Turboshaft engine gas generator rotor assembly device and assembly method

Abstract

The invention discloses a turboshaft engine gas generator rotor assembling device and method, and belongs to the technical field of aero-engine assembly.The turboshaft engine gas generator rotor assembling device comprises an end tooth meshing test clamp, an adjusting nut and a force transmission block which are sequentially arranged at the top of a first pull rod in a sleeving mode from top to bottom, and the adjusting nut is in threaded connection with the first pull rod; the adjusting nut is used for pushing the force transmission block to press the hydraulic pump to the top of the support. According to the gas compressor rotor stretching clamp, the stretching assembly is arranged on the second pull rod in a sleeving mode and located above the positioning sleeve, the stretching assembly is used for driving the second pull rod to ascend and descend, and then when the second pull rod ascends, the protruding part pushes the connecting expansion sleeve to be expanded and engaged with the inner threaded hole of the center pull rod. According to the invention, the end tooth meshing test of the compressor rotor assembly is carried out through the end tooth meshing test clamp before formal assembly, and the meshing condition of the end teeth of each stage of blade disc is checked; the compressor rotor is combined through the compressor rotor stretching clamp.

Description

Technical Field

[0001] The present application relates to the technical field of aeroengine assembly, and in particular, to a turboshaft engine gas generator rotor assembly device. In addition, the present application also relates to an assembly method including the turboshaft engine gas generator rotor assembly device. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] The rotor component of a certain type of engine gas generator is one of the main vibration sources of the engine. It consists of a compressor rotor assembly 100, a turbine connecting shaft 200, a gas turbine first-stage rotor 300, a gas turbine second-stage rotor 400, a first bearing 500, a second bearing 600, etc. Please refer to the attached manual for details. Figure 1 .

[0004] The compressor rotor assembly consists of 4 integral blade disks, 1 centrifugal impeller, 1 drum, 1 spoiler and 1 center tie rod 700. The integral blade disks are connected by arc end teeth. The first-stage blade disk is an integral structure with a front shaft neck, on which the first bearing inner ring, labyrinth seal and bevel gear (for accessory power extraction) are installed, which are pressed on the shaft neck with a self-locking nut. The first bearing 500 is a ball bearing used to bear the axial load of the rotor. The drum is installed between the first and second blade disks through a stopper to form a flow channel. The spoiler is located at the rear end of the fourth-stage integral blade, which introduces the sealed pressurized air into the rotor. The center tie rod 700 is used to assemble the integral blade disks of each stage together. Its front end is screwed on the first-stage blade disk by thread, and the rear end is tightened on the centrifugal impeller by a nut.

[0005] The mounting edge of the rotor connecting shaft is connected to the centrifugal impeller by bolts, and a rotating seal (for compressor outlet air sealing) is also installed on the shaft. The rotor connecting shaft is connected to the turbine connecting shaft 200 by splines. The turbine connecting shaft 200 is equipped with a second bearing 600, which is a roller bearing that only bears radial loads. It supports the rear end of the compressor rotor and the gas turbine. The gas turbine rotor assembly consists of a first-stage turbine rotor assembly, a second-stage turbine rotor assembly, etc. The rotor is fixed by 5 long bolts, and the arc end teeth are positioned. It is connected to the compressor through the splines of the turbine connecting shaft 200 and the axial locking nut.

[0006] The assembly quality of the gas generator rotor directly affects the vibration of the engine. Its structure is complex, and the high precision of parts processing and assembly puts higher requirements on the assembly process.

[0007] At present, during the gas generator rotor assembly process, due to the low pass rate of the gas turbine inner hole runout (the design requires the inner hole runout to be less than 0.03mm), the rotor connecting shaft, rotating seal, turbine connecting shaft, second bearing 600, gas turbine first-stage rotor 300, gas turbine second-stage rotor 400 and other parts are repeatedly disassembled and inspected, which often delays the production progress by one or two weeks, reduces the engine assembly efficiency, and increases production costs. Repeated assembly also causes wear and deformation of parts, which reduces the life of the parts and also brings risks to the safety of engine test runs.

[0008] Since the rotor length of this type of gas generator exceeds 700mm, and the cantilever structure length is about 200mm, and it is connected with multi-stage end teeth, it is difficult to process and assemble. The components require high precision, the consistency of repeated assembly is poor, and the parts are prone to deformation and wear during repeated assembly.

[0009] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0010] After research, the inventor found that: statistical analysis of the main links and reasons that affect the assembly cycle in the gas generator rotor assembly process found that the runout of the inner hole of the gas turbine secondary disk is less than 0.03mm, which is difficult to control, the assembly and matching repeatability is poor, and the adjustment cycle is long; the coaxiality of the rotor connecting shaft and the centrifugal impeller with the rotor fulcrum is difficult to ensure; the assembly quality of the turbine connecting shaft is difficult to control; there is a lack of process control, inspection means and tooling, and low assembly efficiency. Once the coaxiality is not good, the gas generator rotor needs to be completely disassembled.

[0011] In view of at least one of the above technical problems, the present application provides a turboshaft engine gas generator rotor assembly device, which can perform an end tooth engagement test of the compressor rotor assembly before formal assembly through an end tooth engagement test fixture to check the engagement of the end teeth of each stage of blade disk; and assemble the compressor rotor through a compressor rotor stretching fixture.

[0012] The present application also provides an assembly method using the above-mentioned turboshaft engine gas generator rotor assembly device.

[0013] According to one aspect of the present application, a turboshaft engine gas generator rotor assembly device is provided, which is used to assemble a gas generator rotor component, wherein the gas generator rotor component includes a compressor rotor assembly, a turbine connecting shaft, a gas turbine first-stage rotor, a gas turbine second-stage rotor, a center pull rod, a centrifugal impeller and a rotor connecting shaft. The turboshaft engine gas generator rotor assembly device includes an end gear meshing test fixture and a compressor rotor tensile fixture:

[0014] The end tooth meshing test fixture includes a bracket, a hydraulic pump, a force transmission block, an adjusting nut, a first tie rod and a base, the base is used to support the compressor rotor assembly and the first tie rod, the first tie rod is inserted into the compressor rotor assembly and its bottom end is connected to the base by a thread, the bracket is used to be mounted on the compressor assembly, the hydraulic pump is used to be installed on the top of the bracket, the adjusting nut and the force transmission block are sequentially sleeved on the top of the first tie rod from top to bottom, the adjusting nut is connected to the first tie rod by a thread, and the adjusting nut is used to push the force transmission block to press the hydraulic pump against the top of the bracket;

[0015] The compressor rotor stretching clamp includes a connecting expansion sleeve, a positioning plate, a stretching assembly and a second pull rod. The bottom end of the second pull rod is inserted into the compressor rotor assembly. The connecting expansion sleeve is movably sleeved at the bottom of the second pull rod. A protrusion is provided at the bottom end of the second pull rod. The positioning plate is sleeved on the second pull rod and limits the top of the connecting expansion sleeve. The stretching assembly is sleeved on the second pull rod and is located above the positioning sleeve. The stretching assembly is used to drive the second pull rod to rise and fall, and then when the second pull rod rises, the connecting expansion sleeve is pushed to expand through the protrusion and engage with the internal threaded hole of the center pull rod.

[0016] In some embodiments of the present application, the turboshaft engine gas generator rotor assembly device also includes an end tooth runout inspection gauge, which includes a clamping nut, a simulation disk, a limit block and a third pull rod. The third pull rod is used to pass through the first bearing, the compressor rotor assembly and the second bearing in sequence. The simulation disk is sleeved on the first end of the third pull rod close to the first bearing. The simulation disk is used to engage with the arc end teeth of the turbine connecting shaft. The clamping nut is sleeved on the third pull rod. The clamping nut is used to clamp the simulation disk. The limit block is sleeved on the second end of the third pull rod and is threadedly connected to the third pull rod. The limit block is used to abut the second bearing and limit the second end of the third pull rod.

[0017] In some embodiments of the present application, the stretching assembly includes a positioning pin, a positioning block and a locking piece. The positioning block is used to be movably mounted on the second pull rod and is located above the positioning plate. The positioning pin is vertically arranged on the top of the positioning plate. The positioning pin is used to cooperate with a preset U-shaped groove at the bottom of the positioning block. The locking piece is mounted on the second pull rod and is threadedly connected to the second pull rod. The locking piece is used to clamp the top of the limit positioning block. The locking piece is also used to drive the second pull rod to move up and down along the axial direction when rotating.

[0018] According to another aspect of the present application, a method for assembling a turboshaft engine gas generator rotor is provided, which includes the turboshaft engine gas generator rotor assembly device described above. The method for assembling a turboshaft engine gas generator rotor includes the following steps:

[0019] S100, use the end gear meshing test fixture to conduct the end gear meshing test of the compressor rotor assembly, connect the oil pipe between the hydraulic equipment of the compressor rotor assembly and the hydraulic pump, and repeatedly pressurize with the hydraulic pump. After the pressure is completed, disassemble the gear meshing test fixture, check the meshing of the end teeth of each level of blade disk, and if there is no problem, proceed to the next formal assembly;

[0020] S200, using a compressor rotor stretching fixture to assemble a compressor rotor assembly, driving the second pull rod to rise through the stretching assembly, and pushing the connecting expansion sleeve to expand and engage with the internal threaded hole of the center pull rod through the protrusion, rotating the positioning plate to drive the center pull rod to adjust its position and measuring the distance L from the top surface of the positioning plate to the installation end surface of the compressor rotor assembly, so that the distance L meets the preset assembly requirements;

[0021] S300, install the bracket, hydraulic pump, force transmission block and adjusting nut, connect the oil pipe between the hydraulic equipment and the hydraulic pump, repeatedly pressurize with the hydraulic pump, and use a dial indicator to check whether the compression of the back of the centrifugal impeller before and after tightening is within the design requirements;

[0022] S400, disassemble the mounting bracket, hydraulic pump, force transfer block and adjusting nut, use a feeler gauge to check the clearance between the center tie rod locking nut assembly and the centrifugal impeller. The 0.02mm thick feeler gauge should not be able to pass through, and install the first bearing;

[0023] S500, the heating rotor is connected to the shaft and then installed on the centrifugal impeller;

[0024] S600, heat the inner ring of the second bearing and install it on the turbine connecting shaft, and install the outer ring of the second bearing after the inner ring of the second bearing cools down;

[0025] S700. Install the first-stage and second-stage gas turbine rotors. The arc end tooth runout high points of the first-stage gas turbine rotor and the turbine connecting shaft are installed 180 degrees apart. The arc end tooth runout high points of the second-stage gas turbine rotor and the first-stage gas turbine rotor are also installed 180 degrees apart.

[0026] In some embodiments of the present application, in step S100, after connecting the oil pipe between the hydraulic equipment of the compressor rotor assembly and the hydraulic pump, open the hydraulic valve on the hydraulic equipment, tighten the adjusting nut until the hydraulic pump is reset, loosen 1 / 4 turn of the adjusting nut, close the hydraulic valve and pressurize through the hydraulic pump, apply a preload force of 1KN to 2KN on the compressor rotor assembly, open the hydraulic valve to relieve the hydraulic pump pressure, loosen the adjusting nut, repeat 3 to 5 times, remove the end tooth engagement test fixture, and check the engagement of the end teeth of each level of blade disk.

[0027] In some embodiments of the present application, in step S300, after connecting the oil pipe between the hydraulic equipment and the hydraulic pump, open the hydraulic valve on the hydraulic equipment, tighten the adjusting nut until the hydraulic pump is reset, loosen 1 / 4 turn of the adjusting nut, close the hydraulic valve and pressurize through the hydraulic pump, apply a preload force of 3KN to 4KN on the compressor rotor assembly, open the hydraulic valve to relieve the hydraulic pump pressure, loosen the adjusting nut, repeat three times, and then use a dial indicator to check the compression of the back of the centrifugal impeller before and after tensioning.

[0028] In some embodiments of the present application, in step S500, the wall thickness dimensions A and B are measured at the 12, 3, 6, and 9 o'clock positions on the rear flange of the centrifugal impeller and the front flange of the rotor connecting shaft, respectively. After the rotor connecting shaft is assembled, the dimension C of the connection is measured respectively, and the four selected positions are required to simultaneously satisfy A+B≤C±0.02mm.

[0029] In some embodiments of the present application, in step S500, the reference runout on the rotor connecting shaft is checked, and the runout should be no greater than 0.015 mm. If it fails, the rotor connecting shaft is disassembled and reassembled.

[0030] In some embodiments of the present application, in step S600, the end tooth runout inspection fixture is clamped onto the compressor rotor assembly, and the runout of the simulated disk is measured. The runout should be no greater than 0.025 mm. If it fails, the angular position of the simulated disk and the turbine connection shaft is adjusted clockwise, and the measurement is repeated until the runout is no greater than 0.025 mm.

[0031] In some embodiments of the present application, in step S700, a lever micrometer is used to check the inner hole runout of the gas turbine secondary rotor, which should be no more than 0.03 mm. If it fails, the gas turbine primary rotor and the gas turbine secondary rotor are separated, and the angular positions of the gas turbine primary rotor, the gas turbine secondary rotor and the turbine connecting shaft are adjusted. The measurement is repeated until the inner hole runout of the gas turbine secondary rotor is no more than 0.03 mm.

[0032] This application has the following beneficial effects:

[0033] The present application discloses a turboshaft engine gas generator rotor assembly device that uses an end tooth meshing test fixture to perform an end tooth meshing test of a compressor rotor assembly before formal assembly to check the meshing of end teeth of blade disks at all levels. The force transmission block is pushed to press the hydraulic pump against the top of the bracket by adjusting the nut, and the hydraulic pump is repeatedly pressed to apply a preload force to the compressor rotor assembly. After repeated pressure application, the end tooth meshing test fixture is disassembled to check the meshing of end teeth of blade disks at all levels to ensure that there is no problem with the meshing of end teeth of blade disks at all levels. Then, the subsequent formal assembly can be performed to improve the smoothness of the formal assembly. The present application assembles the compressor rotor through a compressor rotor stretching clamp, wherein the second pull rod is driven to rise and fall through the stretching assembly, and then when the second pull rod rises, the protrusion pushes the connecting expansion sleeve to expand and engage with the internal threaded hole of the center pull rod. At this time, the center pull rod can be driven to adjust its position by rotating the positioning plate and measure the distance L from the top surface of the positioning plate to the installation end face of the compressor rotor assembly, so that the distance L meets the preset assembly requirements to ensure that the installation dimensions are in place and improve the stability and accuracy of the assembly.

[0034] The turboshaft engine gas generator rotor assembly method of the present application also has the above-mentioned beneficial effects, and also includes adjusting the assembly dimension control requirements to improve the process accuracy in view of the problem that it is difficult to ensure the coaxiality between the rotor connecting shaft and the centrifugal impeller after the rotor fulcrum is combined; adding process control to improve the assembly quality. In view of the problem that the assembly quality of the turbine connecting shaft is difficult to control, the inspection of parts before assembly is strengthened, and the end tooth meshing test before assembly is carried out. Through the analysis of the compressor rotor structure, repeated pre-tightening-unloading pressing is carried out to make the turbine connecting shaft and the rotor connecting shaft fit completely; at the same time, the end tooth runout inspection tool is added so that the assembly quality of the turbine connecting shaft can be more intuitively reflected, ensuring its assembly quality, improving work efficiency, ensuring the assembly reliability of the engine, and improving the assembly efficiency of the engine. The assembly cycle is shortened from 4 days / unit to 1 day / unit, and good results have been achieved.

[0035] Of course, any product implementing this application does not necessarily need to achieve all the advantages described above at the same time. In addition to the purposes, features and advantages described above, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0037] Figure 1 It is a schematic diagram of the rotor component of the gas generator of the preferred engine of the present application;

[0038] Figure 2 It is a schematic diagram of the process flow of the preferred embodiment of the present application;

[0039] Figure 3 It is a structural schematic diagram of the end tooth engagement test fixture of the preferred embodiment of the present application;

[0040] Figure 4 It is a structural schematic diagram of a compressor rotor stretching fixture of a preferred embodiment of the present application;

[0041] Figure 5 It is a schematic diagram of the assembly of the central pull rod and the centrifugal impeller of the preferred embodiment of the present application;

[0042] Figure 6 It is a structural schematic diagram of the end tooth runout inspection and ranging of the preferred embodiment of the present application;

[0043] Figure 7 It is a schematic diagram of the assembly dimension control of the rotor connecting shaft in the preferred embodiment of the present application;

[0044] Figure 8 It is a schematic diagram of the end face runout inspection of the rotor connecting shaft in the preferred embodiment of the present application;

[0045] Legend: 100, compressor rotor assembly; 200, turbine connecting shaft; 300, gas turbine first-stage rotor; 400, gas turbine second-stage rotor; 500, first bearing; 600, second bearing; 700, center tie rod; 800, centrifugal impeller; 900, rotor connecting shaft; 1000, end tooth meshing test fixture; 2000, compressor rotor stretching fixture; 3000, end tooth runout inspection tool; 1, bracket; 2, connecting expansion sleeve; 3, hydraulic pump; 4, locking bolt; 5, positioning plate; 6, positioning pin; 7, positioning pressure block; 8, locking piece; 9, force transmission block; 10, adjusting nut; 11, base; 12, clamping nut; 13, simulation plate; 14, limit block; 15, first tie rod; 16, second tie rod; 17, third tie rod. DETAILED DESCRIPTION

[0046] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0047] Figure 1 It is a schematic diagram of the rotor component of the gas generator of the preferred engine of the present application; Figure 2 It is a schematic diagram of the process flow of the preferred embodiment of the present application; Figure 3 It is a structural schematic diagram of the end tooth engagement test fixture of the preferred embodiment of the present application; Figure 4 It is a structural schematic diagram of a compressor rotor stretching fixture of a preferred embodiment of the present application;

[0048] Figure 5 It is a schematic diagram of the assembly of the central pull rod and the centrifugal impeller of the preferred embodiment of the present application; Figure 6 It is a structural schematic diagram of the end tooth runout inspection and ranging of the preferred embodiment of the present application; Figure 7 It is a schematic diagram of the assembly dimension control of the rotor connecting shaft in the preferred embodiment of the present application; Figure 8 It is a schematic diagram of the end face runout inspection of the rotor connecting shaft in the preferred embodiment of the present application.

[0049] A turboshaft engine gas generator rotor assembly device is used to assemble gas generator rotor components, the gas generator rotor components include a compressor rotor assembly 100, a turbine connecting shaft 200, a gas turbine first-stage rotor 300, a gas turbine second-stage rotor 400, a center pull rod 700, a centrifugal impeller 800 and a rotor connecting shaft 900. The turboshaft engine gas generator rotor assembly device includes an end gear meshing test fixture 1000 and a compressor rotor tensile fixture 2000:

[0050] The end tooth meshing test fixture 1000 includes a bracket 1, a hydraulic pump 3, a force transmission block 9, an adjusting nut 10, a first tie rod 15 and a base 11. The base 11 is used to support the compressor rotor assembly 100 and the first tie rod 15. The first tie rod 15 is penetrated on the compressor rotor assembly 100 and its bottom end is connected to the base 11 by threads. The bracket 1 is used to be erected on the compressor assembly 100. The hydraulic pump 3 is used to be installed on the top of the bracket 1. The adjusting nut 10 and the force transmission block 9 are sequentially sleeved on the top of the first tie rod 15 from top to bottom. The adjusting nut 10 is connected to the first tie rod 15 by threads. The adjusting nut 10 is used to push the force transmission block 9 to press the hydraulic pump 3 on the top of the bracket 1.

[0051] The compressor rotor stretching clamp 2000 includes a connecting expansion sleeve 2, a positioning plate 5, a stretching assembly and a second pull rod 16. The bottom end of the second pull rod 16 is inserted into the compressor rotor assembly 100. The connecting expansion sleeve 2 is movably sleeved on the bottom of the second pull rod 16. A protrusion is provided at the bottom of the second pull rod 16. The positioning plate 5 is sleeved on the second pull rod 16 and limits the top of the connecting expansion sleeve 2. The stretching assembly is sleeved on the second pull rod 16 and is located above the positioning sleeve 5. The stretching assembly is used to drive the second pull rod 16 to rise and fall, and then when the second pull rod 16 rises, the connecting expansion sleeve 2 is pushed to expand through the protrusion and engage with the internal threaded hole of the center pull rod 700.

[0052] The present application discloses a turboshaft engine gas generator rotor assembly device that performs an end tooth meshing test of a compressor rotor assembly 100 before formal assembly through an end tooth meshing test fixture 1000 to check the meshing of the end teeth of each blade disk. The force transmission block 9 is pushed by adjusting the nut 10 to press the hydraulic pump 3 against the top of the bracket 1, and the hydraulic pump 3 is repeatedly pressed to apply a preload force to the compressor rotor assembly 100. After repeated pressure application, the end tooth meshing test fixture 1000 is disassembled to check the meshing of the end teeth of each blade disk to ensure that there is no problem with the meshing of the end teeth of each blade disk. Then, the subsequent formal assembly can be performed to improve the smoothness of the formal assembly. The present application combines a compressor rotor through a compressor rotor stretching clamp 2000, wherein the second pull rod 16 is driven to rise and fall through the stretching assembly, and then when the second pull rod 16 rises, the protrusion pushes the connecting expansion sleeve 2 to expand and engage with the internal threaded hole of the center pull rod 700. At this time, the center pull rod 700 can be driven to adjust its position by rotating the positioning plate 5 and measure the distance L from the top surface of the positioning plate 5 to the installation end surface of the compressor rotor assembly 100, so that the distance L meets the preset assembly requirements to ensure that the installation dimensions are in place and improve the stability and accuracy of the assembly.

[0053] Preferably, please refer to Figure 6 As shown, the turboshaft engine gas generator rotor assembly device also includes an end tooth runout inspection gauge 3000, which includes a clamping nut 12, a simulation disk 13, a limit block 14 and a third tie rod 17. The third tie rod 17 is used to pass through the first bearing 500, the compressor rotor assembly 100 and the second bearing 600 in sequence. The simulation disk 13 is sleeved on the first end of the third tie rod 17 close to the first bearing 500. The simulation disk 13 is used to engage with the arc end teeth of the turbine connecting shaft 200. The clamping nut 12 is sleeved on the third tie rod 17. The clamping nut 12 is used to clamp the simulation disk 13. The limit block 14 is sleeved on the second end of the third tie rod 17 and is threadedly connected to the third tie rod 17. The limit block 14 is used to abut the second bearing 600 and limit the second end of the third tie rod 17.

[0054] It is understandable that in order to reflect the end tooth runout, that is, the concentricity with the rotor connecting shaft 900, an end tooth runout inspection jig 3000 is manufactured, and the end teeth on the simulated disk 13 are meshed and installed with the end teeth of the turbine connecting shaft 200. Then the runout value of the simulated disk 13 is measured with the first bearing 500 and the second bearing 600 as the fulcrum. Since the size of the simulated disk 13 of the end tooth runout inspection jig 3000 is the same as the inner hole size of the gas turbine first-stage rotor 300 and the gas turbine second-stage rotor 400, it is found through experimental comparison that when the runout of the simulated disk 13 is less than 0.025mm, the runout of the inner hole of the gas generator can meet the requirements or the angular position of the gas turbine first-stage rotor 300 and the gas turbine second-stage rotor 400 can be changed to make the inner hole runout qualified; if the inspection finds that the runout of the simulated disk 13 is greater than 0.025mm, the angular position of the turbine connecting shaft 200 needs to be adjusted according to the high and low points of the runout to control the assembly quality of the turbine connecting shaft 200.

[0055] It should be noted that the original assembly process of the turbine connecting shaft 200 is to install the heated turbine connecting shaft 200 into the rotor connecting shaft 900, and install a sleeve on the balanced material surface of the turbine connecting shaft 200, and use a hammer to knock the other end of the sleeve to assemble the turbine connecting shaft 200 in place. Through repeated assembly tests, we found that when the turbine connecting shaft 200 is installed by hammering, the high and low points of the gas inner hole runout vary greatly, the process reliability is poor, and the impact load generated by the knocking has the risk of deforming thin-walled parts such as the rotor connecting shaft 900 and the rotating seal.

[0056] Therefore, we designed and improved the process flow and assembly inspection tools, added the end tooth runout inspection fixture 3000 so that the assembly quality of the turbine connecting shaft 200 can be more intuitively reflected, ensured its assembly quality, improved work efficiency, and achieved better results.

[0057] Preferably, please refer to Figure 4 As shown, the stretching assembly includes a positioning pin 6, a positioning block 7 and a locking piece 8. The positioning block 7 is used to be movably mounted on the second pull rod 16 and is located above the positioning plate 5. The positioning pin 6 is vertically arranged on the top of the positioning plate 5. The positioning pin 6 is used to cooperate with the U-shaped groove preset at the bottom of the positioning block 7. The locking piece 8 is mounted on the second pull rod 16 and is connected to the second pull rod 16 by threads. The locking piece 8 is used to clamp the top of the limit positioning block 7. The locking piece 8 is also used to drive the second pull rod 16 to move up and down along the axial direction when rotating.

[0058] It can be understood that the positioning block 7 can be positioned and limited by the positioning pin 6. By loosening the locking piece 8, the second pull rod 16 is extended out of the connecting sleeve 2 by about 65mm. The positioning block 7 is lifted and rotated so that its end face is placed on the positioning pin 6. The connecting sleeve 2 is moved to make it close to the second pull rod 16 and then the fixture is installed into the center pull rod 700. Hold the compressor rotor stretching fixture 2000 and move the connecting sleeve 2 to make it buckle with the inner hole thread of the center pull rod 700. Rotate the positioning block 7 to make the positioning pin 6 snap into its U-shaped groove. Tighten the locking piece 8 to move the second pull rod 16 upward, and the connecting sleeve 2 expands evenly outward until it is fully engaged with the inner hole thread of the part; in addition, the positioning plate 5 can be equipped with a limit plate, etc. through the locking bolt 4. At this time, the center pull rod 700 is driven to adjust its position by rotating the positioning plate 5 and measuring the distance L from the top surface of the positioning plate 5 to the installation end surface of the compressor rotor assembly 100, so that the distance L meets the preset assembly requirements to ensure that the installation dimensions are in place and improve the stability and accuracy of the assembly.

[0059] According to another aspect of the present application, a method for assembling a turboshaft engine gas generator rotor is provided, which includes the turboshaft engine gas generator rotor assembly device described above. The method for assembling a turboshaft engine gas generator rotor includes the following steps:

[0060] S100, using the end tooth meshing test fixture 1000 to perform the end tooth meshing test of the compressor rotor assembly 100, connecting the oil pipe between the hydraulic equipment of the compressor rotor assembly 100 and the hydraulic pump 3, and repeatedly pressing with the hydraulic pump 3. After the pressing is completed, dismantling the tooth meshing test fixture 1000, checking the meshing of the end teeth of each level of blade disk, and if there is no problem, proceeding to the next formal assembly;

[0061] S200, using the compressor rotor stretching fixture 2000 to assemble the compressor rotor assembly 100, driving the second pull rod 16 to rise through the stretching assembly, and pushing the connecting expansion sleeve 2 to expand and engage with the internal threaded hole of the center pull rod 700 through the protrusion, rotating the positioning plate 5 to drive the center pull rod 700 to adjust the position and measuring the distance L from the top surface of the positioning plate 5 to the installation end surface of the compressor rotor assembly 100, so that the distance L meets the preset assembly requirements;

[0062] S300, install the bracket 1, hydraulic pump 3, force transmission block 9 and adjusting nut 10, connect the oil pipe between the hydraulic equipment and the hydraulic pump 3, repeatedly pressurize through the hydraulic pump 3, and use a dial indicator to check that the compression of the back of the centrifugal impeller 800 before and after tightening should be within the design requirements;

[0063] S400, disassemble the mounting bracket 1, hydraulic pump 3, force transmission block 9 and adjusting nut 10, check the clearance between the center tie rod locking nut assembly and the centrifugal impeller 800 with a feeler gauge, the 0.02mm thick feeler gauge should not pass, and install the first bearing 500;

[0064] S500, the heating rotor is connected to the shaft 900 and then installed on the centrifugal impeller 800;

[0065] S600, heating the inner ring of the second bearing 600 and installing it on the turbine connecting shaft 200, and installing the outer ring of the second bearing 600 after the inner ring of the second bearing 600 is cooled;

[0066] S700, install the gas turbine first-stage rotor 300 and the gas turbine second-stage rotor 400. The gas turbine first-stage rotor 300 and the turbine connecting shaft 200 are installed with the arc end tooth runout high point staggered by 180 degrees. The gas turbine second-stage rotor 400 and the gas turbine first-stage rotor 300 are also installed with the arc end tooth runout high point staggered by 180 degrees.

[0067] The turboshaft engine gas generator rotor assembly method of the present application also has the above-mentioned beneficial effects, and also includes adjusting the assembly dimension control requirements to improve the process accuracy and increase the process control to address the problem that it is difficult to ensure the coaxiality between the rotor connecting shaft 900 and the centrifugal impeller 800 and the rotor fulcrum after assembly. In view of the problem that the assembly quality of the turbine connecting shaft 200 is difficult to control, the inspection of parts before assembly is strengthened, and the end tooth meshing test before assembly is implemented. Through the analysis of the compressor rotor structure, repeated pre-tightening and unloading pressure is implemented to make the turbine connecting shaft 200 and the rotor connecting shaft 900 fully fit together; at the same time, the end tooth runout inspection tooling is added so that the assembly quality of the turbine connecting shaft 200 can be more intuitively reflected, thereby ensuring its assembly quality. This application analyzes the process difficulties in the assembly process of the cantilever gas generator rotor, formulates reasonable and feasible solutions, and proposes "segmented control method" and "constant temperature press assembly method" to improve assembly stability, optimize the process flow, improve tooling equipment, ensure engine assembly reliability, and improve engine assembly efficiency. The assembly cycle is shortened from 4 days / unit to 1 day / unit, achieving good results.

[0068] Preferably, in step S100, after connecting the oil pipe between the hydraulic equipment of the compressor rotor assembly 100 and the hydraulic pump 3, open the hydraulic valve on the hydraulic equipment, tighten the adjusting nut 10 until the hydraulic pump 3 is reset, loosen 1 / 4 turn of the adjusting nut 10, close the hydraulic valve and pressurize through the hydraulic pump 3, apply a preload force of 1KN to 2KN on the compressor rotor assembly 100, open the hydraulic valve to relieve the pressure of the hydraulic pump 3, loosen the adjusting nut 10, repeat 3 to 5 times, and then disassemble the end tooth engagement test fixture 1000 to check the engagement of the end teeth of each level of blade disk.

[0069] It can be understood that by repeatedly pressing with the hydraulic pump 3 to achieve repeated pre-tightening-unloading operations, the meshing conditions of the end teeth of each level of blade disk can be accurately checked to ensure that problems that have not been considered before formal assembly are avoided.

[0070] It should be noted that in order to ensure defect-free assembly of parts, workers are required to carefully check the surface quality of related parts before assembly. In particular, they should pay attention to checking whether the mating end faces of parts such as the rotor connecting shaft 900 have accumulated chips due to repeated assembly, whether there are burrs or foreign objects on the threads, etc., to avoid the gas generator from vibrating unqualifiedly due to the nut being bitten or the self-locking nut not being tightened properly due to foreign objects or burrs.

[0071] Preferably, in step S300, after connecting the oil pipe between the hydraulic equipment and the hydraulic pump 3, open the hydraulic valve on the hydraulic equipment, tighten the adjusting nut 10 until the hydraulic pump 3 is reset, loosen the 1 / 4 turn of the adjusting nut 10, close the hydraulic valve, pressurize through the hydraulic pump 3, apply a preload force of 3KN to 4KN on the compressor rotor assembly 100, open the hydraulic valve to relieve the pressure of the hydraulic pump 3, loosen the adjusting nut 10, repeat three times, and then use a dial indicator to check the compression of the back of the centrifugal impeller 800 before and after tightening.

[0072] It is understandable that the hydraulic pump 3 is used again to repeatedly pressurize to achieve pressurization-unloading assembly and inspection, which can ensure that the compression of the back of the centrifugal impeller 800 before and after tensioning should be within the design requirements.

[0073] Preferably, in step S500, the wall thickness dimensions A and B are measured at the 12, 3, 6, and 9 o'clock positions on the rear flange of the centrifugal impeller 800 and the front flange of the rotor connecting shaft 900, respectively. After the rotor connecting shaft 900 is assembled, the dimension C of the connection is measured respectively, and the four selected positions are required to simultaneously satisfy A+B≤C±0.02mm.

[0074] It should be noted that in actual operation, we found that the thickness dimensions A and B of the flange edge of the centrifugal impeller 800 would vary within the range of 0.01 to 0.02 mm due to the lack of parallelism requirements. Therefore, we adjusted the measurement of the wall thickness dimensions A and B at the 12, 3, 6, and 9 o'clock positions on the rear flange of the centrifugal impeller 800 and the front flange of the rotor connecting shaft 900. After completing the rotor connecting shaft assembly, we measured the dimension C at the corresponding positions and required that the selected 4 positions simultaneously satisfy A+B≤C±0.02 mm.

[0075] Preferably, in step S500, the reference runout on the rotor connecting shaft 900 is checked, and the runout should be no greater than 0.015 mm. If it is unqualified, the rotor connecting shaft 900 is disassembled and reassembled.

[0076] At the same time, in step S500, ensure that the inner hole anti-rotation groove of the rotor connecting shaft 900 is aligned with the anti-rotation boss of the center pull rod locking nut assembly, and then install the rotor connecting shaft on the centrifugal impeller 800. After the rotor connecting shaft cools to room temperature, tighten the rotor connecting shaft 900 again according to torque.

[0077] It should be noted that, through a large number of engine troubleshooting tests, the inner ring mounting surface of the first bearing 500 on the front journal of the first-stage disk was taken as the front fulcrum, and the rotating seal mounting surface on the rotor connecting shaft 900 was taken as the rear fulcrum, and the runout of the reference K on the rotor connecting shaft 900 was measured. If the runout value of the reference K is less than 0.015mm, the requirement that the inner hole runout of the second-stage disk of the gas turbine is less than 0.03mm can be met.

[0078] In order to avoid repeated rotor assembly work caused by unqualified gas inner hole runout, we have added process internal control requirements for K reference runout during the assembly process, requiring it to be no more than 0.015mm. If it is unqualified, the assembly quality is ensured by adjusting the 90° angular position of the rotor connecting shaft or replacing parts.

[0079] Preferably, in step S600, the end tooth runout inspection jig 3000 is clamped onto the compressor rotor assembly 100, and the runout of the simulated disk 13 is measured. The runout should be no greater than 0.025 mm. If it fails, the angular position of the simulated disk 13 and the turbine connecting shaft 200 is adjusted clockwise, and the measurement is repeated until the runout is no greater than 0.025 mm.

[0080] In addition, in step S600, the turbine connecting shaft 200 is installed 180° away from the preset "H" mark on the rotor connecting shaft 900, and the turbine connecting shaft 200 is pressed down by hand to expose at least one thread of the rotor connecting shaft 900.

[0081] Preferably, in step S700, a lever micrometer is used to check the inner hole runout of the gas turbine secondary rotor 400, which should be no more than 0.03 mm. If it fails, the gas turbine primary rotor 300 and the gas turbine secondary rotor 400 are separated, and the angular positions of the gas turbine primary rotor 300, the gas turbine secondary rotor 400 and the turbine connecting shaft 200 are adjusted, and the measurement is repeated until the inner hole runout of the gas turbine secondary rotor 400 is no more than 0.03 mm.

[0082] It should be noted that during engine assembly, the cross-sectional runout at two locations of the inner hole of the gas turbine secondary disk measured with a lever micrometer should be no greater than 0.03mm, and no greater than 0.01mm compared to the component runout. The position of the high point and the recorded high point of the component should not be greater than ±72° (i.e., it is allowed to change to an adjacent long bolt hole) to ensure assembly consistency.

[0083] The present application is particularly about an assembly method and adjustment method of a cantilever fulcrum joint rotor of a multi-stage compressor, which ensures the coaxiality and assembly consistency of the gas generator rotor by designing tooling, strengthening process control, optimizing process flow and methods, and avoiding repeated disassembly and assembly, wear and deformation of parts, etc.

[0084] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0085] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection of this application.

Claims

1. A turboshaft engine gas generator rotor assembly device, used for assembling a gas generator rotor component, the gas generator rotor component comprising a compressor rotor assembly (100), a turbine connecting shaft (200), a gas turbine first-stage rotor (300), a gas turbine second-stage rotor (400), a center tie rod (700), a centrifugal impeller (800) and a rotor connecting shaft (900), characterized in that: The turboshaft engine gas generator rotor assembly device comprises an end gear meshing test fixture (1000) and a compressor rotor tensile fixture (2000): The end tooth meshing test fixture (1000) comprises a bracket (1), a hydraulic pump (3), a force transmission block (9), an adjusting nut (10), a first tie rod (15) and a base (11), wherein the base (11) is used to support the compressor rotor assembly (100) and the first tie rod (15), the first tie rod (15) is inserted into the compressor rotor assembly (100) and its bottom end is connected to the base (11) by a thread, the bracket (1) is used to be mounted on the compressor assembly (100), the hydraulic pump (3) is used to be installed on the top of the bracket (1), the adjusting nut (10) and the force transmission block (9) are sequentially sleeved on the top of the first tie rod (15) from top to bottom, the adjusting nut (10) is connected to the first tie rod (15) by a thread, and the adjusting nut (10) is used to push the force transmission block (9) to press the hydraulic pump (3) against the top of the bracket (1); The compressor rotor stretching clamp (2000) comprises a connecting expansion sleeve (2), a positioning plate (5), a stretching assembly and a second pull rod (16), wherein the bottom end of the second pull rod (16) is inserted into the compressor rotor assembly (100), the connecting expansion sleeve (2) is movably mounted on the bottom of the second pull rod (16), a protrusion is provided at the bottom end of the second pull rod (16), the positioning plate (5) is mounted on the second pull rod (16) and limits the top of the connecting expansion sleeve (2), the stretching assembly is mounted on the second pull rod (16) and is located above the positioning sleeve (5), and the stretching assembly is used to drive the second pull rod (16) to rise and fall, and then when the second pull rod (16) rises, the connecting expansion sleeve (2) is pushed to expand through the protrusion and engage with the internal threaded hole of the center pull rod (700).

2. A turboshaft engine gas generator rotor assembly device according to claim 1, characterized in that: The turboshaft engine gas generator rotor assembly device also includes an end tooth runout inspection tool (3000), which includes a clamping nut (12), a simulation disk (13), a limit block (14) and a third pull rod (17). The third pull rod (17) is used to sequentially pass through the first bearing (500), the compressor rotor assembly (100) and the second bearing (600). The simulation disk (13) is sleeved on the third pull rod (17) near the first bearing ( 500), the simulation disk (13) is used to mesh with the arc end teeth of the turbine connecting shaft (800), the clamping nut (12) is sleeved on the third tie rod (17), the clamping nut (12) is used to clamp the simulation disk (13), the limit block (14) is sleeved on the second end of the third tie rod (17) and is connected to the third tie rod (17) by threads, and the limit block (14) is used to abut the second bearing (600) and limit the second end of the third tie rod (17).

3. A turboshaft engine gas generator rotor assembly device according to claim 1, characterized in that: The stretching assembly comprises a positioning pin (6), a positioning pressure block (7) and a locking piece (8); the positioning pressure block (7) is used to be movably mounted on the second pull rod (16) and is located above the positioning plate (5); the positioning pin (6) is vertically arranged on the top of the positioning plate (5); the positioning pin (6) is used to cooperate with a U-shaped groove preset at the bottom of the positioning pressure block (7); the locking piece (8) is mounted on the second pull rod (16) and is connected to the second pull rod (16) by a thread; the locking piece (8) is used to press the top of the limit positioning pressure block (7); the locking piece (8) is also used to drive the second pull rod (16) to move up and down along the axial direction when rotating.

4. A method for assembling a turboshaft engine gas generator rotor, characterized in that: Using the turboshaft engine gas generator rotor assembly device according to any one of claims 1 to 3, the turboshaft engine gas generator rotor assembly method comprises the following steps: S100, using an end tooth meshing test fixture (1000) to conduct an end tooth meshing test of a compressor rotor assembly (100), connecting the oil pipe between the hydraulic equipment of the compressor rotor assembly (100) and the hydraulic pump (3), and repeatedly pressing with the hydraulic pump (3). After the pressing is completed, disassembling the tooth meshing test fixture (1000), checking the meshing conditions of the end teeth of each level of blade disk, and if there is no problem, proceeding to the next formal assembly; S200, using a compressor rotor stretching fixture (2000) to assemble a compressor rotor assembly (100), driving the second pull rod (16) to rise through the stretching assembly, and pushing the connecting expansion sleeve (2) to expand and engage with the internal threaded hole of the center pull rod (700) through the protrusion, rotating the positioning plate (5) to drive the center pull rod (700) to adjust the position and measuring the distance L from the top surface of the positioning plate (5) to the installation end surface of the compressor rotor assembly (100), so that the distance L meets the preset assembly requirements; S300, install the bracket (1), hydraulic pump (3), force transmission block (9) and adjusting nut (10), connect the oil pipe between the hydraulic equipment and the hydraulic pump (3), repeatedly pressurize with the hydraulic pump (3), and use a dial indicator to check whether the compression of the back of the centrifugal impeller (800) before and after tightening is within the design requirement range; S400, disassemble the mounting bracket (1), hydraulic pump (3), force transmission block (9) and adjusting nut (10), and use a feeler gauge to check the gap between the center tie rod locking nut assembly and the centrifugal impeller (800). A feeler gauge with a thickness of 0.02 mm should not be able to pass through, and install the first bearing (500); S500, the heating rotor is connected to the shaft (900) and then installed on the centrifugal impeller (800); S600, heating the inner ring of the second bearing (600) and installing it on the turbine connecting shaft (200), and installing the outer ring of the second bearing (600) after the inner ring of the second bearing (600) is cooled; S700, installing a gas turbine first-stage rotor (300) and a gas turbine second-stage rotor (400), wherein the arc end tooth runout high points of the gas turbine first-stage rotor (300) and the turbine connecting shaft (200) are installed at a 180-degree offset, and the arc end tooth runout high points of the gas turbine second-stage rotor (400) and the gas turbine first-stage rotor (300) are also installed at a 180-degree offset.

5. A turboshaft engine gas generator rotor assembly method according to claim 4, characterized in that: In step S100, after connecting the oil pipe between the hydraulic equipment of the compressor rotor assembly (100) and the hydraulic pump (3), the hydraulic valve on the hydraulic equipment is opened, the adjusting nut (10) is tightened until the hydraulic pump (3) is reset, 1 / 4 turn of the adjusting nut (10) is loosened, the hydraulic valve is closed and pressurized by the hydraulic pump (3), a preload force of 1KN to 2KN is applied to the compressor rotor assembly (100), the hydraulic valve is opened to release the pressure of the hydraulic pump (3), the adjusting nut (10) is loosened, and after repeating 3 to 5 times, the end tooth engagement test fixture (1000) is disassembled to check the engagement of the end teeth of each level of blade disk.

6. A turboshaft engine gas generator rotor assembly method according to claim 4, characterized in that: In step S300, after connecting the oil pipe between the hydraulic device and the hydraulic pump (3), the hydraulic valve on the hydraulic device is opened, the adjusting nut (10) is tightened until the hydraulic pump (3) is reset, 1 / 4 turn of the adjusting nut (10) is loosened, the hydraulic valve is closed and pressurized by the hydraulic pump (3), a preload force of 3KN to 4KN is applied to the compressor rotor assembly (100), the hydraulic valve is opened to relieve the pressure of the hydraulic pump (3), the adjusting nut (10) is loosened, and this is repeated three times. Then, a dial indicator is used to check the compression of the back of the centrifugal impeller (800) before and after tightening.

7. A turboshaft engine gas generator rotor assembly method according to claim 4, characterized in that: In step S500, the wall thickness dimensions A and B are measured at the 12, 3, 6, and 9 o'clock positions on the rear flange of the centrifugal impeller (800) and the front flange of the rotor connecting shaft (900), respectively. After the rotor connecting shaft (900) is assembled, the dimension C of the connection is measured respectively, and the four selected positions are required to simultaneously satisfy A+B≤C±0.02mm.

8. A turboshaft engine gas generator rotor assembly method according to claim 4, characterized in that: In step S500, the reference runout on the rotor connecting shaft (900) is checked. The runout should be no greater than 0.015 mm. If it is unqualified, the rotor connecting shaft (900) is disassembled and reassembled.

9. A turboshaft engine gas generator rotor assembly method according to claim 4, characterized in that: In step S600, the end tooth runout inspection jig (3000) is clamped onto the compressor rotor assembly (100) to measure the runout of the simulated disk (13). The runout should be no greater than 0.025 mm. If it fails, the angular position of the simulated disk (13) and the turbine connecting shaft (200) is adjusted clockwise and the measurement is repeated until the runout is no greater than 0.025 mm.

10. A turboshaft engine gas generator rotor assembly method according to claim 4, characterized in that: In step S700, a lever micrometer is used to check the inner hole runout of the gas turbine secondary rotor (400), which should be no more than 0.03 mm. If it fails, the gas turbine primary rotor (300) and the gas turbine secondary rotor (400) are separated, and the angular positions of the gas turbine primary rotor (300), the gas turbine secondary rotor (400) and the turbine connecting shaft (200) are adjusted. The measurement is repeated until the inner hole runout of the gas turbine secondary rotor (400) is no more than 0.03 mm.

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