Tool and method for repairing inner ring of flame tube of combustion chamber of aero-engine

Abstract

The invention discloses a tool and method for repairing an inner ring of a flame tube of a combustion chamber of an aero-engine, and the tool comprises a base bearing which comprises a bearing plate, a bottom plate with the outer diameter larger than that of the bearing plate, and a connecting cylinder connected between the bottom plate and the bearing plate; the top plate is arranged on the bearing plate; the section of the pressing column is circular, and the diameter of the pressing column is gradually reduced from one end to the other end, so that when the pressing column presses one end of the bearing plate, the pressing column can push the top plate to move towards the outer diameter direction of the bearing plate; the cover plate comprises a supporting plate arranged on the pressing column and at least two pressing plates fixed to the periphery of the supporting plate through bolts, and the top plate is arranged between the pressing column and the pressing plates; and the adjusting bolt is used for fixing the base bearing seat, the pressing column and the cover plate and adjusting the depth of the pressing column pressed into the top plate. The inner wall of the flame tube inner ring is supported through the tool, deformation can be effectively reduced in the welding process, and the repairing quality is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of repairing a flame tube inner ring, and specifically relates to a repair tool and method for the flame tube inner ring of an aircraft engine combustion chamber. Background Art

[0002] The main combustion chamber of an aircraft engine is located between the compressor and the turbine. It is a component in which the fuel burns stably and produces high-temperature combustion gas. The combustion chamber converts the chemical energy in the fuel into thermal energy and produces a temperature field that meets the turbine inlet requirements. The fuel is sprayed into the flame tube through the fuel main pipe and the fuel nozzle for combustion, and its performance directly affects the overall efficiency and stability of the engine. The flame tube has the characteristics of high operating temperature, high pressure, complex load, and harsh working environment, and its failures are numerous and complex. At the same time, there are many product components on the unit body, which are severely deformed under high temperature conditions, and are prone to cracks, ablation, and falling blocks. Most high-frequency failures have relatively mature repair processes and methods. The welding and heat treatment of the inner ring of the flame tube belong to medium and low frequency failures, and its repair method currently uses argon arc welding. However, the argon arc welding technology used has a high temperature during the welding process, and the wear-resistant ring and the inner ring support ring are prone to deformation. Summary of the invention

[0003] In order to solve the problem of easy deformation in the existing method for repairing the inner ring of the flame tube, the present invention proposes a repair tool and method for the inner ring of the flame tube of the combustion chamber of an aircraft engine.

[0004] The objective of the present invention is achieved through the following technical solutions: The first aspect of the present invention discloses a repair tool for an inner ring of a flame tube of a combustion chamber of an aircraft engine, comprising: A base support seat, the base support seat comprises a support plate, a bottom plate with an outer diameter larger than the outer diameter of the support plate, and a connecting tube connected between the bottom plate and the support plate, and the support plate is provided with a first adjustment hole; at least two top plates, the top plates being placed on the carrier plate; a pressure column, the pressure column is placed in the middle of the top plate, the cross section of the pressure column is circular and its diameter gradually decreases from one end to the other end so that when the pressure column presses against one end of the support plate, the top plate can be pushed to move in the outer diameter direction of the support plate, and a second adjustment hole is provided at a position corresponding to the first adjustment hole of the pressure column; A cover plate, the cover plate comprising a support plate placed on the pressure column and at least two pressure plates fixed around the support plate by bolts, the support plate is provided with a third adjustment hole at a position corresponding to the second adjustment hole, and the top plate is placed between the pressure column and the pressure plate; An adjusting bolt is used to pass through the first adjusting hole, the second adjusting hole and the third adjusting hole to fix the base support, the pressure column and the cover plate and to adjust the depth of the pressure column pressed into the top plate.

[0005] The second aspect of the present invention discloses a method for repairing an inner ring of a flame tube of a combustion chamber of an aircraft engine. The method adopts the repair tool for the inner ring of a flame tube of a combustion chamber of an aircraft engine described in the first aspect. The method comprises the following steps: Place the inner ring of the flame tube to be repaired on the base support so that the front mounting end face of the inner ring of the flame tube is placed on the bottom plate. After placing the top plate, pressure column and cover plate, install the adjusting bolts and adjust the adjusting bolts so that the pressure plate is in close contact with the inner wall of the inner ring of the flame tube. Transfer the entire tooling to the processing position and weld the inner ring of the flame tube; After welding is completed, grind the welded parts.

[0006] The beneficial effects of the present invention are: The present invention realizes the support of the inner wall of the inner ring of the flame tube by adopting the tooling, which can effectively reduce deformation and improve the repair quality during welding. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0008] Figure 1 A side view of a repair tool for the inner ring of a flame tube in a combustion chamber of an aircraft engine according to the present invention; Figure 2 A top view of a repair tool for the inner ring of a flame tube in a combustion chamber of an aircraft engine according to the present invention; Figure 3 A top view of the base support; Figure 4 is a side view of the base support; Figure 5 is a top view of the top plate; Figure 6 is a cross-sectional view of the top plate; Figure 7 is a cross-sectional view of the compression column; Figure 8 It is the top view of the pressure column; Fig. 9 A structural schematic diagram of a cover plate.

[0009] The reference numerals in the figures are: 1. Cover plate; 11. Pressing plate; 12. Support plate; 121. Third adjustment hole; 2. base support; 21. support plate; 211. first adjustment hole; 22. connecting tube; 23. bottom plate; 3. top plate; 31. inclined surface; 4. Pressure column; 41. Second adjustment hole; 5. Adjust the bolt; 6. Inner ring of flame tube; 7. Rings. DETAILED DESCRIPTION

[0010] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0011] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0012] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features of the embodiments may be combined with each other.

[0013] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0014] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the invention is usually placed when in use, or the positions or positional relationships commonly understood by those skilled in the art, which are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0015] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0016] The first aspect of the present invention discloses a repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine, such as Figures 1 to 9 As shown, the tooling includes a base support 2, at least two top plates 3, a pressure column 4, a cover plate 1 and an adjusting bolt 5. The base support 2 includes a support plate 21, a bottom plate 23 whose outer diameter is larger than the outer diameter of the support plate 21, and a connecting tube 22 connected between the bottom plate 23 and the support plate 21. The support plate 21 is provided with a first adjusting hole 211; the top plate 3 is placed on the support plate 21; the pressure column 4 is placed in the middle of the top plate 3, the cross section of the pressure column 4 is circular and its diameter gradually decreases from one end to the other end so that when the pressure column 4 presses against one end of the support plate 21, the top plate 3 can be pushed to move in the direction of the outer diameter of the support plate 21. The pressure column 4 corresponds to the first adjusting hole 211. A second adjustment hole 41 is provided; the cover plate 1 includes a support plate 12 placed on the pressure column 4 and at least two pressure plates 11 fixed around the support plate 12 by bolts, and a third adjustment hole 121 is provided at a position corresponding to the support plate 12 and the second adjustment hole 41, and the top plate 3 is placed between the pressure column 4 and the pressure plate 11; the adjusting bolt 5 is used to pass through the first adjustment hole 211, the second adjustment hole 41 and the third adjustment hole 121 to realize the fixation of the base support 2, the pressure column 4 and the cover plate 1 and adjust the depth of the pressure column 4 pressed into the top plate 3. With the above structure, the front mounting end face of the flame tube inner ring 6 is placed on the bottom plate 23, and then the top plate 3 is installed on the support plate 21. The end of the pressure column 4 with a smaller diameter is placed downward between the top plates 3; then the cover plate 1 is placed on the pressure column 4 so that the pressure plate 11 is placed outside the top plate 3 and embedded in the middle of the flame tube inner ring support ring. The adjusting bolt is screwed in, and the pressure column 4 moves downward to push the top plate 3 outward, thereby pushing the pressure plate 11 to further press the flame tube inner ring support ring to achieve support.

[0017] In order to reduce the overall weight of the tooling, reduce the support cost and the lifting weight, weight-reducing holes are provided on the base support 2 and / or the top plate 3 .

[0018] There are many ways to implement the pressing plate 11. Preferably, Fig. 9 As shown, in order to reduce damage to the inner ring 6 of the flame tube, the pressure plate 11 is arc-shaped.

[0019] In order to facilitate the installation of the pressing plate 11 and reduce the overall quality of the tooling, Fig. 9 As shown, the support plate 12 includes a middle plate and a connecting strip connected between the middle plate and the pressing plate 11 , and the third adjustment hole 121 is provided on the middle plate.

[0020] In order to enhance the stability of the tooling structure, fixing holes are provided on the connecting strips, and fixing bolts are used to further fix the cover plate 1 and the base support 2.

[0021] In order to facilitate the lifting of the tooling, a lifting hole for fixing the lifting ring 7 is provided on the connecting bar.

[0022] There are many implementations of the top plate 3, preferably, Figure 5 As shown, the top plate 3 is fan-shaped. In order to achieve effective support of the inner ring 6 of the flame tube, multiple top plates 3 can be provided. For example, 4, 5, 6, 7, 8 or even more top plates 3 can be provided along the circumference of the pressure column 4.

[0023] In order to facilitate the rapid installation of the pressure column 4 between multiple top plates 3, as shown in FIG. Figure 6 As shown, an inclined surface 31 is provided at the inner diameter end of the top plate 3 .

[0024] Based on the above-mentioned tooling, the second aspect of the present invention discloses a method for repairing the inner ring of a flame tube of a combustion chamber of an aircraft engine. The method is implemented using a tooling for repairing the inner ring of a flame tube of a combustion chamber of an aircraft engine in the first aspect. The method includes steps S11 to S13.

[0025] Step S11, place the inner ring of the flame tube to be repaired on the base support 2 so that the front mounting end face of the inner ring of the flame tube is placed on the bottom plate 23, after placing the top plate 3, the pressure column 4, and the cover plate 1, install the adjusting bolt 5, and adjust the adjusting bolt 5 to make the pressure plate 11 fit tightly against the inner wall of the inner ring of the flame tube.

[0026] Specifically, place one end of the bottom plate 23 of the base support 2 horizontally downward, and install the front mounting end face of the flame tube inner ring downward onto the base support 2, so that the front mounting end face of the flame tube inner ring contacts the bottom plate 23, and the support plate 21 is placed inside the flame tube inner ring.

[0027] Place the top plate 3 evenly distributed on the support plate 21, and place the end of the pressure column 4 with a smaller diameter downward in the top plate 3. At this time, the pressure column 4 is placed on the inclined surface 31 of the top plate 3. Then place the cover plate 1 on the pressure column 4, so that the pressure plate 11 is embedded in the middle of the inner ring support ring of the flame tube. Fix the adjustment bolt 5, so that the pressure column 4 moves downward and the top plate 3 moves around to squeeze the pressure plate 11 to achieve close support with the inner ring support ring of the flame tube.

[0028] Step S12: transfer the entire tooling to the processing position and weld the inner ring of the flame tube.

[0029] After the lifting ring 7 is installed, the entire tooling is hoisted to the processing position and welding can be carried out.

[0030] Step S13: After welding is completed, the welding part is polished.

[0031] After welding is completed, use a pneumatic grinding pen to grind the welding part until it is flush with the main body, perform heat treatment to eliminate stress, move the entire tooling out of the workstation, and remove the adjusting bolts and fixing bolts.

[0032] By adopting the above structure, the inner ring of the flame tube can be effectively supported from the inside through the tooling, which can reduce the deformation during the welding process and improve the repair quality.

[0033] Those skilled in the art will appreciate that the embodiments described herein are intended to help readers understand the principles of the present invention, and should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific variations and combinations that do not deviate from the essence of the present invention based on the technical revelations disclosed by the present invention, and these variations and combinations are still within the protection scope of the present invention.

Claims

1. A repair tool for the inner ring of the flame tube of an aircraft engine combustion chamber, characterized in that: include: A base support (2), the base support (2) comprising a support plate (21), a bottom plate (23) having an outer diameter greater than that of the support plate (21), and a connecting tube (22) connected between the bottom plate (23) and the support plate (21), wherein the support plate (21) is provided with a first adjustment hole (211); at least two top plates (3), the top plates (3) being placed on the support plate (21); a pressure column (4), the pressure column (4) being disposed in the middle of the top plate (3), the pressure column (4) having a circular cross section and a diameter that gradually decreases from one end to the other end so that when the pressure column (4) presses against one end of the support plate (21), the top plate (3) can be pushed to move in the outer diameter direction of the support plate (21), and a second adjustment hole (41) is provided at a position corresponding to the first adjustment hole (211); A cover plate (1), the cover plate (1) comprising a support plate (12) placed on the pressure column (4) and at least two pressure plates (11) fixed to the periphery of the support plate (12) by bolts, a third adjustment hole (121) being arranged at a position corresponding to the second adjustment hole (41) on the support plate (12), and the top plate (3) being placed between the pressure column (4) and the pressure plate (11); An adjusting bolt (5), the adjusting bolt (5) being used to pass through the first adjusting hole (211), the second adjusting hole (41) and the third adjusting hole (121) to achieve fixation of the base support (2), the pressure column (4) and the cover plate (1) and to adjust the depth of the pressure column (4) pressed into the top plate (3).

2. The repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to claim 1, characterized in that: The base support (2) and / or the top plate (3) are provided with weight-reducing holes.

3. The repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to claim 1, characterized in that: The pressing plate (11) is arc-shaped.

4. The repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to claim 1, characterized in that: The support plate (12) comprises an intermediate plate and a connecting strip connected between the intermediate plate and the pressing plate (11), and the third adjustment hole (121) is arranged on the intermediate plate.

5. The repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to claim 4, characterized in that: The connecting strip is provided with a fixing hole and / or a lifting hole for fixing the lifting ring (7).

6. The repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to claim 1, characterized in that: The top plate (3) is fan-shaped.

7. The repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to claim 1, characterized in that: The inner diameter end of the top plate (3) is provided with an inclined surface (31).

8. A method for repairing the inner ring of a flame tube in a combustion chamber of an aircraft engine, characterized in that: The method adopts a repair tool for the inner ring of the flame tube of the combustion chamber of an aircraft engine according to any one of claims 1 to 7, and the method comprises the following steps: Place the inner ring of the flame tube to be repaired on the base support (2) so that the front mounting end face of the inner ring of the flame tube is placed on the bottom plate (23), and after placing the top plate (3), the pressure column (4), and the cover plate (1), install the adjusting bolt (5), and adjust the adjusting bolt (5) so that the pressure plate (11) is in close contact with the inner wall of the inner ring of the flame tube; Transfer the entire tooling to the processing position and weld the inner ring of the flame tube; After welding is completed, grind the welded parts.

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