Aero-engine installation and transportation rack and its manufacturing method

Abstract

The present invention discloses an installation and transportation rack for an aeroengine and a manufacturing method thereof, including the following steps: S1. Imitate the shape parameters of the aeroengine to process a positioning mold; S2. Process an installation support according to the parameters of the positioning mold; S3. Fix the positioning mold and two installation supports to be connected respectively by bolts, process columns according to the parameters of the positioning mold and the installation supports, and determine the distance between the two columns; S4. Process a base for bearing the columns according to the distance between the two columns, and fix the columns and the base; S5. Remove the positioning mold; it can ensure the design accuracy rate of the installation and transportation rack for a certain type of newly developed and designed aeroengine. After a period of application, it is found that each aeroengine of this type can be accurately installed on the installation and transportation rack, solving the installation and positioning problem caused by the special structure and layout of the installation section of this type of aeroengine, and can meet the requirements of the installation and production of aeroengines.

Description

Technical Field

[0001] The present invention relates to the technical field of aero - engines, and in particular, to an installation and transportation rack for an aero - engine. In addition, the present invention also relates to a manufacturing method including the above - mentioned installation and transportation rack for an aero - engine. Background Art

[0002] Due to the requirements of the aircraft's external shape and the limitation of the assembly space, the layout of the mounting lugs of a newly developed aero - engine is relatively special. The mounting lugs are divided into two, namely left and right. The two mounting lugs are evenly arranged on the lower semi - circle of the aero - engine, and the mounting surfaces of the two mounting lugs are arranged at an included angle.

[0003] For a fully assembled aero - engine that has completed the whole - machine test at the manufacturer's location, it is necessary to transport the aero - engine to its final installation location. Since there are many accessories on the aero - engine, in order to avoid damage or deformation of the accessories on this type of aero - engine, during transportation, only the two mounting surfaces corresponding to the mounting lugs on this type of aero - engine can be used for support. It is obvious that the traditional whole - engine mounting rack for the engine cannot be used for installation and fixation. Therefore, it is necessary to re - design the installation and transportation rack for this type of aero - engine, which is difficult to meet the requirements of installation and production. Summary of the Invention

[0004] The present invention provides an installation and transportation rack for an aero - engine to solve the technical problem that the existing installation and transportation rack for an aero - engine is difficult to meet the installation and production requirements of a newly developed aero - engine.

[0005] According to one aspect of the present invention, a manufacturing method of an installation and transportation rack for an aero - engine includes the following steps:

[0006] S1. Imitate the external shape of the aero - engine to process a positioning die. Two inclined surfaces corresponding to the mounting surfaces of the aero - engine are arranged on the positioning die, and positioning holes corresponding to the mounting holes on the mounting surfaces are opened on each inclined surface;

[0007] S2. Process the mounting supports according to the parameters of the positioning die;

[0008] S3. Fix the positioning die and the two mounting supports to each other by bolts respectively, process the columns according to the parameters of the positioning die and the mounting supports, and determine the distance between the two columns;

[0009] S4. Process the base for bearing the columns according to the distance between the two columns, and fix the columns to the base;

[0010] S5. Remove the positioning die.

[0011] Further, the step S1 specifically includes the following steps:

[0012] S11. Imitate the outer circumference of the mounting surface of the aeroengine to obtain the first outer contour.

[0013] S12. Machine the first profiling block according to the obtained first outer contour, and arrange the first profiling blocks on the outer circumference of both inclined surfaces.

[0014] Furthermore, step S1 further includes the following steps:

[0015] S13. Project the aeroengine along the axial direction to obtain the second outer contour including the engine accessories.

[0016] S14. Machine the second profiling block according to the obtained second outer contour.

[0017] S15. Concentrically connect the first profiling block and the second profiling block to obtain the positioning die.

[0018] Furthermore, step S2 specifically includes the following steps:

[0019] S21. Machine the mounting plate according to the shape of the inclined surface on the first profiling block, and open through holes corresponding to the positioning holes on the mounting plate.

[0020] S22. Arrange connecting rods on the mounting plate along the radial direction of the first profiling block, arrange hinge seats at the ends of the connecting rods far from the mounting plate, and determine the length of the connecting rods according to the second profiling block so that the projection of the hinge seats along the axial direction of the first profiling block does not interfere with the second outer contour.

[0021] Furthermore, step S3 specifically includes the following steps:

[0022] S31. Fix the mounting plates of the two mounting supports to the corresponding inclined surfaces on the first profiling block through bolts respectively.

[0023] S32. Arrange a support at the top of the column, hinge the support and the hinge seat through a hinge shaft parallel to the axis of the first profiling block, and determine the height of the column when the column hangs vertically so that the second profiling block is completely suspended.

[0024] Furthermore, in step S32, the support is welded and fixed to the top of the column.

[0025] Furthermore, step S4 specifically includes the following steps:

[0026] S41. Confirm the length of the longitudinal beam according to the distance between the two columns, and then confirm the length of the cross beam according to the length of the existing transport vehicle.

[0027] S42. Weld the cross beam and the longitudinal beam to form the base.

[0028] S43. Weld the column to the base;

[0029] S44. Perform artificial aging treatment on the entire welded aviation engine installation and transportation rack.

[0030] Further, before performing the artificial aging treatment in step S44, it further includes welding a support beam for connecting the column and the base.

[0031] Further, before performing the artificial aging treatment in step S44, it further includes welding a sleeve for connecting the transport vehicle on the longitudinal beam.

[0032] According to another aspect of the present invention, there is also provided an aviation engine installation and transportation rack, which is manufactured by the manufacturing method of the above-mentioned aviation engine installation and transportation rack.

[0033] The present invention has the following beneficial effects:

[0034] The manufacturing method of the aviation engine installation and transportation rack of the present invention, by imitating the external shape parameters of the aviation engine, first making a positioning mold, and then using the positioning mold to replace the aviation engine to position the two mounting supports, thereby determining the position and height of the two columns. After the position of the column is confirmed, the base can be machined. After the column is fixedly installed on the base and the positioning mold is removed, the installation and transportation rack can be used for the transportation operation of the aviation engine; it can ensure the design accuracy rate of the installation and transportation rack for a certain type of newly developed and designed aviation engine. After a period of application, it is found that each such type of aviation engine can be accurately installed on the installation and transportation rack, and the design accuracy rate reaches 100%; it solves the installation and positioning problems caused by the special structure and layout of the installation joints of this type of aviation engine, simplifies the installation process, and can meet the installation and production requirements of new aviation engines.

[0035] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The following will refer to the drawings to further elaborate on the present invention in detail. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0037] Figure 1 is a flowchart of the manufacturing method of the aviation engine installation and transportation rack according to the preferred embodiment of the present invention;

[0038] Figure 2 is a schematic structural diagram of the positioning mold according to the preferred embodiment of the present invention;

[0039] Figure 3 It is a schematic structural diagram of the mounting plate of the preferred embodiment of the present invention;

[0040] Figure 4 It is a schematic structural diagram of the mounting support of the preferred embodiment of the present invention;

[0041] Figure 5 It is a schematic structural diagram of the connection between the mounting support and the positioning die of the preferred embodiment of the present invention;

[0042] Figure 6 It is a schematic structural diagram of the column of the preferred embodiment of the present invention;

[0043] Figure 7 It is a schematic structural diagram of the base of the preferred embodiment of the present invention;

[0044] Figure 8 It is a schematic structural diagram of the aero-engine installation and transportation rack of the preferred embodiment of the present invention;

[0045] Figure 9 It is a schematic structural diagram of the aero-engine installation and transportation rack from another perspective of the preferred embodiment of the present invention.

[0046] Legend:

[0047] 100, aero-engine; 101, mounting surface; 1, positioning die; 11, first profiling block; 111, inclined surface; 112, positioning hole; 12, second profiling block; 2, mounting support; 21, mounting plate; 22, connecting rod; 23, hinge seat; 3, column; 31, support; 32, hinge shaft; 4, base; 41, longitudinal beam; 42, cross beam; 43, sleeve; 5, support beam. Detailed implementation

[0048] The following will describe the embodiments of the present invention in detail with reference to the drawings, but the present invention can be implemented in many different ways defined and covered by the following.

[0049] As Figure 1 shown, a manufacturing method of an aero-engine installation and transportation rack includes the following steps:

[0050] S1. Carry out profile imitation processing on the shape parameters of the aero-engine 100 to produce a positioning die 1. Two inclined surfaces 111 corresponding to the mounting surface 101 of the aero-engine are arranged on the positioning die 1, and positioning holes 112 corresponding to the mounting holes on the mounting surface 101 are opened on each inclined surface 111;

[0051] S2. Process a mounting support 2 according to the parameters of the positioning die 1;

[0052] S3. Fix the positioning die 1 and the two mounting brackets 2 to each other by bolts respectively, machine the column 3 according to the parameters of the positioning die 1 and the mounting brackets 2, and determine the distance between the two columns.

[0053] S4. Machine the base 4 for bearing the columns according to the distance between the two columns 3, and fix the columns 3 to the base 4.

[0054] S5. Remove the positioning die 1.

[0055] In the manufacturing method of the aero-engine installation and transportation rack of this embodiment, by imitating the outer shape parameters of the aero-engine 100, first make the positioning die 1, and then use the positioning die 1 to replace the aero-engine 100 to position the two mounting brackets 2, so as to determine the position and height of the two columns 3. After the position of the column 3 is confirmed, the base 4 can be machined. After the column 3 is fixedly installed on the base 4 and the positioning die 1 is removed, the installation and transportation rack can be used for the transportation operation of the aero-engine; it can ensure the design accuracy rate of the installation and transportation rack for a certain type of newly developed aero-engine. After a period of application, it is found that each aero-engine of this type can be accurately installed on the installation and transportation rack, and the design accuracy rate reaches 100%; it solves the installation and positioning problem caused by the special structure and layout of the installation joint of this type of aero-engine, simplifies the installation process, and can meet the installation and production requirements of the new aero-engine.

[0056] As Figure 2 shown, in this embodiment, the step S1 specifically includes the following steps:

[0057] S11. Imitate the outer circumference of the installation surface 101 of the aero-engine to obtain the first outer contour.

[0058] S12. Machine the first profiling block 11 according to the obtained first outer contour, and arrange the two inclined surfaces 111 on the outer circumference of the first profiling block 11.

[0059] By profiling the installation surface 101 of the aero-engine, the design accuracy rate can be guaranteed. Optionally, when imitating the outer circumference of the installation surface 101 of the aero-engine, only the lower half circumference of the aero-engine can be imitated. On the one hand, it can reduce the material required for the positioning die 1 and reduce the weight of the positioning die 1; on the other hand, it can reduce the processing workload, save processing time, and thus improve production efficiency.

[0060] As Figure 2 shown, in this embodiment, the step S1 further includes the following steps:

[0061] S13. Project the aeroengine 100 along the axial direction to obtain a second external contour including the engine accessories;

[0062] S14. Machine a second profiling block 12 according to the obtained second external contour;

[0063] S15. Connect the first profiling block 11 and the second profiling block 12 concentrically to obtain a positioning die 1.

[0064] Since there are many engine accessories on the aeroengine, obtaining the second profiling block 12 by profiling is helpful for designing the size of the aeroengine installation and transportation rack, and avoiding interference between the aeroengine installation and transportation rack and the engine accessories of the aeroengine. Optionally, when machining the second profiling block 12 according to the obtained second external contour, only the part of the second external contour corresponding to the lower half circumference of the aeroengine can be selected for machining. On the one hand, it can reduce the material required for the positioning die 1 and reduce the weight of the positioning die 1; on the other hand, it can reduce the workload of machining, save machining time, and thus improve production efficiency.

[0065] In this embodiment, the step S2 specifically includes the following steps:

[0066] S21. As Figure 3 shown, machine an installation plate 21 according to the shape of the inclined surface 111 on the first profiling block 11, and a through hole 211 corresponding to the positioning hole 112 is opened on the installation plate 21;

[0067] S22. As Figure 4 shown, arrange a connecting rod 22 on the installation plate 21 along the radial direction of the first profiling block 11, arrange a hinge seat 23 at the end of the connecting rod 22 far from the installation plate 21, and determine the length of the connecting rod 22 according to the second profiling block 12 so that the projection of the hinge seat 23 along the axial direction of the first profiling block 11 does not interfere with the second external contour.

[0068] Optionally, the connecting rod 22 is arranged along the radial direction of the first profiling block 11 and is arranged at the center of the installation plate 21 to avoid deformation of the installation plate 21.

[0069] In this embodiment, the step S3 specifically includes the following steps:

[0070] S31. As Figure 5 shown, respectively fixedly connect the installation plates 21 of the two installation supports 2 and the corresponding inclined surfaces 111 on the first profiling block 11 through bolts,

[0071] S32. As Figure 6As shown in the figure, at the top of the vertical column 3, a support 31 is arranged, and the support 31 is hinged to the hinge seat 23 through a hinge shaft 32 parallel to the axis of the first profiling block 11. When the vertical column 3 hangs vertically, the height of the vertical column 3 is determined so that the second profiling block is completely suspended.

[0072] In this embodiment, in step S32, the support 31 is welded and fixed to the top of the vertical column 3, which is simple to operate and firmly connected.

[0073] As Figure 7 shown, in this embodiment, the step S4 specifically includes the following steps:

[0074] S41. Confirm the length of the longitudinal beam 41 according to the distance between the two vertical columns 3, and then confirm the length of the cross beam 42 according to the length of the existing transport vehicle;

[0075] S42. Weld the cross beam 42 and the longitudinal beam 41 to form the base 4;

[0076] S43. Weld the vertical column 3 to the cross beam 42 of the base 4 to ensure that the projection of the center of gravity of the aero-engine in the vertical direction is within the base 4;

[0077] S44. Perform artificial aging treatment on the entire welded aero-engine installation transport rack, that is, put the entire transport rack into a furnace at about 600 - 650 °C for stress relief annealing treatment after welding. The holding time is 1 hour at the holding temperature. After keeping at 600 °C in the furnace for one hour, take it out and cool it naturally to room temperature. The main function of artificial aging is to remove processing stress and avoid strain and deformation in the later stage. After heat treatment in the furnace for one hour, the stress can be effectively removed. The cooling speed with the furnace is too slow, which affects production efficiency.

[0078] Optionally, the vertical column 3 is arranged along the perpendicular bisector of the cross beam 42; since the projection of the center of gravity of this type of aero-engine in the vertical direction is not within the installation surface 101, when installing this type of aero-engine using the left and right installation surfaces 101, there is an eccentricity between the center of gravity of this type of aero-engine and the installation surface 101 in the axial direction of the engine; to solve the installation eccentricity problem, it is necessary to ensure that the center of gravity of this type of aero-engine is within the frame of the transport rack. Arranging the vertical column on the perpendicular bisector of the 3 cross beam 42 can make the center of gravity of this type of aero-engine as close as possible to the center of the base, thus avoiding the overturning of the aero-engine installation transport rack during transportation.

[0079] As Figure 7 and Figure 9 shown, in this embodiment, before the step S44 performs artificial aging treatment, it also includes welding a support beam 5 for connecting the vertical column 3 and the base 4 to prevent the vertical column 3 from tipping over.

[0080] As Figure 7As shown in the figure, in this embodiment, before the artificial aging treatment in step S44, it further includes welding sleeves 43 for connecting the transport vehicle on the longitudinal beam 41; the four sleeves 43 are in the same positions as the four positioning pins of the existing transport vehicle. During use, the sleeves 43 are correspondingly sleeved on the four positioning pins of the existing transport vehicle, and then positioning can be carried out. It can achieve universal installation and transportation, without the need to re-design the transport vehicle, and can save costs.

[0081] Please refer to Figures 2 to 9 , an installation and transportation rack for an aeroengine, which is obtained by the manufacturing method of the installation and transportation rack for an aeroengine as described above. It includes a positioning die 1, an installation support 2 for connecting the positioning die 1, a column 3 for supporting the installation support 2, and a base 4 for bearing the column 3. The positioning die 1 includes a first profiling block 11 and a second profiling block 12. Two inclined surfaces 111 parallel to the axis of the positioning die 1 are arranged on the outer circumference of the first profiling block 11. The two inclined surfaces 111 are arranged at an angle. The two installation supports 2 are respectively in close connection with the two inclined surfaces 111.

[0082] The installation support 2 includes an installation plate 21 for fitting the inclined surface 111, a connecting rod 22 arranged on the installation plate 21, and a hinge seat 23 arranged on the connecting rod 22 for connecting the column 3. A support 31 is arranged at the top of the column 3. The support 31 is hinged to the hinge seat 23 through a hinge shaft 32 parallel to the axis of the first profiling block 11. The installation support 2 can rotate around the hinge shaft 32 and can also be used for the installation surfaces of different engines, with a wider application range.

[0083] The base 4 includes a longitudinal beam 41 and a cross beam 42. The column 3 is arranged on the cross beam 42. The longitudinal beam 41 is used to connect the cross beam 42 to form a frame structure. Optionally, a support beam 5 for preventing the column 3 from tipping over is arranged between the column 3 and the cross beam 42. Optionally, sleeves 43 for connecting the transport vehicle are arranged on the longitudinal beam 41. The four sleeves 43 are in the same positions as the four positioning pins of the existing transport vehicle. During use, the sleeves 43 are correspondingly sleeved on the four positioning pins of the existing transport vehicle, and then positioning can be carried out. It can achieve universal installation and transportation, without the need to re-design the transport vehicle, and can save costs. Its structure is simple and convenient to process, and can meet the installation and production requirements of aeroengines.

[0084] In use, the two mounting supports 2 are respectively fixedly connected to the mounting surface 101 of the aero-engine 100 by screws. The two mounting supports 2 and the aero-engine 100 form an integral body. The hinge seats 23 of each mounting support 2 are hinged to the supports 31 on the corresponding columns 3 by hinge shafts 32. In the axial direction perpendicular to the aero-engine 100, the ends of the two mounting plates 21 can be limited respectively to restrict four degrees of freedom in the up, down, left, and right directions. Although the fit between the mounting support 2 and the support 31 is a clearance fit in the axial direction of the engine, through the hinge shaft 32 with a bolted structure inserted between the two, and the other end is fastened with a nut, the flipping and moving in the front and back directions can be restricted by two degrees of freedom. That is, the entire aero-engine 100 can be placed on the aero-engine installation and transportation rack without moving, thus ensuring that the entire aero-engine 100 is stable and without shaking during transportation.

[0085] When performing the installation and transportation operation, first lift the aero-engine 100 of this type and suspend it in the air. Connect and fix the mounting plates 21 of the two mounting supports 2 to the aero-engine 100 of this type through connecting screws. Then, lift the entire aero-engine 100 with the two mounting supports 2 installed, align the two hinge seats 23 with the two supports 31 on the columns, and install the aero-engine 100 with the mounting supports 2 on the columns 3 using the hinge shaft 32. Lift the entire aero-engine 100 including the aero-engine installation and transportation rack of this embodiment, place the sleeves 43 on the base 4 onto the positioning pins of the transport vehicle, and transport it to the designated work station through the transport vehicle, then the entire installation and transportation process can be completed.

[0086] When disassembling the aero-engine 100, after the transport vehicle is transported to the designated work station, first connect the lifting rope of the lifting tool to the aero-engine 100, and the electric hoist rises until the lifting rope is in a pre-tightened state, so that the aero-engine 100 and the aero-engine installation and transportation rack are in a state of about to be lifted. Then, remove the hinge shaft 32 connecting the mounting support 2 and the support 31. The lifting rope pulls the aero-engine 100 and directly lifts the aero-engine 100 to a certain height from the aero-engine installation and transportation rack. Loosen the eight connecting screws between the aero-engine 100 and the mounting plate 21, disassemble the two mounting supports 2 from the aero-engine 100, and place the mounting supports 2 at the designated work station, and the disassembly process is completed.

[0087] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A manufacturing method of an installation and transportation rack for an aeroengine, characterized in that It includes the following steps: S1. Carry out contour imitation processing on the external shape parameters of the aero-engine to produce a positioning mold. Two inclined surfaces corresponding to the mounting surface of the aero-engine are arranged on the positioning mold, and positioning holes corresponding to the mounting holes on the mounting surface are opened on each inclined surface; S2. Machine the mounting support according to the parameters of the positioning mold; S3. Fix the positioning mold and the two mounting supports respectively through bolts, machine the columns according to the parameters of the positioning mold and the mounting supports, and determine the distance between the two columns; S4. Machine the base for bearing the columns according to the distance between the two columns, and fixedly connect the columns and the base; S5. Remove the positioning mold; The step S1 specifically includes the following steps: S11. Carry out contour imitation on the outer circumference where the mounting surface of the aero-engine is located to obtain the first contour; S12. Machine the first profiling block according to the obtained first contour. The two inclined surfaces are arranged on the outer circumference of the first profiling block; S13. Project the aero-engine along the axial direction to obtain the second contour including the engine accessories; S14. Machine the second profiling block according to the obtained second contour; S15. Connect the first profiling block and the second profiling block concentrically to obtain the positioning mold; The step S2 specifically includes the following steps: S21. Machine the mounting plate according to the shape of the inclined surface on the first profiling block, and open through holes corresponding to the positioning holes on the mounting plate; S22. Arrange connecting rods on the mounting plate along the radial direction of the first profiling block, arrange hinge seats at the ends of the connecting rods far from the mounting plate, and determine the length of the connecting rods according to the second profiling block so that the projection of the hinge seats along the axial direction of the first profiling block does not interfere with the second contour; The step S3 specifically includes the following steps: S31. Fix the mounting plates of the two mounting supports to the corresponding inclined surfaces on the first profiling block respectively through bolts, S32. Arrange a support on the top of the column, hinge the support and the hinge seat through a hinge shaft parallel to the axis of the first profiling block. When the column hangs vertically, determine the height of the column so that the second profiling block is completely suspended, and at the same time determine the distance between the two columns.

2. The manufacturing method of the aero-engine mounting and transportation frame according to claim 1, characterized in that, In the step S32, the support is welded and fixed to the top of the column.

3. The manufacturing method of the aero-engine mounting and transportation frame according to claim 2, characterized in that, The step S4 specifically includes the following steps: S41. Confirm the length of the longitudinal beam according to the distance between the two columns, and then confirm the length of the cross beam according to the length of the existing transport vehicle; S42. Weld the cross beam and the longitudinal beam to form the base; S43. Weld the columns to the base; S44. Carry out artificial aging treatment on the whole welded aero-engine mounting and transportation frame.

4. The manufacturing method of the aero-engine mounting and transportation frame according to claim 3, characterized in that, Before the step S44 carries out artificial aging treatment, it also includes welding a support beam for connecting the column and the base.

5. The manufacturing method of the aero-engine mounting and transportation frame according to claim 4, characterized in that, Before the artificial aging treatment in the step S44, it further includes welding a sleeve for connecting a transport vehicle on the longitudinal beam.

6. An aircraft engine installation and transportation rack, characterized in that, It is made by the manufacturing method of the aircraft engine mounting and transport rack according to any one of claims 1 to 5.

Images