A kind of turboshaft engine gas generator rotor assembly device and assembly method

Abstract

The application discloses a kind of turboshaft engine gas generator rotor assembly device and assembly method, belong to aero-engine assembly technical field, it includes end tooth engagement test fixture, adjusting nut and force block are sequentially set from top to bottom in the top of first pull rod, adjusting nut is connected with first pull rod by thread, adjusting nut is used to push force block and compress hydraulic pump in the top of support;Compressor rotor stretching fixture, stretching assembly is set on the second pull rod and is located above the positioning sleeve, stretching assembly is used to drive the second pull rod to go up and down, and then when the second pull rod rises, it is pushed to connect the expansion sleeve and is engaged with the internal thread hole of center pull rod by protruding portion.The end tooth engagement test of compressor rotor assembly is carried out by end tooth engagement test fixture before formal assembly, and the engagement of the end tooth of each stage blade disc is checked;Compressor rotor is combined by compressor rotor stretching fixture.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine assembly, in particular, to a turboshaft engine gas generator rotor assembly device. In addition, the present application also relates to an assembly method comprising the above turboshaft engine gas generator rotor assembly device. BACKGROUND

[0002] The information provided in this section is for the purpose of generally presenting the context of the application. The work of the presently named inventors, to the extent the descriptions are described in this section, as well as aspects of the descriptions that can not otherwise qualify as prior art at the time of filing, are neither expressly nor impliedly admitted as prior art against the present application.

[0003] A certain type of engine gas generator rotor component is one of the main vibration sources of the engine, which is composed 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, and the like. Please refer to the attached drawings for a detailed description. Figure 1 .

[0004] The compressor rotor assembly is composed of four integral blade discs, one centrifugal impeller, one hub, one spoiler, and one center pull rod 700. The integral blade discs are connected through circular arc end teeth, and the first-stage blade disc is an integral structure with a front shaft neck, on which a first bearing inner ring, a labyrinth seal, and a bevel gear (for accessory power extraction) are mounted, which are pressed on the shaft neck by a self-locking nut. The first bearing 500 is a ball bearing for bearing the axial load of the rotor. The hub is fitted between the first and second-stage blade discs through a stop port to form a flow passage. The spoiler is located at the rear end of the fourth-stage integral blade, which introduces sealed pressurized air into the interior of the rotor. The center pull rod 700 is used to assemble the integral blade discs together, with the front end screwed on the first-stage blade disc by threads, and the rear end screwed on the centrifugal impeller by a nut.

[0005] The rotor connecting shaft mounting edge is connected to the centrifugal impeller by bolts, and a rotary seal (for compressor outlet air sealing) is also mounted on the shaft. The rotor connecting shaft is connected to the turbine connecting shaft 200 through splines. The turbine connecting shaft 200 is provided with a second bearing 600, which is a roller bearing that only bears radial load, supporting the rear end of the compressor rotor and the gas turbine. The gas turbine rotor assembly is composed of a first-stage turbine rotor assembly and a second-stage turbine rotor assembly, and the rotor is fixed by five long bolts, circular arc end teeth positioning, and connected to the compressor through turbine connecting shaft 200 splines and an axial locking nut.

[0006] The assembly quality of the gas generator rotor directly affects the vibration of the engine, and the structure is complex, and at the same time, due to the high precision of part machining and assembly, higher requirements are put forward for the assembly process.

[0007] At present, the rotor assembly process of the gas generator is affected by the low qualified rate of the gas turbine inner hole runout (the design requires that the inner hole runout is less than 0.03 mm), which causes repeated disassembly and inspection of the rotor connecting shaft, rotating seal, turbine connecting shaft, second bearing 600, gas turbine first rotor 300, gas turbine second rotor 400 and other parts, and often delays the production schedule for one or two weeks, reduces the engine assembly efficiency, increases the production cost, and also causes part wear and deformation due to repeated assembly, which reduces the service life of the parts and also brings risks to the engine test safety.

[0008] Since the length of the gas generator rotor exceeds 700 mm, the cantilever structure length is about 200 mm, there are multi-stage end tooth connections, the machining difficulty is great, the assembly difficulty is great, the assembly precision is high, the consistency is poor after repeated assembly, and the parts are prone to deformation and wear after repeated assembly.

[0009] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present application, and therefore can include information that does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0010] The inventor found through research that the main links and reasons affecting the assembly cycle in the gas generator rotor assembly process were analyzed, and it was found that the control difficulty of the gas turbine second disc inner hole runout was great, the assembly repeatability was poor, the adjustment cycle was long, the coaxiality of the rotor connecting shaft and the centrifugal impeller after combination was difficult to guarantee, the turbine connecting shaft assembly quality was difficult to control, there was a lack of process control, a lack of inspection means, tooling and low assembly efficiency, and once the coaxiality was poor, the gas generator rotor needed 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 end tooth engagement test of the compressor rotor assembly before formal assembly through an end tooth engagement test fixture, and check the engagement of the end teeth of each stage of blade disc.

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

[0013] According to an aspect of the present application, a turbine shaft engine gas generator rotor assembly device is provided for assembling a gas generator rotor component, the gas generator rotor component comprising 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 turbine shaft engine gas generator rotor assembly device comprising an end tooth engagement test fixture compressor rotor stretching fixture:

[0014] The end tooth engagement test fixture comprises a support, a hydraulic pump, a force block, an adjusting nut, a first pull rod and a base, the base is used for supporting the compressor rotor assembly and the first pull rod, the first pull rod is arranged on the compressor rotor assembly and the bottom end thereof is connected with the base through screw threads, the support is used for being arranged on the compressor assembly, the hydraulic pump is arranged on the top of the support, the adjusting nut and the force block are sequentially arranged on the top of the first pull rod from top to bottom, the adjusting nut is connected with the first pull rod through screw threads, and the adjusting nut is used for pushing the force block to press the hydraulic pump on the top of the support;

[0015] The compressor rotor stretching fixture comprises a connecting expansion sleeve, a positioning disc, a stretching assembly and a second pull rod, the bottom end of the second pull rod is arranged in the compressor rotor assembly, the connecting expansion sleeve is movably arranged on the bottom of the second pull rod, the bottom end of the second pull rod is provided with a protruding part, the positioning disc is arranged on the second pull rod and limits the top of the connecting expansion sleeve, and the stretching assembly is arranged on the second pull rod and above the positioning sleeve, the stretching assembly is used for driving the second pull rod to ascend and descend, and the connecting expansion sleeve is expanded and engaged with the internal threaded hole of the center pull rod through the protruding part when the second pull rod ascends.

[0016] In some embodiments of the present application, the turbine shaft engine gas generator rotor assembly device further comprises an end tooth runout inspection gauge, the end tooth runout inspection gauge comprising a pressing nut, an analog disc, a limiting block and a third pull rod, the third pull rod is used for sequentially penetrating through a first bearing, the compressor rotor assembly and a second bearing, the analog disc is arranged on the first end of the third pull rod close to the first bearing, the analog disc is used for engaging with the circular arc end tooth of the turbine connecting shaft, the pressing nut is arranged on the third pull rod, the pressing nut is used for pressing the analog disc, and the limiting block is arranged on the second end of the third pull rod and connected with the third pull rod through screw threads, the limiting block is used for abutting against the second bearing and limiting the second end of the third pull rod.

[0017] In some embodiments of the present application, the stretching assembly comprises a positioning pin, a positioning pressure block and a locking piece, the positioning pressure block is movably arranged on the second pull rod and above the positioning disc, the positioning pin is vertically arranged on the top of the positioning disc, the positioning pin is used for cooperating with the U-shaped groove pre-set on the bottom of the positioning pressure block, the locking piece is arranged on the second pull rod and connected with the second pull rod through screw threads, the locking piece is used for pressing the top of the limiting positioning pressure block, and the locking piece is used for driving the second pull rod to ascend and descend along the axial direction when rotating.

[0018] According to another aspect of the present application, a turboshaft engine gas generator rotor assembly method is also provided, which comprises the turboshaft engine gas generator rotor assembly device described above, and comprises the following steps:

[0019] S100, end tooth engagement test of the compressor rotor assembly is carried out by using the end tooth engagement test fixture, the oil pipe between the hydraulic equipment and the hydraulic pump connected to the compressor rotor assembly is connected, repeated pressure is carried out by the hydraulic pump, after the pressure is finished, the tooth engagement test fixture is disassembled, the engagement of the end teeth of the blade discs of each stage is checked, if there is no problem, the formal assembly is carried out next;

[0020] S200, the compressor rotor assembly is assembled by using the compressor rotor stretching fixture, the second pull rod is lifted by the stretching assembly, and the connecting expansion sleeve is expanded and engaged with the internal threaded hole of the center pull rod by the protruding part, the center pull rod is adjusted in position by rotating the positioning disc and the distance L from the top surface of the positioning disc to the mounting end surface of the compressor rotor assembly is measured, so that the distance L meets the preset assembly requirement;

[0021] S300, the support, the hydraulic pump, the force transmission block and the adjusting nut are installed, the oil pipe between the hydraulic equipment and the hydraulic pump is connected, repeated pressure is carried out by the hydraulic pump, and the compression amount of the rear back of the centrifugal impeller before and after tensioning should be within the design requirement range by checking with the dial gauge;

[0022] S400, the support, the hydraulic pump, the force transmission block and the adjusting nut are disassembled, the gap between the center pull rod locking nut assembly and the centrifugal impeller is checked with the feeler gauge, the 0.02mm thickness feeler gauge should not be able to pass, and the first bearing is installed;

[0023] S500, the rotor connecting shaft is installed on the centrifugal impeller after being warmed up;

[0024] S600, the inner ring of the second bearing is installed on the turbine connecting shaft after being warmed up, and the outer ring of the second bearing is installed after the inner ring of the second bearing is cooled;

[0025] S700, the gas turbine first stage rotor and the gas turbine second stage rotor are installed, the gas turbine first stage rotor is installed with the circular arc end tooth run-out high point of the turbine connecting shaft staggered by 180 degrees, and the gas turbine second stage rotor is installed with the circular arc end tooth run-out high point of the gas turbine first stage rotor also staggered by 180 degrees.

[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 resets, 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 the blade disks at all levels.

[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 tightening.

[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 to meet the requirements, 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 application is a kind of end tooth engagement test fixture for the assembly of the rotor of the gas generator of a turboshaft engine, which is used to check the engagement of the end teeth of the blade discs of the compressor rotor assembly before formal assembly. The hydraulic pump is pressed against the top of the support by adjusting the nuts to push the force block, and the pre-tightening force is applied to the compressor rotor assembly by repeated pressing by the hydraulic pump. After repeated pressing, the end tooth engagement test fixture is disassembled to check the engagement of the end teeth of the blade discs, so as to ensure that the end teeth of the blade discs are engaged without problems, and then the formal assembly can be carried out to improve the smoothness of the formal assembly. The compressor rotor is assembled by the compressor rotor stretching fixture. The second pull rod is lifted by the stretching assembly, and the connecting expansion sleeve is expanded and engaged with the internal threaded hole of the center pull rod by the protrusion when the second pull rod rises. At this time, the position of the center pull rod is adjusted by rotating the positioning disc, and the distance L between the top surface of the positioning disc and the mounting end surface of the compressor rotor assembly is measured, so that the distance L meets the preset assembly requirements, so as to ensure that the installation size is in place and improve the stability and accuracy of the assembly.

[0034] The application also has the above-mentioned beneficial effects. The assembly size control requirements are adjusted to improve the process accuracy. The process control is increased to improve the assembly quality. The inspection of the parts before assembly is strengthened to realize the end tooth engagement test before assembly. The pre-tightening-unloading repeated pressing is realized by analyzing the structure of the compressor rotor, so that the turbine connecting shaft is completely matched with the rotor connecting shaft. The end tooth runout inspection tool is added to make the turbine connecting shaft assembly quality more intuitive, so as to ensure the assembly quality, improve the work efficiency, ensure the assembly reliability of the engine, improve the assembly efficiency of the engine, and shorten the assembly cycle from 4 days per engine to 1 day per engine, which achieves good results.

[0035] Of course, implementing any product of the application does not necessarily require all the advantages described above. In addition to the purposes, features and advantages described above, the application has other purposes, features and advantages. The application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0036] The drawings that form a part of this application are used to provide a further understanding of the application, and the illustrative embodiments of the application and their descriptions serve to explain the application, and do not constitute an improper limitation on the application. In the drawings:

[0037] Figure 1 is a schematic view of the rotor components of the gas generator of the application;

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

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

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

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

[0042] Figure 6 is a schematic diagram of the end tooth run-out checking and measuring of the preferred embodiment of the present application;

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

[0044] Figure 8 is a schematic diagram of the end face run-out checking of the rotor connecting shaft of 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 pull rod; 800, centrifugal impeller; 900, rotor connecting shaft; 1000, end tooth engagement test fixture; 2000, compressor rotor stretching fixture; 3000, end tooth run-out checking and measuring tool; 1, bracket; 2, connecting expansion sleeve; 3, hydraulic pump; 4, locking bolt; 5, positioning disc; 6, positioning pin; 7, positioning pressing block; 8, locking member; 9, force transmission block; 10, adjusting nut; 11, base; 12, pressing nut; 13, simulation disc; 14, limiting block; 15, first pull rod; 16, second pull rod; 17, third pull rod. DETAILED DESCRIPTION

[0046] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following description.

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

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

[0049] A turboshaft engine gas generator rotor assembly device 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 pull rod 700, a centrifugal impeller 800 and a rotor connecting shaft 900, the turboshaft engine gas generator rotor assembly device comprising an end tooth meshing test clamp 1000 and a compressor rotor stretching clamp 2000:

[0050] The end tooth meshing test clamp 1000 comprises a bracket 1, a hydraulic pump 3, a force block 9, an adjusting nut 10, a first pull rod 15 and a base 11, the base 11 is used to support the compressor rotor assembly 100 and the first pull rod 15, the first pull rod 15 is provided on the compressor rotor assembly 100 and the bottom end thereof is connected with the base 11 through screw thread, 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 block 9 are sequentially sleeved on the top of the first pull rod 15 from top to bottom, the adjusting nut 10 is connected with the first pull rod 15 through screw thread, and the adjusting nut 10 is used to push the force block 9 to press the hydraulic pump 3 tightly on the top of the bracket 1;

[0051] The compressor rotor stretching clamp 2000 comprises a connecting expansion sleeve 2, a positioning disc 5, a stretching assembly and a second pull rod 16, the bottom end of the second pull rod 16 is provided in the compressor rotor assembly 100, the connecting expansion sleeve 2 is movably sleeved on the bottom of the second pull rod 16, the bottom end of the second pull rod 16 is provided with a protruding part, the positioning disc 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 above the positioning sleeve 5, the stretching assembly is used to drive the second pull rod 16 to ascend and descend, and then the connecting expansion sleeve 2 is expanded and engaged with the internal threaded hole of the center pull rod 700 through the protruding part when the second pull rod 16 ascends.

[0052] The end-tooth engagement test clamp 1000 is used to check the engagement of the end teeth of the blade discs of each stage before the formal assembly of the compressor rotor assembly 100, wherein the hydraulic pump 3 is pressed against the top of the support 1 by adjusting the nut 10 to push the force block 9, the pre-tightening force is applied to the compressor rotor assembly 100 by repeatedly pressing through the hydraulic pump 3, and after repeated pressing, the end-tooth engagement test clamp 1000 is disassembled to check the engagement of the end teeth of the blade discs of each stage, so as to ensure that the end teeth of the blade discs of each stage are engaged without problems, and then the formal assembly can be carried out to improve the smoothness of the formal assembly. The compressor rotor stretching clamp 2000 is used to assemble the compressor rotor, wherein the second pull rod 16 is lifted by the stretching assembly, and then when the second pull rod 16 rises, the connecting expansion sleeve 2 is pushed to expand and engage with the internal threaded hole of the center pull rod 700 by the protrusion, at this time, the center pull rod 700 is adjusted in position by rotating the positioning disc 5, and the distance L from the top surface of the positioning disc 5 to the installation end surface of the compressor rotor assembly 100 is measured, so that the distance L meets the preset assembly requirement, so as to ensure that the installation size is in place and improve the stability and accuracy of the assembly.

[0053] Preferably, referring to Figure 6 The turbine connecting shaft 200 also includes an end-tooth runout checking gauge 3000, the end-tooth runout checking gauge 3000 includes a pressing nut 12, a simulation disc 13, a limiting block 14 and a third pull rod 17, the third pull 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 disc 13 is sleeved on the first end of the third pull rod 17 close to the first bearing 500, the simulation disc 13 is used to engage with the circular arc end teeth of the turbine connecting shaft 200, the pressing nut 12 is sleeved on the third pull rod 17, the pressing nut 12 is used to press the simulation disc 13, and the limiting block 14 is sleeved on the second end of the third pull rod 17 and is connected with the third pull rod 17 through threads, the limiting block 14 is used to abut against the second bearing 600 and limit the second end of the third pull rod 17.

[0054] It can be understood that, in order to react to the end tooth runout, i.e. the concentricity with the rotor connecting shaft 900, the end tooth runout checking gauge 3000 is manufactured, and the end teeth on the simulation disc 13 are engaged with the turbine connecting shaft 200 end teeth. Then, the runout value of the simulation disc 13 is measured with the first bearing 500 and the second bearing 600 as the fulcrum. Since the end tooth runout checking gauge 3000 has the same size as the inner hole of the gas turbine first rotor 300 and the gas turbine second rotor 400, it is found through test comparison that when the simulation disc 13 runout is less than 0.025 mm, the gas generator inner hole runout can meet the requirements or can pass by replacing the angular position of the gas turbine first rotor 300 and the gas turbine second rotor 400 to make the inner hole runout qualified; if it is found through inspection that the simulation disc 13 runout is greater than 0.025 mm, the angular position of the turbine connecting shaft 200 needs to be adjusted according to the runout high point to control the assembly quality of the turbine connecting shaft 200.

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

[0056] Therefore, we have designed and improved the process flow and assembly detection tool, and added the end tooth runout checking gauge 3000 to make the turbine connecting shaft 200 assembly quality more intuitive, ensure the assembly quality, improve the work efficiency, and achieve good results.

[0057] Preferably, as shown in Figure 4 The stretching assembly includes a positioning pin 6, a positioning block 7, and a locking piece 8. The positioning block 7 is movably sleeved on the second pull rod 16 and located above the positioning disc 5. The positioning pin 6 is vertically arranged on the top of the positioning disc 5 and used to cooperate with a U-shaped groove pre-set on the bottom of the positioning block 7. The locking piece 8 is sleeved on the second pull rod 16 and connected with the second pull rod 16 through threads. The locking piece 8 is used to press the top of the positioning block 7 and 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 pin 6 can be positioned and limited by the positioning pin 6. By loosening the locking part 8, the second pull rod 16 is extended by about 65mm, the positioning block 7 is lifted and rotated to be placed on the positioning pin 6, the connecting expansion sleeve 2 is moved to be close to the second pull rod 16, and the clamp is installed in the center pull rod 700. Hold the compressor rotor stretching clamp 2000 and move the connecting expansion sleeve 2 to be screwed with the inner hole thread of the center pull rod 700, rotate the positioning block 7 to make the positioning pin 6 clamped in the U-shaped groove. Tighten the locking part 8 to make the second pull rod 16 move upward, the connecting expansion sleeve 2 uniformly expands outward, and the distance L between the top surface of the positioning disc 5 and the mounting end surface of the compressor rotor assembly 100 is measured until the inner hole thread of the part is completely meshed. In addition, the positioning disc 5 can be equipped with a limiting disc through the locking bolt 4. At this time, the center pull rod 700 is adjusted by rotating the positioning disc 5, and the distance L between the top surface of the positioning disc 5 and the mounting end surface of the compressor rotor assembly 100 is measured, so that the distance L meets the preset assembly requirement, so as to ensure the size of the installation and improve the stability and accuracy of the assembly.

[0059] According to another aspect of the present application, a turboshaft engine gas generator rotor assembly method is also provided, which comprises the turboshaft engine gas generator rotor assembly device, and the turboshaft engine gas generator rotor assembly method comprises the following steps:

[0060] S100, the end tooth engagement test of the compressor rotor assembly 100 is carried out by using the end tooth engagement test clamp 1000, the oil pipe between the hydraulic equipment connected with the compressor rotor assembly 100 and the hydraulic pump 3 is connected, the hydraulic pump 3 is repeatedly pressed, after the pressing is completed, the tooth engagement test clamp 1000 is disassembled, the engagement of the end teeth of the blade discs of each stage is checked, and if there is no problem, the formal assembly is carried out.

[0061] S200, the compressor rotor assembly 100 is combined by using the compressor rotor stretching clamp 2000, the second pull rod 16 is lifted by the stretching assembly, the connecting expansion sleeve 2 is expanded and engaged with the inner threaded hole of the center pull rod 700 by the protruding part, the center pull rod 700 is adjusted by rotating the positioning disc 5, and the distance L between the top surface of the positioning disc 5 and the mounting end surface of the compressor rotor assembly 100 is measured, so that the distance L meets the preset assembly requirement.

[0062] S300, the support 1, the hydraulic pump 3, the force transmission block 9 and the adjusting nut 10 are installed, the oil pipe between the hydraulic equipment and the hydraulic pump 3 is connected, the hydraulic pump 3 is repeatedly pressed, and the compression amount of the rear back of the centrifugal impeller 800 before and after tensioning should be within the design requirement range by using the dial indicator.

[0063] S400, the support 1, the hydraulic pump 3, the force transmission block 9 and the adjusting nut 10 are disassembled, the gap between the center pull rod locking nut assembly and the centrifugal impeller 800 is checked by using the feeler gauge, the 0.02mm thickness feeler gauge should not be able to pass, and the first bearing 500 is installed.

[0064] S500, after warming the rotor connecting shaft 900, it is installed on the centrifugal impeller 800;

[0065] S600, the inner ring of the second bearing 600 is installed on the turbine connecting shaft 200 after being warmed, and the outer ring of the second bearing 600 is installed after the inner ring of the second bearing 600 is cooled;

[0066] S700, the gas turbine first rotor 300 and the gas turbine second rotor 400 are installed, the gas turbine first rotor 300 is installed with the high point of the circular arc end tooth jump of the turbine connecting shaft 200 being staggered by 180 degrees, and the gas turbine second rotor 400 is also installed with the high point of the circular arc end tooth jump of the gas turbine first rotor 300 being staggered by 180 degrees.

[0067] The turbine-shaft engine gas generator rotor assembly method has the beneficial effects as described above, and further includes adjusting the assembly size control requirement to improve the process accuracy, increasing the process control to improve the assembly quality, strengthening the inspection work of the parts before assembly, realizing the end tooth engagement test before assembly, realizing the pre-tightening-unloading repeated pressing through the analysis of the compressor rotor structure, making the turbine connecting shaft 200 and the rotor connecting shaft 900 completely fit, and increasing the end tooth jump inspection tooling to make the turbine connecting shaft 200 assembly quality more intuitive, thereby ensuring the assembly quality. Through the analysis of the process difficulties in the cantilever gas generator rotor assembly process, the application formulates reasonable and feasible solutions, proposes the "segmented control method" and "constant temperature pressing method", improves the assembly stability, optimizes the process flow, improves the tooling equipment, ensures the assembly reliability of the engine, improves the assembly efficiency of the engine, and shortens the assembly cycle from 4 days per unit to 1 day per unit, thereby 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, the hydraulic valve on the hydraulic equipment is opened, the adjusting nut 10 is tightened to reset the hydraulic pump 3, the adjusting nut 10 is loosened by 1 / 4 turn of the thread, the hydraulic valve is closed, the pressing is performed through the hydraulic pump 3, the pre-tightening force of 1KN-2KN is applied on the compressor rotor assembly 100, the hydraulic valve is opened to remove the pressure of the hydraulic pump 3, the adjusting nut 10 is loosened, and the end tooth engagement test fixture 1000 is disassembled after repeating 3-5 times, and the engagement of the end teeth of the blade discs of each stage is checked.

[0069] It can be understood that through the repeated pressing by the hydraulic pump 3, the pre-tightening-unloading repeated operation is realized, the engagement of the end teeth of the blade discs of each stage can be accurately checked, and no problem is found before formal assembly.

[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 relevant 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, and whether there are burrs or foreign objects on the threads, etc., to avoid the problem of gas generator vibration caused by the nut being stuck or the self-locking nut not being tightened properly due to foreign objects and 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 1 / 4 turn of the adjusting nut 10, close the hydraulic valve and 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 repeatedly pressing with the hydraulic pump 3 to achieve pressurization-unloading assembly and inspection can ensure that the compression of the back of the centrifugal impeller 800 before and after tightening 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 during 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, respectively. After completing the rotor connecting shaft assembly, we measured the dimension C at the corresponding positions, and required that the selected 4 positions simultaneously meet A+B≤C±0.02mm.

[0075] Preferably, 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.

[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 the torque.

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

[0078] In order to avoid repeated assembly of the rotor caused by unqualified runout of the inner hole of the gas, the process internal control requirement of the runout of the reference K is added in the assembly process, which requires that the runout is not greater than 0.015 mm. If it is unqualified, the assembly quality is ensured by adjusting the angular position of the rotor connecting shaft 900 or replacing the part.

[0079] Preferably, in step S600, the end tooth runout checking gauge 3000 is clamped to the compressor rotor assembly 100, the runout of the simulation disk 13 is measured, and the runout should be not greater than 0.025 mm. If it is unqualified, the angular position of the simulation disk 13 and the turbine connecting shaft 200 is adjusted clockwise, and the measurement is repeated until the runout is not 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 rotor connecting shaft 900 is exposed at least one thread by pressing the turbine connecting shaft 200 with the hand.

[0081] Preferably, in step S700, the lever dial gauge is used to check the inner hole runout of the second stage rotor 400 of the gas turbine, which should be not greater than 0.03 mm. If it is unqualified, the second stage rotor 400 and the first stage rotor 300 of the gas turbine are separated, the angular position of the first stage rotor 300 and the second stage rotor 400 of the gas turbine and the turbine connecting shaft 200 is adjusted, and the measurement is repeated until the inner hole runout of the second stage rotor 400 of the gas turbine is not greater than 0.03 mm.

[0082] It should be noted that when the engine is assembled, the inner hole runout of the second stage disk of the gas turbine at two cross sections should be not greater than 0.03 mm, and the part runout is not greater than 0.01 mm, and the high point and the part record high point position are not greater than ±72° (i.e. allowed to change to an adjacent long bolt hole), which ensures the assembly consistency.

[0083] The application is especially a multi-stage compressor cantilever fulcrum combined rotor assembly method and adjustment method. The coaxiality and assembly consistency of the gas generator rotor are ensured by designing tooling, strengthening process control, optimizing process flow and method, etc., which avoids repeated disassembly, part wear and deformation, etc.

[0084] It should be noted that, in this text, the term "comprising", "including" or any other variant thereof is intended to cover a non-exclusive inclusion, so that a process, method, article or apparatus that includes a list of elements not only includes those elements, but also includes other elements not explicitly listed, or inherent to such process, method, article or apparatus.

[0085] The principles and implementation manners of the present application are described herein by using specific examples, and the above example descriptions are only for helping to understand the method of the present application and its core idea. The above description is only the preferred implementation manner of the present application, and it should be noted that, due to the limited expression of the text, there are objectively infinite specific structures, and for ordinary skilled persons in the technical field, some improvements, refinements or changes can be made without departing from the principles of the present application, and the above technical features can also be combined in an appropriate manner; the improvements, refinements, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, shall be regarded as the protection of the present application.

Claims

1. A turboshaft engine gas generator rotor assembly device for assembling a gas generator rotor component, wherein the gas generator rotor component comprises 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 turbine engine gas generator rotor assembly device comprises an end-tooth engagement test clamp (1000) and a compressor rotor stretching clamp (2000): The end-tooth engagement test clamp (1000) comprises a support (1), a hydraulic pump (3), a force block (9), an adjusting nut (10), a first pull rod (15) and a base (11), the base (11) is used for supporting the compressor rotor assembly (100) and the first pull rod (15), the first pull rod (15) is arranged on the compressor rotor assembly (100) and the bottom end thereof is connected with the base (11) through screw threads, the support (1) is used for being arranged on the compressor rotor assembly (100), the hydraulic pump (3) is arranged on the top of the support (1), the adjusting nut (10) and the force block (9) are sequentially arranged on the top of the first pull rod (15) from top to bottom, the adjusting nut (10) is connected with the first pull rod (15) through screw threads, and the adjusting nut (10) is used for pushing the force block (9) to press the hydraulic pump (3) on the top of the support (1); The compressor rotor stretching clamp (2000) comprises a connecting expansion sleeve (2), a positioning disc (5), a stretching assembly and a second pull rod (16), the bottom end of the second pull rod (16) is arranged in the compressor rotor assembly (100), the connecting expansion sleeve (2) is movably arranged on the bottom of the second pull rod (16), the bottom end of the second pull rod (16) is provided with a protruding part, the positioning disc (5) is arranged on the second pull rod (16) and limits the top of the connecting expansion sleeve (2), the stretching assembly is arranged on the second pull rod (16) and above the positioning disc (5), the stretching assembly is used for driving the second pull rod (16) to ascend and descend, and then the connecting expansion sleeve (2) is expanded and engaged with the internal thread hole of the central pull rod (700) through the protruding part when the second pull rod (16) ascends; the turbine engine gas generator rotor assembly device further comprises an end-tooth runout checking gauge (3000), the end-tooth runout checking gauge (3000) comprises a pressing nut (12), an analog disc (13), a limiting block (14) and a third pull rod (17), the third pull rod (17) is used for sequentially penetrating through the first bearing (500), the compressor rotor assembly (100) and the second bearing (600), the analog disc (13) is arranged on the first end of the third pull rod (17) close to the first bearing (500), the analog disc (13) is used for engaging with the circular arc end tooth of the turbine connecting shaft (200), the pressing nut (12) is arranged on the third pull rod (17), the pressing nut (12) is used for pressing the analog disc (13), and the limiting block (14) is arranged on the second end of the third pull rod (17) and is connected with the third pull rod (17) through screw threads, the limiting block (14) is used for abutting against the second bearing (600) and limiting the second end of the third pull rod (17).

2. A turboshaft engine gas generator rotor assembly as set forth in claim 1 wherein, The stretching assembly comprises a positioning pin (6), a positioning block (7) and a locking piece (8), the positioning block (7) is arranged on the second pull rod (16) movably and above the positioning disc (5), the positioning pin (6) is vertically arranged on the top of the positioning disc (5), the positioning pin (6) is used for cooperating with the U-shaped groove pre-set on the bottom of the positioning block (7), the locking piece (8) is sleeved on the second pull rod (16) and is connected with the second pull rod (16) through screw threads, the locking piece (8) is used for pressing the top of the limiting positioning block (7), and the locking piece (8) is also used for driving the second pull rod (16) to move up and down along the axial direction when rotating.

3. A method of assembling a gas generator rotor of a turboshaft engine, characterized in that, The turboshaft engine gas generator rotor assembly device and the turboshaft engine gas generator rotor assembly method of any one of claims 1-2 comprise the following steps: S100, the end tooth engagement test of the compressor rotor assembly (100) is carried out by using the end tooth engagement test fixture (1000), the oil pipe between the hydraulic equipment connected with the compressor rotor assembly (100) and the hydraulic pump (3) is connected, repeated pressure is carried out through the hydraulic pump (3), after the pressure is finished, the end tooth engagement test fixture (1000) is disassembled, the engagement of the end teeth of the blade discs of all levels is checked, if there is no problem, the formal assembly is carried out; S200, the compressor rotor assembly (100) is combined by using the compressor rotor stretching fixture (2000), the second pull rod (16) is driven to rise by the stretching assembly, the connecting expansion sleeve (2) is expanded and engaged with the internal threaded hole of the center pull rod (700) by the protruding part, the center pull rod (700) is adjusted in position by rotating the positioning disc (5), and the distance L from the top surface of the positioning disc (5) to the mounting end surface of the compressor rotor assembly (100) is measured, so that the distance L meets the preset assembly requirement; S300, the support (1), the hydraulic pump (3), the force transmission block (9) and the adjusting nut (10) are installed, the oil pipe between the hydraulic equipment and the hydraulic pump (3) is connected, repeated pressure is carried out through the hydraulic pump (3), and the compression amount of the rear back of the centrifugal impeller (800) before and after tensioning should be within the design requirement range by using the dial gauge; S400, the support (1), the hydraulic pump (3), the force transmission block (9) and the adjusting nut (10) are disassembled, the gap between the center pull rod locking nut assembly and the centrifugal impeller (800) is checked by using the feeler gauge, the 0.02mm thickness feeler gauge should not be able to pass, and the first bearing (500) is installed; S500, after the rotor connecting shaft (900) is warmed, it is installed on the centrifugal impeller (800); S600, the inner ring of the second bearing (600) is installed on the turbine connecting shaft (200) after being warmed, and the outer ring of the second bearing (600) is installed after the inner ring of the second bearing (600) is cooled; S700, the gas turbine first stage rotor (300) and the gas turbine second stage rotor (400) are installed, the gas turbine first stage rotor (300) is installed with the circular arc end tooth high point of the turbine connecting shaft (200) staggered by 180 degrees, and the gas turbine second stage rotor (400) is installed with the circular arc end tooth high point of the gas turbine first stage rotor (300) also staggered by 180 degrees.

4. A method of assembling a gas generator rotor for a turboshaft engine as claimed in claim 3, wherein, In step S100, after connecting the oil pipe between the hydraulic device of the compressor rotor assembly (100) and the hydraulic pump (3), the hydraulic valve on the hydraulic device is opened, the adjusting nut (10) is tightened to reset the hydraulic pump (3), the adjusting nut (10) is loosened by 1 / 4 of a turn, the hydraulic valve is closed to press by the hydraulic pump (3), a pre-tightening force of 1KN-2KN is applied on the compressor rotor assembly (100), the hydraulic valve is opened to remove the pressure of the hydraulic pump (3), the adjusting nut (10) is loosened, and the end tooth engagement test fixture (1000) is disassembled after repeating 3-5 times, and the engagement of the end teeth of the blade discs of each stage is checked.

5. The turboshaft engine gas generator rotor assembly method of claim 3, wherein, 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 to reset the hydraulic pump (3), the adjusting nut (10) is loosened by 1 / 4 of a turn, the hydraulic valve is closed to press by the hydraulic pump (3), a pre-tightening force of 3KN-4KN is applied on the compressor rotor assembly (100), the hydraulic valve is opened to remove the pressure of the hydraulic pump (3), the adjusting nut (10) is loosened, and the compression amount of the rear back of the centrifugal impeller (800) before and after tensioning is checked again by using the dial gauge after repeating three times.

6. A method of assembling a gas generator rotor for a turboshaft engine as set forth in claim 3, 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 of the rear flange of the centrifugal impeller (800) and the front flange of the rotor connecting shaft (900) respectively, the size C of the connection after the rotor connecting shaft (900) is assembled is measured, and the four selected positions simultaneously satisfy A+B≤C±0.02mm.

7. The method of assembling a gas generator rotor for a turboshaft engine of claim 3, wherein, In step S500, the reference runout on the rotor connecting shaft (900) is checked, and the runout should be not greater than 0.015mm, if not qualified, the rotor connecting shaft (900) is disassembled and reassembled.

8. The method of assembling a gas generator rotor for a turboshaft engine of claim 3, wherein, In step S600, the end tooth runout checking gauge (3000) is clamped to the compressor rotor assembly (100), the runout of the simulation disc (13) is measured, and the runout should be not greater than 0.025mm, if not qualified, the angular position of the simulation disc (13) and the turbine connecting shaft (200) is adjusted clockwise, and the measurement is repeated until the runout is not greater than 0.025mm.

9. The method of claim 3, wherein: In step S700, the lever dial gauge is used to check the bore runout of the gas turbine second rotor (400), which should be not greater than 0.03mm, if not qualified, the gas turbine first rotor (300) and the gas turbine second rotor (400) are separated, and the angular position of the gas turbine first rotor (300) and the gas turbine second rotor (400) and the turbine connecting shaft (200) is adjusted, and the measurement is repeated until the bore runout of the gas turbine second rotor (400) is not greater than 0.03mm.

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