CN118518345B - Rotor testing device and rotor testing method - Google Patents
Rotor testing device and rotor testing method Download PDFInfo
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- CN118518345B CN118518345B CN202410997410.1A CN202410997410A CN118518345B CN 118518345 B CN118518345 B CN 118518345B CN 202410997410 A CN202410997410 A CN 202410997410A CN 118518345 B CN118518345 B CN 118518345B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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Abstract
The invention discloses a rotor test device and a rotor test method, which are used for carrying out vibration response test on a rotor of an aero-engine, wherein the aero-engine rotor comprises a rotating shaft, a bearing and a squirrel cage elastic support, and the rotor test device comprises: a support structure for supporting; the switching component is annular and is used for being connected with the supporting structure and supporting the bearing so as to support the rotating shaft, and the switching component is provided with a mounting structure; the oil film bushing is annular, the oil film bushing is provided with a matching structure, the mounting structure is used for mounting the oil film bushing, and the matching structure of the oil film bushing is used for forming an oil film gap with a preset size with the squirrel cage elastic support; the first oil supply structure is arranged on the switching assembly and connected with a first oil source and is used for supplying oil to the oil film gap; the second oil supply structure is arranged on the switching assembly and connected with a second oil source and used for supplying oil to the bearing.
Description
Technical Field
The invention relates to the technical field of aero-engine rotors, in particular to a rotor test device. In addition, the invention also relates to a rotor test method comprising the rotor test device.
Background
The quality of the vibration characteristics of the rotor of the aero-engine is directly related to the performance and reliability of the engine, but the rotor of the aero-engine has complex structure, high rotating speed and severe working environment, and has more factors influencing the vibration characteristics of the rotor, so that how to effectively inhibit the vibration of a rotor-supporting system is particularly important. The extrusion oil film damper has the characteristics of simple structure, small occupied space, easy manufacture, remarkable vibration reduction effect and the like, and is widely applied to a rotor-supporting system of an aero-engine. The oil film gap is an important parameter of the extrusion oil film damper and has a decisive influence on the vibration reduction effect, however, because the actual boundary condition is difficult to simulate during modeling, the oil film mechanism is not quite clear, the oil film gap obtained through theoretical calculation is difficult to meet engineering requirements, a group of oil film gaps are generally initially selected by combining calculation results, reference and engineering experience in actual work, and then the ideal oil film gap is determined through a rotor vibration response test on a rotation tester. However, determining an ideal oil film gap through a rotor vibration response test is a very complicated and high-cost work, and usually, each fulcrum is used for processing a group of squirrel cage elastic supports and/or a group of adapter seats (corresponding to bearing seats of an engine rotor) according to the required oil film gap, and the purpose of changing the fit gap between the squirrel cage elastic supports and the bearing seats is achieved through the combination of the squirrel cage elastic supports and the adapter seats, so that the adjustment of the oil film gap is realized; it is also possible to machine only one elastic cage support and one adaptor for each fulcrum, for example to change the oil film gap, by means of additional machining of the relevant mating surfaces of the cage support and/or the bearing seat. The invention provides an accurate adjustment device for the extrusion oil film gap of an aeroengine rotor, which can accurately, conveniently and quickly change the oil film gap in a rotor vibration response test on a rotary tester, can efficiently determine an ideal oil film gap range through accurate adjustment of the oil film gap, can greatly reduce the processing cost of a squirrel cage elastic support and a bearing seat and the assembly cost of a rotor test piece, can greatly shorten the period of multiple rotor vibration response tests, and has great significance in accelerating the development progress of models and improving the design level of oil film structural parameters of an extrusion oil film damper, and has remarkable engineering application value.
The prior art scheme will be described with reference to a certain scroll engine gas generator rotor. The rotor adopts a supporting scheme of 1-0-1, front and rear fulcrums adopt squirrel-cage elastic supporting structures with extrusion oil film dampers, as shown in fig. 1, a group of oil film gaps are preliminarily selected by each fulcrum in combination with calculation results, references and engineering experience, and vibration reduction effect verification is carried out on the group of oil film gaps one by one on a rotary tester through a rotor vibration response test, so that an ideal oil film gap range is determined, and a schematic diagram of the prior scheme is shown in fig. 2. If the oil film gap is to be changed for rotor vibration response test, the following two methods are generally adopted: (1) Each fulcrum is provided with a group of squirrel cage elastic supports and/or a group of adapter seats, and the purpose of changing the oil film gap is achieved by changing the fit gap (namely the oil film gap) of the corresponding fit surfaces of the squirrel cage elastic supports and/or the adapter seats; the method has the advantages of high material and processing cost, higher difficulty in meeting the requirement of consistent processing precision, high difficulty in disassembling and assembling the rotor and high requirement of replacing the squirrel cage elastic support and/or the adapter seat in each rotor test, and longer period for completing the rotor vibration response test of a group of oil film gaps; (2) Each fulcrum is provided with a squirrel cage elastic support and an adapter seat, if the oil film clearance needs to be changed, the corresponding matching surfaces of the squirrel cage elastic support and/or the adapter seat are subjected to complementary machining according to the requirement, so that the matching clearance (namely the oil film clearance) of the corresponding matching surfaces meets the requirement, and the method has the advantages of high complementary machining difficulty, difficult guarantee of the machining precision (poor machining precision) of the matching surfaces and high machining cost; the squirrel-cage elastic support and/or the adapter seat after the repair processing are replaced before each rotor test, the difficulty in rotor disassembly and assembly is high, the requirement is high, the period of rotor vibration response test for completing a group of oil film gaps is longer, and meanwhile, the strength and the rigidity of the squirrel-cage elastic support can be changed by the repair processing, so that the service performance of the squirrel-cage elastic support is adversely affected.
In the prior art, as disclosed in the technical scheme of patent number cn201711463234.X, a performance test device for an extrusion oil film damper with adjustable parameters is disclosed, by arranging an oil film outer ring support piece, an oil film outer ring and an oil film inner ring to be respectively matched, and replacing the oil film outer ring to realize different oil film gaps and oil film widths for testing, the test efficiency is higher and the cost is lower, but because extrusion oil film and bearing lubrication and the like in an engine are all of homologous oil supply, although the extrusion oil film and the bearing lubrication are in a normal oil supply pressure range, the oil supply pressures of the extrusion oil film and the bearing lubrication and the like are always consistent, the conventional vibration reduction characteristic test equipment is designed for simulating the actual working condition of the engine so as to discharge various influencing factors, and therefore, the test in the prior art does not consider the influence of different oil supply pressures under different oil film gaps and cannot realize verification of the influence, thereby being unfavorable for the design of the engine.
Disclosure of Invention
The invention provides a rotor test device and a rotor test method, which are used for solving the technical problems that in the rotor vibration damping characteristic test in the prior art, the cost for changing the oil film gap is high, the disassembly and assembly difficulty is high, and the influence of oil supply pressure cannot be considered.
According to one aspect of the present invention, there is provided a rotor test apparatus for performing a vibration response test on a rotor of an aircraft engine, the aircraft engine rotor including a shaft, a bearing and a cage spring support, the rotor test apparatus comprising:
a support structure for supporting;
the switching component is annular and is used for being connected with the supporting structure and supporting the bearing so as to support the rotating shaft, and the switching component is provided with a mounting structure;
The oil film bushing is annular, the oil film bushing is provided with a matching structure, the mounting structure is used for mounting the oil film bushing, and the matching structure of the oil film bushing is used for forming an oil film gap with a preset size with the squirrel cage elastic support;
the first oil supply structure is arranged on the switching assembly and connected with a first oil source and is used for supplying oil to the oil film gap;
the second oil supply structure is arranged on the switching assembly and connected with a second oil source and used for supplying oil to the bearing.
As a further improvement of the above technical solution, the second oil supply structure includes a nozzle disposed on the adapter assembly, and the nozzle is located on one side of the bearing; the first oil supply structure comprises an oil inlet path and an oil return path which are arranged on the switching assembly, the oil film bushing is provided with an oil inlet hole, and two ends of the oil inlet hole are respectively communicated with the oil inlet path and the matching structure.
As a further improvement of the technical scheme, the oil return oil way is positioned at the lower part of the switching assembly in the installation state and returns oil based on the action of gravity, and the oil return oil way is communicated to the bottom of the installation structure and is communicated to the inner wall of the switching assembly through the bottom of the installation structure.
As a further improvement of the technical scheme, the mounting structure is arranged in the inner cavity of the switching assembly, the inner wall of the inner cavity is provided with an oil return port, or the mounting structure is arranged at one end of the inner cavity of the switching assembly, and the outer end, close to the oil film bushing, of the inner wall of the oil film bushing is provided with an oil return hole which is communicated to the oil return path.
As a further improvement of the technical scheme, the outer end of the oil film bushing is provided with a connecting flange, connecting holes are uniformly distributed on the connecting flange along the circumferential direction, and threaded holes matched with the connecting holes are formed in the adapter component.
As a further improvement of the technical scheme, sealing grooves for embedding sealing rings are respectively arranged on the two ends of the inner wall of the oil film bushing in the matching structure.
As the further improvement of above-mentioned technical scheme, rotor test device still includes test platform, power device and sets up the vacuum test case on test platform, bearing structure including the activity set up in first support and the second support in the vacuum test case, the switching subassembly is including corresponding respectively first adapter and the second adapter that the bearing set up, first support is used for the installation first adapter, the second support is used for the installation the second adapter.
According to another aspect of the present invention, there is also provided a rotor test method including the rotor test apparatus described above, the test method including:
S1, preparing a test;
s2, adjusting the pressure of the vacuum test chamber and the oil supply pressure;
s3, starting to a parameter limit value or a target rotating speed, and recording related parameters in the speed increasing process;
S4, stopping the vehicle to finish the test;
S5, replacing the oil film bushing and/or changing oil film gap oil supply pressure, and repeating the steps S2-S4.
As a further improvement of the above technical solution, step S1 includes:
s11, adjusting positions of the first support and the second support;
S12, aligning;
s13, mounting a rotor to be tested;
s14, checking lubrication and oil return conditions of the bearing;
S15, checking the processing, assembling and mounting quality of the rotor;
s16, installing a measuring module and connecting the measuring module with a test.
As a further improvement of the above technical solution, step S3 further includes: if the speed is increased to the target rotating speed and exceeds the parameter limit value, stopping the vehicle to analyze the vibration signal, if the parameter limit value is exceeded due to the change of the oil film parameter, turning to the step S5, otherwise, reassembling, installing or aligning, and restarting the driving test after eliminating the overrun factor.
The invention has the following beneficial effects:
The supporting structure of the rotor test device is used as a support, the adapter component is arranged between the supporting structure and the bearing of the rotor to support the bearing so as to further support the rotating shaft, the installation structure arranged on the adapter component is used for installing the oil film bushings, the matching structure of the oil film bushings is arranged to be in a preset size, a plurality of groups of oil film bushings are manufactured through design, the accurate adjustment of the extrusion oil film clearance of the rotor test can be realized by only replacing the oil film bushings with different matching structure sizes for combination in the test research process, and the ideal value range of the oil film clearance of the rotor of the aeroengine can be determined quickly, efficiently and at low cost; and the first oil supply structure and the second oil supply structure are respectively and independently arranged based on the design of the switching assembly, the extrusion oil film gap and the bearing lubrication in the test are respectively and independently supplied with oil, so that the extrusion oil film pressure and the lubricating oil pressure in the oil film gap can be independently adjusted, under the condition that the bearing lubrication is kept to be normally supplied with oil in the test, the normal oil supply or the oil supply stopping is controlled to verify the lower vibration reduction effectiveness of the oil film gap under the limit working condition, the oil film gap range is further rapidly screened, the test efficiency is greatly improved, the design of the extrusion oil film damper is effectively guided, the influence of different oil pressures of the extrusion oil film is respectively considered in the test, the oil pressure of the extrusion oil film gap is further introduced as a reference variable, a large number of test groups are jointly formulated by combining with the oil film gaps with different sizes, and all the tests can be rapidly, high efficiency and low cost are completed.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic illustration of a prior art rotor vibration response test;
FIG. 2 is an enlarged view at B of FIG. 1;
FIG. 3 is a schematic view of a rotor test apparatus according to a preferred embodiment of the present invention;
FIG. 4 is a schematic view of a nozzle in a first stand-off position according to a preferred embodiment of the present invention;
FIG. 5 is a schematic view of a nozzle in a second stand-off position in accordance with a preferred embodiment of the present invention;
FIG. 6 is a schematic view of oil supply at a first seat position according to a preferred embodiment of the present invention;
FIG. 7 is a schematic illustration of oil supply to a second seat position in accordance with a preferred embodiment of the present invention;
FIG. 8 is a schematic view of oil return from a first stand position according to a preferred embodiment of the present invention;
FIG. 9 is a schematic view of oil return from a second seat position in accordance with a preferred embodiment of the present invention;
FIG. 10 is a schematic view of an installation test of a preferred embodiment of the present invention;
FIG. 11 is a histogram of rotor deflection at different oil film gap conditions for a first embodiment of the present invention;
FIG. 12 is a bar graph of vibration acceleration under different oil film gap conditions for a first embodiment of the present invention;
FIG. 13 is a spring-loaded strain bar graph under different oil film gap conditions for a first embodiment of the present invention;
FIG. 14 is a bar chart of bearing temperature rise under different oil film gap conditions for a first embodiment of the present invention;
Legend description:
1. The device comprises a first adapter seat 2, a second adapter seat 3, a mounting structure 4, an oil film bushing 5, an oil inlet oil way 6, an oil return oil way 7, a nozzle 8, an oil inlet hole 9, an oil return hole 10, an oil return hole 11, an oil storage tank 12, a connecting flange 13, a sealing groove 14, a squirrel cage elastic support 15 and a bearing.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
FIG. 3 is a schematic view of a rotor test apparatus according to a preferred embodiment of the present invention; FIG. 4 is a schematic view of a nozzle in a first stand-off position according to a preferred embodiment of the present invention; FIG. 5 is a schematic view of a nozzle in a second stand-off position in accordance with a preferred embodiment of the present invention; FIG. 6 is a schematic view of oil supply at a first seat position according to a preferred embodiment of the present invention; FIG. 7 is a schematic illustration of oil supply to a second seat position in accordance with a preferred embodiment of the present invention; FIG. 8 is a schematic view of oil return from a first stand position according to a preferred embodiment of the present invention; FIG. 9 is a schematic view of oil return from a second seat position in accordance with a preferred embodiment of the present invention; FIG. 10 is a schematic view of an installation test of a preferred embodiment of the present invention; FIG. 11 is a histogram of rotor deflection at different oil film gap conditions for a first embodiment of the present invention; FIG. 12 is a bar graph of vibration acceleration under different oil film gap conditions for a first embodiment of the present invention; FIG. 13 is a spring-loaded strain bar graph under different oil film gap conditions for a first embodiment of the present invention; FIG. 14 is a bar chart of bearing temperature rise under different oil film gap conditions for a first embodiment of the present invention.
As shown in fig. 3 to 9, the rotor test apparatus of the present embodiment is used for performing a vibration response test on a rotor of an aeroengine, the aeroengine including a rotating shaft, a bearing 15 and a cage elastic support 14, the rotor test apparatus including:
a support structure for supporting;
The switching component is annular and is used for being connected with the supporting structure and supporting the bearing 15 so as to further support the rotating shaft, and the switching component is provided with the mounting structure 3;
the oil film bushing 4 is annular, the oil film bushing 4 is provided with a matching structure, the mounting structure 3 is used for mounting the oil film bushing 4, and the matching structure of the oil film bushing 4 is used for forming an oil film gap with a preset size with the squirrel cage elastic support 14; the preset size comprises a radial size and an axial size of an oil film gap;
The first oil supply structure is arranged on the switching assembly and connected with a first oil source and is used for supplying oil to the oil film gap;
The second oil supply structure is arranged on the adapter assembly and connected with a second oil source for supplying oil to the bearing 15.
The rotor test device in this embodiment takes a horizontal high-speed rotation tester as an example, and further comprises a test platform, a power device and a vacuum test box arranged on the test platform, wherein the support structure comprises a first support and a second support movably arranged in the vacuum test box, the switching component comprises a first adapter seat 1 and a second adapter seat 2 which are respectively arranged corresponding to a front bearing 15 and a rear bearing 15, the first support is used for installing the first adapter seat 1, the second support is used for installing the second adapter seat 2, the power device is connected with a rotating shaft, and the rotor is driven to rotate in the test;
The oil film bushing 4 is in cylindrical surface centering and interference fit with the mounting structure 3 of the adapter assembly, and the outer wall of the inner end of the oil film bushing 4 is provided with a conical surface so as to enter the mounting structure 3; the mounting structure 3 is of a step structure arranged in the inner cavity of the adapter assembly, and the depth of the mounting structure 3 is matched with the oil film bushing 4;
It can be understood that the supporting structure of the rotor test device is used as a support, a switching component supporting bearing 15 is arranged between the supporting structure and a bearing 15 of a rotor so as to support a rotating shaft, a mounting structure 3 arranged on the switching component is used for mounting oil film bushings 4, the matching structure of the oil film bushings 4 is arranged to be in a preset size, and a plurality of groups of oil film bushings 4 are designed and manufactured, so that the accurate adjustment of the extrusion oil film gap of the rotor test can be realized by only replacing the oil film bushings 4 with different matching structure sizes for combination in the test research process, and the ideal value range of the oil film gap of the rotor of the aeroengine can be determined quickly, efficiently and at low cost; and the first oil supply structure and the second oil supply structure are respectively and independently arranged based on the design of the switching assembly, the extrusion oil film gap and the bearing 15 in the test are respectively and independently supplied with oil, so that the extrusion oil film pressure and the lubricating oil pressure in the oil film gap can be independently adjusted, under the condition that the bearing 15 is lubricated and normally supplied with oil in the test, the lower vibration reduction effectiveness of the oil film gap is verified under the limit working condition by controlling the normal oil supply or the oil supply stopping of the extrusion oil film, the oil film gap range is further rapidly screened, the test efficiency is greatly improved, the design of the extrusion oil film damper is effectively guided, the influence of different oil pressures of the extrusion oil film is also respectively considered in the test, the oil pressure of the extrusion oil film gap is further introduced as a reference variable, a large number of test groups are jointly formulated in combination with the oil film gaps with different sizes, and all tests can be rapidly, high efficiency and low cost are completed, a reliable basis is provided for the design of the extrusion oil film damper oil film parameters of the gas generator rotor, the forward design level of the extrusion oil film damper is facilitated, and the vibration reduction design technology of the high-speed rotor is enriched and developed.
In one embodiment, the second oil supply structure comprises a nozzle 7 arranged on the adapter component, the nozzle 7 is positioned on one side of the bearing 15, in one embodiment, the front nozzle 7 at the front bearing 15 is in jet lubrication, the rear nozzle 7 at the rear bearing 15 is in ring lubrication, and in other embodiments, the jet lubrication or the ring lubrication is arranged in a matching way in actual design conditions; the first oil supply structure comprises an oil inlet path 5 and an oil return path 6 which are arranged on the adapter assembly, the oil film bushing 4 is provided with an oil inlet hole 8, and two ends of the oil inlet hole 8 are respectively communicated with the oil inlet path 5 and the matching structure;
The oil return oil way 6 is positioned at the lower part of the switching assembly in the installation state and is used for returning oil based on the action of gravity, the oil return oil way 6 is communicated to the bottom of the installation structure 3 and is communicated to the inner wall of the switching assembly through the bottom of the installation structure 3, namely, the connection position of the bottom of the installation structure 3 and the switching assembly is positioned on the oil return oil way 6, and oil flows to the oil inlet oil way 5 towards the inner end direction of the oil film bushing 4 and returns oil under the action of gravity;
In an embodiment, the mounting structure 3 is arranged in an inner cavity of the adapter component, an oil return port 10 is formed in the inner wall of the inner cavity, or the mounting structure 3 is arranged at one end of the inner cavity of the adapter component, and an oil return hole 9 for communicating to the oil return oil way 6 is formed in the inner wall of the oil film bushing 4, close to the outer end of the oil film bushing 4; specifically, referring to fig. 8, the mounting structure 3 is disposed in the inner cavity of the first adapter 1, an oil return port 10 is formed in the inner cavity of the first adapter 1, an oil return oil path 6 of the first adapter 1 is connected to the inner wall of the inner cavity, so that oil flowing out from an extrusion oil film to the inner end of the oil film bushing 4 returns through the oil return oil path 6 to the oil return port 10, oil flowing out from the extrusion oil film to the outer end of the oil film bushing 4 flows to the inner wall of the inner cavity to the oil return port 10 under the action of gravity for returning, and the oil return of the first adapter 1 are the same; referring to fig. 9, the outer end of the oil film bushing 4 in the second adapter 2 is located outside the inner cavity of the second adapter 2, oil cannot be returned through the oil return opening 10 formed in the inner cavity, and the oil return hole 9 formed in the inner wall of the oil film bushing 4 and close to the outer end of the oil film bushing 4 is communicated to the oil return oil path 6, so that oil flowing out from two ends of the oil film bushing 4 is returned through the oil return oil path 6.
It should be understood that the outer wall of the oil film bushing 4 is provided with an annular oil storage groove 11 matched with the axial position of the oil inlet passage 5 so as to ensure stable oil supply capacity and oil supply pressure, and the plurality of oil inlet holes 8 are uniformly distributed along the circumferential direction of the oil film bushing 4.
In an embodiment, the outer end of the oil film bushing 4 is provided with a connecting flange 12, connecting holes are uniformly distributed on the connecting flange 12 along the circumferential direction, and threaded holes matched with the connecting holes are formed in the adapter component, so that the oil film bushing 4 is convenient to assemble and disassemble, and the operation is simple.
In one embodiment, seal grooves 13 for embedding seal rings are respectively arranged at two ends of the matching structure on the inner wall of the oil film bushing 4.
The rotor test method of the embodiment is applied with the rotor test device, and comprises the following steps:
S1, preparing a test;
s2, adjusting the pressure of the vacuum test chamber and the oil supply pressure;
s3, starting to a parameter limit value or a target rotating speed, and recording related parameters in the speed increasing process;
S4, stopping the vehicle to finish the test;
s5, replacing the oil film bushing 4 and/or changing oil film gap oil supply pressure, and repeating the steps S2-S4.
In one embodiment, step S1 includes:
S11, adjusting positions of the first support and the second support; specifically, according to the trial assembly condition of the tested rotor on the tester, the first support and the second support are respectively adjusted to proper axial positions;
S12, aligning; specifically, a laser centering instrument and a special centering tool are used for sequentially completing centering work of the central hole of the first support relative to an output shaft of a power rotating shaft of the tester and the central hole of the second support relative to the central hole of the first support; the opening errors of the central holes of two adjacent supports are required to be no more than phi 0.05mm/100mm, and the parallel errors in the vertical direction and the horizontal direction are required to be no more than 0.05mm;
s13, mounting a rotor to be tested; fixing the first support and the second support after aligning on a test platform, wherein each support does not move any more in the processes of mounting the tested rotor and repeating the test, and the stability and the accuracy of the test are ensured;
S14, checking lubrication and oil return conditions of the bearing 15, and checking flexibility of a rotor by a manual jigger;
S15, checking the machining, assembling and mounting quality of the rotor, and measuring the radial runout of the rotor at the relevant axial position by using a dial indicator under the static state;
S16, installing a measuring module and connecting the measuring module with a test; the measuring module comprises various measuring components and parts, completes the installation of a measuring sensor (comprising a vibration displacement sensor and a vibration acceleration sensor), and completes the connection and debugging of the measuring sensor, a strain gauge, a temperature sensor and a measuring instrument (a data acquisition system); referring to fig. 10, wherein "∈" represents a vertical direction and "=" represents a horizontal direction; a1 to A4 are acceleration sensors for measuring the vertical acceleration of the first support, the horizontal acceleration of the first support, the vertical acceleration of the second support and the horizontal acceleration of the second support, D1 and D2 are vibration displacement sensors for measuring the vibration displacement of the rotor, S1 to S4 are strain gauges for measuring the spring strain of the squirrel cage elastic support 14 in the horizontal direction and the vertical direction, and T1 and T2 are thermocouples for measuring the temperature of the bearing 15.
In an embodiment, step S3 further includes: if the speed is increased to the target rotation speed and exceeds the parameter limit value, stopping the vehicle to analyze the vibration signal, if the parameter limit value is exceeded due to the change of the oil film parameter, screening out the oil film gap or the oil film gap combination, and turning to the step S5, otherwise, re-assembling, installing or aligning, and restarting the driving test after eliminating the overrun factor.
In an embodiment, when the test is started for the first time, any oil film bushing 4 is selected in step S1, the size of the installed oil film bushing 4 is larger or maximum in the range, and the bearing 15 is normally supplied with oil and the oil supply is stopped for the oil film gap in step S2; in the subsequent repeated test process, the relevant parameters obtained in the step S3 are compared with the relevant parameters obtained in the first test to judge the vibration reduction effectiveness of the extrusion oil film, if the data has no deviation or has smaller deviation, the oil film gap is judged to be invalid, the group of oil film gaps are further screened out and removed, the screening range is further narrowed, the oil film gap range can be more rapidly screened through comparison with the test data in the limit state, the test efficiency is greatly improved, the test cost is reduced, and the design of the extrusion oil film damper is effectively guided;
in some embodiments, the oil film gap of each test group can also be used for carrying out driving tests of oil film gap oil supply stopping and normal oil supply under the limit state and carrying out data comparison, so that the range screening result is more accurate and precise.
In an embodiment, the front bearing 15 and the rear bearing 15 may be combined into a test set by adopting the oil film bushings 4 with the same or different oil film gaps, the oil supply pressure of the oil film gaps is adjusted in the optional range in the step S5 based on the oil film gap combination of the test set, test results of different oil supply pressures under the test set are obtained, and after the rest test sets are assembled and disassembled, tests of different oil supply pressures are performed.
It should be understood that in the test method, except for the oil film gap and the oil supply pressure adjustment, the other parts such as the rotor component, the support centering precision and the axial position, the vacuum box pressure, the lubricating oil supply pressure and the like are kept consistent, so that the influence of other influencing factors on the test result is reduced, and the ideal range of the oil film gap of the rotor of the aeroengine is obtained.
It should be noted that, because the lubrication of the bearing 15 and the oil pressure of the extrusion film in the aero-engine are usually supplied simultaneously, the oil pressures of the two are the same, but the lubrication of the bearing 15 only needs to ensure that the bearing 15 is not over-heated, so that under the condition that the lubrication oil supply pressure of the bearing 15 is ensured to be within a normal range, the oil supply pressure range of the extrusion film obtained by the test method can be matched and selected to be more suitable, and the working effect of the extrusion film damper in practical application is improved.
Examples
In this embodiment, based on the above-mentioned rotor test apparatus and test method, with a certain civil vortex shaft engine gas generator rotor as a study object, 7 sets of oil film bushings are designed and processed under the condition of limiting the oil film gap width, and the diameter gaps (2 c/D) are about: 1.0%o, 1.5%o, 2.0%o, 2.5%o, 3.0%o, 4.0%o, 5.0%o, wherein D is the shaft diameter of the oil film bushing mounting position, the oil film gap design and the actual measurement value refer to table 1, and through changing oil film bushings with different gaps, the vibration response test of the rotor of the gas generator in 9 groups of different oil film gap combination states is carried out, and refer to table 2;
TABLE 1 oil film gap (diameter)
Table 2 oil film gap combinations
Referring to fig. 11 to 14, the test researches show rotor deflection, vibration acceleration and spring strain values of the gas generator rotor at rated working rotation speed and bearing temperature rise in the full rotation speed range under different oil film clearance states.
In general, in this embodiment, there is a significant tendency for the rotor deflection and spring strain of the gasifier rotor at rated operating speeds to increase when the oil film gap reaches 4.0% and, in particular, to increase dramatically when the oil film gap reaches 5.0% and the rated operating speeds. The bearing temperature rise is relatively small when the oil film clearance is 2.0 per mill, 2.5 per mill and 3.0 per mill. Through comprehensive analysis, the ideal oil film gap range of the gas generator rotor is (1.0-3.0 mill), which is completely consistent with the oil film gap range of the actual engine gas generator rotor, and the feasibility of the rotor test device and the rotor test method is demonstrated.
According to the embodiment, a certain civil vortex shaft engine gas generator rotor is taken as a research object, systematic experimental research is conducted on a high-speed rotation tester aiming at the influence of different extrusion oil film gaps on the vibration response of the rotor, the change rule of the rotor vibration along with the oil film gaps is revealed, the ideal value range of the oil film gaps of the gas generator rotor is determined, the research result provides a reliable basis for the design of oil film parameters of the extrusion oil film damper of the gas generator rotor, the forward design level of the extrusion oil film damper is improved, the vibration reduction design technology of the high-speed rotor is enriched and developed, and the method has engineering application value.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A rotor test device for performing a vibration response test on a rotor of an aero-engine, the aero-engine rotor comprising a shaft, a bearing (15) and a squirrel cage elastic support (14), characterized in that the rotor test device comprises:
a support structure for supporting;
The switching component is annular, is used for being connected with the supporting structure and used for supporting the bearing (15) so as to further support the rotating shaft, and is provided with a mounting structure (3);
The oil film bushing (4) is annular, the oil film bushing (4) is provided with a matching structure, the mounting structure (3) is used for mounting the oil film bushing (4), and the matching structure of the oil film bushing (4) is used for forming an oil film gap with a preset size with the squirrel cage elastic support (14);
the first oil supply structure is arranged on the switching assembly and connected with a first oil source and is used for supplying oil to the oil film gap; the first oil supply structure comprises an oil inlet circuit (5) and an oil return circuit (6) which are arranged on the switching assembly, an oil inlet hole (8) is formed in the oil film bushing (4), and two ends of the oil inlet hole (8) are respectively communicated with the oil inlet circuit (5) and the matching structure;
The second oil supply structure is arranged on the switching assembly and connected with a second oil source and is used for supplying oil to the bearing (15); the second oil supply structure comprises a nozzle (7) arranged on the switching assembly, and the nozzle (7) is positioned on one side of the bearing (15).
2. The rotor test device according to claim 1, wherein the oil return path (6) is located at a lower portion of the adapter assembly in an installed state so as to return oil based on gravity, and the oil return path (6) is communicated to the bottom of the installation structure (3) and is communicated to the inner wall of the adapter assembly through the bottom of the installation structure (3).
3. The rotor test device according to claim 2, wherein the mounting structure (3) is arranged in the inner cavity of the adapter assembly, the inner wall of the inner cavity is provided with an oil return port (10), or the mounting structure (3) is arranged at one end of the inner cavity of the adapter assembly, and the inner wall of the oil film bushing (4) is provided with an oil return hole (9) close to the outer end of the oil film bushing (4) and used for being communicated to the oil return oil path (6).
4. The rotor test device according to claim 1, characterized in that the outer end of the oil film bushing (4) is provided with a connecting flange (12), connecting holes are uniformly distributed on the connecting flange (12) along the circumferential direction, and threaded holes for matching with the connecting holes are formed on the adapter component.
5. The rotor test device according to claim 1, characterized in that the inner wall of the oil film bushing (4) is provided with sealing grooves (13) for embedding sealing rings at both ends of the mating structure, respectively.
6. The rotor testing device according to any one of claims 1-5, further comprising a testing platform, a power device and a vacuum testing chamber arranged on the testing platform, wherein the support structure comprises a first support and a second support movably arranged in the vacuum testing chamber, the adapter assembly comprises a first adapter seat (1) and a second adapter seat (2) respectively arranged corresponding to the bearing (15), the first support is used for installing the first adapter seat (1), and the second support is used for installing the second adapter seat (2).
7. A rotor testing method, characterized by being applied to the rotor testing device of claim 6, comprising the following:
S1, preparing a test;
s2, adjusting the pressure of the vacuum test chamber and the oil supply pressure;
s3, starting to a parameter limit value or a target rotating speed, and recording related parameters in the speed increasing process;
S4, stopping the vehicle to finish the test;
s5, replacing the oil film bushing and/or changing the oil film gap oil supply pressure, and repeating the steps S2-S4 so as to screen the value range of the oil film gap.
8. The rotor testing method of claim 7, wherein step S1 comprises:
s11, adjusting positions of the first support and the second support;
S12, aligning;
s13, mounting a rotor to be tested;
s14, checking lubrication and oil return conditions of the bearing;
S15, checking the processing, assembling and mounting quality of the rotor;
s16, installing a measuring module and connecting the measuring module with a test.
9. The rotor testing method of claim 8, wherein step S3 further comprises: if the speed is increased to the target rotating speed and exceeds the parameter limit value, stopping the vehicle to analyze the vibration signal, if the parameter limit value is exceeded due to the change of the oil film parameter, turning to the step S5, otherwise, reassembling, installing or aligning, and restarting the driving test after eliminating the overrun factor.
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| CN116164075A (en) * | 2021-11-24 | 2023-05-26 | 中国航发商用航空发动机有限责任公司 | Extrusion oil film damper, planetary reducer and gear drive turbofan engine |
| CN117028820A (en) * | 2023-06-27 | 2023-11-10 | 中国航发湖南动力机械研究所 | Oil distributing device for rotor dynamic characteristic test |
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| CN116202718A (en) * | 2023-02-08 | 2023-06-02 | 中国航发沈阳发动机研究所 | Vibration suppression effect test device for extrusion oil film damper |
| CN118329409A (en) * | 2024-04-09 | 2024-07-12 | 中国航发湖南动力机械研究所 | Bidirectional excitation test device for extrusion oil film damper |
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| CN116164075A (en) * | 2021-11-24 | 2023-05-26 | 中国航发商用航空发动机有限责任公司 | Extrusion oil film damper, planetary reducer and gear drive turbofan engine |
| CN117028820A (en) * | 2023-06-27 | 2023-11-10 | 中国航发湖南动力机械研究所 | Oil distributing device for rotor dynamic characteristic test |
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