure the welding precision, avoid problems such as misalignment of the welding mating surfaces and post-welding deformation, and thus can ensure the performance and service life of the intermediate casing, providing technical support for the development of high-bypass ratio aero-engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a working schematic diagram of the welding tooling for the struts and the inner casing of the intermediate casing of an aero-engine provided by an embodiment of the present application;

[0025] Figure 2 is a schematic diagram of the assembly of each strut and the inner casing provided by an embodiment of the present application;

[0026] Figure 3 is a schematic diagram of the welding mating surface provided by an embodiment of the present application;

[0027] Wherein:

[0028] 1 - support positioning ring; 2 - support positioning bracket; 3 - telescopic strut; 4 - strut; 5 - inner casing; 6 - support positioning boss; 7 - welding joint.

[0029] For better illustration of this embodiment, some contents in the drawings are omitted, enlarged or reduced, and are only used for exemplary illustration and should not be construed as a limitation to the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely in detail below with reference to the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application and are not a limitation to the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the normal design.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should have the ordinary meaning understood by those of ordinary skill in the art to which the present application belongs. The "including" used in the description of the present application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0032] In addition, the terms indicating orientation used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to specific circumstances.

[0033] A welding tooling for the intermediate casing support plate and the inner casing of an aeroengine, as Figure 1 shown, includes a support positioning ring 1, support positioning brackets 2, and telescopic rods 3.

[0034] There are multiple support positioning brackets 2, which are equal in number to the number of support plates 4, and are circumferentially connected to the support positioning ring 1. The positions of the respective support positioning brackets 2 in the circumferential direction of the support positioning ring 1 correspond to the positions of the respective support plates 4 in the circumferential direction of the inner casing 5;

[0035] The connection between each support positioning bracket 2 and the support positioning ring 1 is detachable, and specifically, bolts can be used for connection to facilitate disassembly and assembly.

[0036] There are multiple groups of telescopic rods 3, with three in each group. Each group of telescopic rods 3 is connected to each support positioning bracket 2. Among them, two telescopic rods 3 are used to abut against the two side walls of the corresponding support plate 4, and one telescopic rod 3 is used to abut against the top of the corresponding support plate 4, so as to realize the support and positioning of the support plate 4 in the form of three-point support, align the root of the support plate 4 with the welding mating surface on the outside of the inner casing 5, and then facilitate the welding of each support plate 4 to the inner casing 5, realize the assembly between each support plate 4 and the inner casing 5, avoid misalignment of the welding mating surface, ensure the consistency of the welding quality between each support plate 4 and the inner casing 5. In addition, to improve the welding accuracy, electron beam welding can be used.

[0037] Each support positioning bracket 2 can be specifically designed to have a support positioning notch. Two telescopic rods 3 of the corresponding group are relatively connected to the two side walls of the support positioning notch, and the remaining one telescopic rod 3 is connected to the bottom wall of the support positioning notch. Specifically, welding connection or bolt connection can be used.

[0038] The telescopic rod 3 can specifically adopt an electric telescopic rod, which can be telescopically controlled electrically, or adopt a two-section structure, with the two sections connected by threads and can be telescopically adjusted by screwing, so as to be able to adapt to the support and positioning of support plates 4 of different sizes.

[0039] Considering that the strut 4 is a thin-walled shell structure, if the telescopic strut 3 is directly pressed against the side walls on both sides of it, deformation is likely to occur. Therefore, it can be further designed that support positioning bosses 6 are formed on the side walls on both sides of each strut 4, as Figure 2 shown. When each support positioning bracket 2 supports and positions the corresponding strut 4, the two telescopic struts 3 on it can be pressed against the support positioning bosses 6 on both sides of the strut 4. The support positioning bosses 6 can locally enhance the strength of the side wall of the strut 4, and can avoid the deformation of the side wall of the strut 4 caused by force. After welding each strut 4 to the inner casing 5 is completed, after removing the welding fixture, the support positioning bosses 6 on both sides of each strut 4 can be ground off.

[0040] In order to facilitate the alignment and welding of each strut 4 on the inner casing 5, it is designed that there are a plurality of welding joints 7 on the outer side of the inner casing 5 for welding with the roots of each strut 4, and the welding mating surfaces are as Figure 3 shown.

[0041] In order to facilitate the alignment and welding of each strut 4 on the inner casing 5, usually reference positioning holes or reference positioning marks will be set on the inner casing 6. With the help of measuring tools, the relative positions are measured, and the adjustment is made to align and weld each strut 4 on the inner casing 5. Based on the design of this application, the relative position between the support positioning boss 6 on one side of each strut 4 and the reference positioning hole can be specifically measured, and the adjustment is made to align and weld the root of each strut 4 with each welding joint 7 on the outer side of the inner casing 5.

[0042] In addition, the energy density of electron beam welding is relatively large. In order to reduce the deformation generated in the heat affected zone, after welding each strut 4 to the inner casing 5 is completed, the welding fixture is not removed first. Each strut 4, the inner casing 5 and the welding fixture are heat-treated together. After the residual stress is eliminated, the welding fixture is removed, and the support positioning bosses 6 on both sides of each strut 4 are ground off, so as to avoid post-welding deformation, improve the post-welding yield rate, and reduce the welding cost.

[0043] Using the welding fixture for the strut and the inner casing of the aero-engine intermediate casing disclosed in the above embodiment to weld each strut 4 to the inner casing 5, the specific process can be referred to as follows:

[0044] Connect each support positioning bracket 2 together with the telescopic strut 3 to the support positioning ring 1;

[0045] With the two telescopic struts 3 on each support positioning bracket 2 pressed against the support positioning bosses 6 on the side walls on both sides of the corresponding strut 4, and one pressed against the top of the corresponding strut 4, the corresponding strut 4 is supported and positioned, so that the root of each strut 4 is aligned with the corresponding welding joint 7 on the outer side of the inner casing 5;

[0046] Weld the root of each strut 4 to the corresponding welding joint 7 on the outer side of the inner casing 5 by electron beam welding;

[0047] Heat-treat each stay 4, the inner casing 5 together with the welding fixture, then remove the welding fixture, and grind off the support positioning bosses 6 on both sides of each stay 4 to achieve the assembly between each stay 4 and the inner casing 5.

[0048] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. A welding tooling for the strut of an aero-engine intermediate case and the inner case, characterized in that It includes a support positioning ring (1), a support positioning bracket (2), and a telescopic rod (3); There are multiple support positioning brackets (2), which are equal in number to the number of support plates (4), and are circumferentially connected to the support positioning ring (1). The positions of the respective support positioning brackets (2) in the circumferential direction of the support positioning ring (1) correspond to the positions of the respective support plates (4) in the circumferential direction of the inner casing (5); There are multiple groups of telescopic rods (3), with three in each group. Each group of telescopic rods (3) is connected to the respective support positioning brackets (2). Among them, two telescopic rods (3) are used to abut against the two side walls of the corresponding support plate (4), and one telescopic rod (3) is used to abut against the top of the corresponding support plate (4), so as to support and position the support plate (4) in the form of three-point support, aligning the root of the support plate (4) with the welding mating surface on the outer side of the inner casing (5); Each support positioning bracket (2) has a support positioning notch. Two telescopic rods (3) of the corresponding group are relatively connected to the two side walls of the support positioning notch, and the remaining one telescopic rod (3) is connected to the bottom wall of the support positioning notch.

2. The welding tooling for the intermediate casing support plate and the inner casing of an aero-engine according to claim 1, characterized in that Each support positioning bracket (2) is connected to the support positioning ring (1) by bolts.

3. The welding tooling for the intermediate casing support plate and the inner casing of an aero-engine according to claim 2, characterized in that The telescopic rod (3) adopts an electric telescopic rod, which can be telescopically controlled electrically, or adopts a two-section structure, with the two sections connected by threads and can be telescoped by screwing.

4. The welding tooling for the intermediate casing support plate and the inner casing of an aero-engine according to claim 3, characterized in that Support positioning bosses (6) are formed on the two side walls of each support plate (4); When each support positioning bracket (2) supports and positions the corresponding support plate (4), the two telescopic rods (3) thereon abut against the support positioning bosses (6) on the two sides of the support plate (4).

5. The welding tooling for the intermediate casing support plate and the inner casing of an aero-engine according to claim 4, characterized in that There are multiple welding joints (7) on the outer side of the inner casing (5) for welding with the roots of the respective support plates (4).

6. A welding method for the intermediate case support plate and the inner case of an aeroengine, which is implemented based on the welding tooling for the intermediate case support plate and the inner case of the aeroengine described in claim 5, is characterized in that It includes: Connect each support positioning bracket (2) together with the telescopic rod (3) to the support positioning ring (1); With the two telescopic rods (3) on each support positioning bracket (2) abutting against the support positioning bosses (6) on the two side walls of the corresponding support plate (4) and one abutting against the top of the corresponding support plate (4), support and position the corresponding support plate (4), aligning the roots of the respective support plates (4) with the corresponding welding joints (7) on the outer side of the inner casing (5); Weld the roots of the respective support plates (4) and the corresponding welding joints (7) on the outer side of the inner casing (5) by electron beam welding; Heat-treat each support plate (4), the inner casing (5) together with the welding tooling, then remove the welding tooling, and grind off the support positioning bosses (6) on both sides of each support plate (4) to complete the assembly between each support plate (4) and the inner casing (5).

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