Heating device and assembly method for gas generator rotor for aircraft engine

Abstract

The present invention discloses a heating device and an assembly method for a gas generator rotor for an aircraft engine, comprising a rotor hoisting mechanism and a coil heating mechanism, wherein the rotor hoisting mechanism is located directly above the coil heating mechanism, and the coil heating mechanism comprises a workbench, a coil radius adjustment component and a coil height adjustment component, wherein the coil radius adjustment component is connected to the workbench with a bearing, and the coil radius adjustment component is driven by a motor at the lower end of the workbench. The present invention solves the problems of poor gas generator rotor assembly quality and difficulty in passing rotor balance. Through process improvement, the gas turbine rotor is changed from the original overall heating to local heating, thereby ensuring the engine assembly quality, reducing the occurrence rate of vibration failures of the aircraft engine, and greatly improving the reliability of the aircraft engine. At the same time, a rotor neck heating device is used to uniformly heat the local mounting journal of the gas turbine rotor and the compressor shaft, thereby further improving the heating efficiency and assembly quality.

Description

Technical Field

[0001] The invention relates to the technical field of production and assembly of a gas generator rotor for an aircraft engine, in particular to a heating device and an assembly method of a gas generator rotor for an aircraft engine. Background Art

[0002] The gas generator rotor is an important rotating part of the aircraft engine, providing power for the gas turbine engine. The gas generator rotor is mainly composed of the compressor rotor and the gas turbine rotor, which are positioned by the arc end teeth, and the gas turbine rotor and the compressor shaft are interference fit. In the early assembly, the gas turbine rotor was heated and kept warm as a whole. Long-term heating caused the arc end teeth of the gas turbine rotor to expand due to heat, which affected the positioning of the arc end teeth after cooling, and easily led to failure of the gas generator rotor balance inspection.

[0003] The existing assembly method is to use a special hot air gun with a temperature set to 200°C to locally heat the mounting journal of the gas turbine rotor and the compressor shaft for 5 minutes. This assembly method can strictly avoid the thermal expansion of the arc end teeth of the gas turbine rotor, which will affect the positioning of the arc end teeth after cooling and easily cause the gas generator rotor to fail the balance inspection. It greatly shortens the assembly time and improves the assembly quality.

[0004] However, manually heating the installation journal where the gas turbine rotor and the compressor shaft meet with a hot air gun is inefficient, time-consuming and labor-intensive, and can easily cause uneven heating of the installation journal, affecting the balance of the gas generator rotor. Summary of the invention

[0005] The object of the present invention is to provide a heating device and an assembly method for a gas generator rotor for an aircraft engine, so as to improve the assembly quality of the gas generator rotor.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions: a heating device for a gas generator rotor for an aircraft engine, comprising a rotor hoisting mechanism and a coil heating mechanism, wherein the rotor hoisting mechanism is located directly above the coil heating mechanism, the coil heating mechanism comprises a workbench, a coil radius adjustment component and a coil height adjustment component, the coil radius adjustment component is connected to the workbench by a bearing, the coil radius adjustment component is driven by a motor at the lower end of the workbench, and the coil height adjustment component is installed inside the coil radius adjustment component;

[0007] The coil radius adjustment assembly comprises a base plate, a gear ring is fixedly connected to the outer edge of the base plate, a slide rail is formed on the inner side of the base plate, a roller is arranged in the slide rail, an annular plate is rotatably connected to the roller, a bevel gear is meshedly connected to the gear ring, an adjusting rod is connected to the inner side of the bevel gear, the adjusting rods are distributed in a circle, there are at least three adjusting rods, and the adjusting rods are evenly distributed in the annular plate, the outer side of the adjusting rod is a cylinder, and the inner side is a screw rod, the cylindrical part of the adjusting rod passes through the annular plate and the bearing is connected in the annular plate, the screw rod part of the adjusting rod is meshed with a screw sleeve, a guide column is fixed on the outer side of the screw sleeve, a guide sleeve is fixed on the annular plate, the guide column and the guide sleeve are slidably connected, and a coil height adjustment assembly is fixed to the end of the screw sleeve;

[0008] The coil height adjustment assembly includes a guide rail and a guide block. The guide rail is fixed to the end of the coil radius adjustment assembly. The guide rail and the guide block are slidably connected. A coil bracket is fixed to one side of the guide block. At least two coil clamps are formed in the coil bracket.

[0009] According to the above technical solution, screws are threadedly connected on the outer surface of the guide rail, and the screws are fitted with the guide blocks.

[0010] According to the above technical solution, the rotor lifting mechanism includes a bracket, a lifting cylinder is fixed to the upper end of the bracket, the lower end of the lifting cylinder is connected to a clamping frame, telescopic cylinders are evenly arranged on the inner wall of the clamping frame, and the telescopic cylinders are connected to clamping claws.

[0011] The present invention also provides the following technical solution: an assembly method for a gas generator rotor for an aircraft engine, the assembly method uses the above-mentioned heating device for the gas generator rotor for an aircraft engine, a gas generator rotor assembly is fixed inside the heating device for the gas generator rotor for an aircraft engine, the gas generator rotor assembly includes a compressor shaft, a compressor rotor, a gas turbine rotor, a duplex grate and a bearing, the compressor, the gas turbine rotor, the duplex grate and the bearing are all assembled on the compressor shaft in sequence, and the duplex grate is sleeved on one end of the gas turbine rotor.

[0012] According to the above technical solution, the following steps are included:

[0013] S1. Lift the gas turbine rotor and the double comb teeth in the gas generator rotor assembly respectively by using the rotor lifting mechanism, and move the clamping claws inward by the movement of the telescopic cylinder to clamp the parts of the gas generator rotor assembly;

[0014] S2. The bottom plate is rotated by the rotation of the motor, thereby adjusting the coil radius adjustment assembly, pushing the coil support to move inward or outward, so that the diameter of the coil can match the diameter of the gas generator rotor assembly;

[0015] S3. Move the gas turbine rotor or the duplex comb teeth downward so that the parts are located in the coil heating mechanism;

[0016] S4. Fix the electromagnetic coil in the coil holder so that the electromagnetic coil is located 20mm-25mm outside the component;

[0017] S5, connecting the electromagnetic coil to a power source, starting the equipment, and heating the gas turbine rotor and the double-linked grate teeth in the electromagnetic coil respectively;

[0018] S6. Complete the assembly of the compressor rotor, the gas turbine rotor, the double-linked grate teeth and the bearings;

[0019] S7. Perform a dynamic balancing check on the assembled gas generator rotor assembly to reduce the vibration of the rotor to within the allowable range.

[0020] According to the above technical solution, in S2, when the upper and lower radii of the heating part are larger than the radius of the heating section, the radius of the coil bracket can be adjusted to be larger than the upper and lower sides of the heating section, and then the coil bracket can be moved to the heating section, and finally the circular ring formed by the coil bracket can be reduced so that the electromagnetic coil can be close to the heating section.

[0021] According to the above technical solution, in S5, the heating part is heated to 200° C. and kept warm for 5 minutes.

[0022] Compared with the prior art, the beneficial effects achieved by the present invention are as follows: through process improvement, the gas turbine rotor is changed from the original overall heating to local heating, which ensures the engine assembly quality, reduces the incidence of aircraft engine vibration failures, and greatly improves the reliability of aircraft engines. At the same time, the rotor neck heating device is used to uniformly heat the local installation journal of the gas turbine rotor and the compressor shaft, thereby improving the heating efficiency and assembly quality. The length of the adjustment rod is further adjusted by rotating the gear ring to adjust the position of the coil bracket, so that the coil can uniformly heat the journals of rotors of different specifications. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0024] Figure 1 It is a schematic diagram of the installation structure of the gas generator rotor balance of the present invention;

[0025] Figure 2 It is a schematic diagram of the local heating part of the gas turbine rotor and the double comb teeth of the present invention;

[0026] Figure 3It is a schematic structural diagram of a neck heating device for a gas generator rotor for an aircraft engine according to the present invention;

[0027] Figure 4 is a schematic diagram of a coil radius adjustment assembly of the present invention;

[0028] Figure 5 is a schematic diagram of a coil height adjustment assembly of the present invention;

[0029] In the figure: 1. bracket; 11. lifting cylinder; 12. clamping frame; 13. telescopic cylinder; 14. clamping claw; 2. workbench; 21. motor; 3. coil radius adjustment assembly; 31. gear ring; 32. bevel gear; 33. cylinder; 34. screw; 35. bottom plate; 36. screw sleeve; 37. guide sleeve; 38. guide column; 39. annular plate; 4. coil height adjustment assembly; 41. coil bracket; 42. guide rail; 43. guide block; 44. screw; 45. coil clamp; 5. gas generator rotor assembly; 51. compressor shaft; 52. compressor rotor; 53. gas turbine rotor; 54. double comb teeth; 55. bearing. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. 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.

[0031] See also Figure 3 The present invention provides a technical solution: a neck heating device for a gas generator rotor for an aircraft engine, comprising a rotor hoisting mechanism and a coil heating mechanism, wherein the rotor hoisting mechanism is located directly above the coil heating mechanism, the coil heating mechanism comprises a workbench 2, a coil radius adjustment component 3 and a coil height adjustment component 4, the coil radius adjustment component 3 is connected to the workbench 2 by a bearing, the coil radius adjustment component 3 is driven by a motor 21 at the lower end of the workbench 2, the coil height adjustment component 4 is installed inside the coil radius adjustment component 3, the rotor is hoisted by the rotor hoisting mechanism, the rotor is moved to the workbench 2, and then the height and radius of the coil are adjusted by the coil radius adjustment component 3 and the coil height adjustment component 4, so that the coil is close to the mounting journal of the gas turbine rotor and the compressor shaft, so that the power is turned on and the coil heats the mounting journal;

[0032] like Figure 4As shown, the coil radius adjustment component 3 includes a bottom plate 35, the outer edge of the bottom plate 35 is fixedly connected to a gear ring 31, a slide rail is formed on the inner side of the bottom plate 35, a roller is arranged in the slide rail, an annular plate 39 is rotatably connected to the roller, a bevel gear 32 is meshedly connected to the gear ring 31, an adjusting rod is connected to the inner side of the bevel gear 32, the adjusting rod is distributed in a circle, the outer side of the adjusting rod is a cylinder 33, the inner side is a screw 34, the cylinder 33 part of the adjusting rod passes through the annular plate 39 and the bearing is connected in the annular plate 39, the screw 34 part of the adjusting rod is meshed with a screw sleeve 36, a guide column 38 is fixed to the outer side of the screw sleeve 36, a guide sleeve 37 is fixed to the annular plate 39, the guide column 38 and the guide sleeve 37 are slidably connected, and the end of the screw sleeve 36 A coil height adjustment component 4 is fixed, and the base plate 35 is driven to rotate by the motor 21. The base plate 35 pushes the gear ring 31 to rotate, so that the bevel gear 32 on the gear ring 31 also rotates, and the rotation of the bevel gear 32 drives the adjusting rod to rotate. The adjusting rod is fixed in the annular plate 39 and cannot rotate in the annular plate 39. The rotation of the adjusting rod drives the screw 34 to rotate, and further moves the screw sleeve 36 on the screw 34. A guide column 38 is fixed to the side of the screw sleeve 36, and a guide sleeve 37 is fixed on the inner wall of the annular plate 39, so that the screw sleeve 36 is fixed to prevent it from rotating, so that the screw sleeve 36 moves along the guide column 38, and the coil height adjustment component 4 is fixed to the end of the screw 34, so that the radius of the coil can be adjusted.

[0033] There are at least three adjusting rods, which are evenly distributed in the annular plate 39 . The adjusting rods evenly distribute the height adjustment assembly 4 inside the annular plate 39 , so as to stably fix the coil.

[0034] like Figure 5 As shown, the coil height adjustment component 4 includes a guide rail 42 and a guide block 43. The guide rail 42 is fixed at the end of the coil radius adjustment component 3. The guide rail 42 and the guide block 43 are slidably connected. A coil bracket 41 is fixed on one side of the guide block 43. At least two coil clamps 45 are formed in the coil bracket 41. Through the vertically fixed guide rail 42, the guide block 43 can slide in the guide rail 42. The guide block 43 is formed with a coil bracket 41. The coil clamp 45 formed in the coil bracket 41 is used to fix the magnetic induction coil. The sliding of the guide block 43 can adjust the height of the coil bracket 41, thereby further controlling the position of the coil.

[0035] The outer surface of the guide rail 42 is threadedly connected with a screw 44 , and the screw 44 is fitted with the guide block 43 . By tightening the screw 44 , the guide block 43 is fixed in the guide rail 42 , thereby fixing the position of the coil.

[0036] The rotor hoisting mechanism includes a bracket 1, a lifting cylinder 11 is fixed to the upper end of the bracket 1, a clamping frame 12 is connected to the lower end of the lifting cylinder 11, telescopic cylinders 13 are evenly arranged on the inner wall of the clamping frame 12, and a clamping claw 14 is connected to the telescopic cylinder 13. The clamping force of the clamping claw 14 is controlled by the telescopic cylinder 13 to clamp the rotor, and the height of the clamping frame 12 is adjusted by the lifting cylinder 11, thereby controlling the height of the rotor.

[0037] The present invention provides a technical solution: Figure 1 As shown, an assembly method for a gas generator rotor for an aircraft engine uses the above-mentioned neck heating device for a gas generator rotor for an aircraft engine. A gas generator rotor assembly 5 is fixed inside the neck heating device for a gas generator rotor for an aircraft engine. The gas generator rotor assembly 5 includes a compressor shaft 51, a compressor rotor 52, a gas turbine rotor 53, a double comb teeth 54 and a bearing 55. The compressor rotor 52, the gas turbine rotor 53, the double comb teeth 54 and the bearing 55 are sequentially assembled on the compressor shaft 51, the double comb teeth 54 are sleeved on one end of the gas turbine rotor 53, the compressor rotor 52 and the gas turbine rotor 53 are positioned by arc end teeth, and the gas turbine rotor 53 and the compressor shaft 51 are interference fit.

[0038] The steps include:

[0039] S1. The gas turbine rotor 53 and the double comb teeth 54 in the gas generator rotor assembly 5 are respectively lifted by the rotor lifting mechanism, and the clamping claws 14 are moved inward by the movement of the telescopic cylinder 13 to clamp the parts of the gas generator rotor assembly 5;

[0040] S2. The motor 21 rotates to rotate the bottom plate 35, thereby adjusting the coil radius adjustment assembly 3, pushing the coil support 41 to move inward or outward, so that the diameter of the coil can match the diameter of the heating portion of the gas generator rotor assembly 5;

[0041] S3, such as Figure 2 As shown, the gas turbine rotor 53 or the double comb teeth 54 are moved downward so that the heating portion of the component is located within the coil heating mechanism;

[0042] S4, fix the electromagnetic coil in the coil support 41, so that the electromagnetic coil is located 20mm-25mm outside the component;

[0043] S5, connecting the electromagnetic coil to a power source, starting the equipment, and heating the gas turbine rotor 53 and the double-linked grate teeth 54 in the electromagnetic coil respectively;

[0044] S6, assembling the compressor rotor 52, the gas turbine rotor 53, the double comb teeth 54 and the bearing 55;

[0045] S7. Perform a dynamic balance check on the assembled gas generator rotor assembly 5 to reduce the vibration of the rotor to an allowable range.

[0046] In S2, when the upper and lower radii of the heating part are larger than the radius of the heating section, the radius of the coil bracket 41 can be adjusted to be larger than the upper and lower sides of the heating section, and then the coil bracket 41 can be moved to the heating section, and finally the circular ring formed by the coil bracket 41 can be reduced so that the electromagnetic coil can be close to the heating section.

[0047] In S5, the heating part is heated to 200°C and kept warm for 5 minutes.

[0048] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A heating device for a gas generator rotor for an aircraft engine, characterized in that: It includes a rotor hoisting mechanism and a coil heating mechanism, wherein the rotor hoisting mechanism is located directly above the coil heating mechanism, the coil heating mechanism includes a workbench, a coil radius adjustment component and a coil height adjustment component, the coil radius adjustment component is connected to the workbench by a bearing, the coil radius adjustment component is driven by a motor at the lower end of the workbench, and the coil height adjustment component is installed inside the coil radius adjustment component; The coil radius adjustment assembly comprises a base plate, a gear ring is fixedly connected to the outer edge of the base plate, a slide rail is formed on the inner side of the base plate, a roller is arranged in the slide rail, an annular plate is rotatably connected to the roller, a bevel gear is meshedly connected to the gear ring, an adjusting rod is connected to the inner side of the bevel gear, the adjusting rods are distributed in a circle, there are at least three adjusting rods, and the adjusting rods are evenly distributed in the annular plate, the outer side of the adjusting rod is a cylinder, and the inner side is a screw rod, the cylindrical part of the adjusting rod passes through the annular plate and the bearing is connected in the annular plate, the screw rod part of the adjusting rod is meshed with a screw sleeve, a guide column is fixed on the outer side of the screw sleeve, a guide sleeve is fixed on the annular plate, the guide column and the guide sleeve are slidably connected, and a coil height adjustment assembly is fixed to the end of the screw sleeve; The coil height adjustment assembly includes a guide rail and a guide block. The guide rail is fixed to the end of the coil radius adjustment assembly. The guide rail and the guide block are slidably connected. A coil bracket is fixed to one side of the guide block. At least two coil clamps are formed in the coil bracket.

2. The heating device for a gas generator rotor for an aircraft engine according to claim 1, characterized in that: The outer surface of the guide rail is threadedly connected with a screw, and the screw is fitted with the guide block.

3. The heating device for a gas generator rotor for an aircraft engine according to claim 1, characterized in that: The rotor hoisting mechanism comprises a bracket, a lifting cylinder is fixed to the upper end of the bracket, a clamping frame is connected to the lower end of the lifting cylinder, telescopic cylinders are evenly arranged on the inner wall of the clamping frame, and clamping claws are connected to the telescopic cylinders.

4. A method for assembling a gas generator rotor for an aircraft engine, characterized in that: The assembly method uses the heating device for the gas generator rotor for an aircraft engine as described in any one of claims 1 to 3 above, and a gas generator rotor assembly is fixed inside the neck heating device of the gas generator rotor for an aircraft engine, and the gas generator rotor assembly includes a compressor shaft, a compressor rotor, a gas turbine rotor, a duplex comb teeth and a bearing, and the compressor, the gas turbine rotor, the duplex comb teeth and the bearings are all assembled on the compressor shaft in sequence, and the duplex comb teeth are sleeved on one end of the gas turbine rotor.

5. The method for assembling a gas generator rotor for an aircraft engine according to claim 4, characterized in that: The steps include: S1. Lift the gas turbine rotor and the double comb teeth in the gas generator rotor assembly respectively by using the rotor lifting mechanism, and move the clamping claws inward by the movement of the telescopic cylinder to clamp the gas turbine rotor and the double comb teeth of the gas generator rotor assembly respectively; S2. The bottom plate is rotated by the rotation of the motor, thereby adjusting the coil radius adjustment assembly, pushing the coil support to move inward or outward, so that the diameter of the coil can match the diameter of the component to be heated in the gas generator rotor assembly; S3, moving the gas turbine rotor or the double comb teeth downward so that it is located inside the coil heating mechanism; S4. Fix the electromagnetic coil in the coil holder so that the electromagnetic coil is located 20mm-25mm outside the component; S5, connecting the electromagnetic coil to a power source, starting the equipment, and heating the gas turbine rotor and the double-linked grate teeth in the electromagnetic coil respectively; S6. Complete the assembly of the compressor rotor, the gas turbine rotor, the double-linked grate teeth and the bearings; S7. Perform a dynamic balancing check on the assembled gas generator rotor assembly to reduce the vibration of the rotor to within the allowable range.

6. The method for assembling a gas generator rotor for an aircraft engine according to claim 5, characterized in that: In S2, when the upper and lower radii of the heating part are larger than the radius of the heating section, the radius of the coil bracket can be adjusted to be larger than the upper and lower sides of the heating section, and then the coil bracket is moved to the heating section, and finally the circular ring formed by the coil bracket is reduced so that the electromagnetic coil can be close to the heating section.

7. The method for assembling a gas generator rotor for an aircraft engine according to claim 5, characterized in that: In the above S5, the heating part is heated to 200°C and kept warm for 5 minutes.

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