CN112504643A - Double-rotor-bearing system test bed with detachable bolt connection structure and method - Google Patents
Double-rotor-bearing system test bed with detachable bolt connection structure and method Download PDFInfo
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- CN112504643A CN112504643A CN202011271831.4A CN202011271831A CN112504643A CN 112504643 A CN112504643 A CN 112504643A CN 202011271831 A CN202011271831 A CN 202011271831A CN 112504643 A CN112504643 A CN 112504643A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention belongs to the technical field of structural design and vibration test of a dual-rotor system of an aircraft engine and discloses a detachable dual-rotor-supporting system test bed and a method of a bolt connection structure. The test bed mainly comprises an electric driving system, a double-rotor-supporting system, a single-rotor-supporting system, a belt transmission system, a sensing test system and a base; the bolt-hub connecting structure in the low-pressure and high-pressure gas compressors of the aero-engine is considered, so that the dynamic real situation of a high-pressure and low-pressure dual-rotor system of the aero-engine can be reflected; the invention can also replace the bolt connecting shaft section in the double-rotor system with the bolt-free connecting shaft section, thereby realizing the experimental research that the high-pressure rotor and the low-pressure rotor are simultaneously provided with the bolt connecting structure and the high-pressure rotor or the low-pressure rotor is independently provided with the bolt connecting structure, and also carrying out the comparison test that the high-pressure rotor and the low-pressure rotor are not provided with the bolt connecting structure without reworking to manufacture the rotor system.
Description
Technical Field
The invention belongs to the technical field of structural design and vibration test of a dual-rotor system of an aircraft engine, and particularly relates to a test bed and a vibration test method for researching the influence of a bolt flange connection structure on the dynamic characteristics of the dual-rotor system.
Background
In aviation flight, the engine is used as power to guarantee, and the reliability of the work of the engine is directly related to flight safety. The rotor system of the aero-engine generally adopts a multi-rotor structure, wherein a double-rotor structure is applied more, and in the actual application process of the multi-rotor structure, the vibration of the double-rotor structure and the failure of a bolt connecting structure are always serious problems faced by the aero-engine.
The bolt connection is widely applied to the structure of the aero-engine by the advantages of simple structure, good connection rigidity, convenient installation, strong operability and the like. Under the working state of high rotating speed and large load, the discontinuous rotor system with the bolt connection structure may cause relative deformation between connection structure parts, so that local rigidity of the rotor system is changed, nonlinear vibration is further caused, unbalance is increased, and great influence is caused on vibration of an engine. However, most of the dual-rotor experimental devices established by various colleges and scientific research institutions do not consider bolt connection structures, and the vibration characteristics of the dual-rotor system are more complicated due to the mutual coupling of high-voltage rotors and low-voltage rotors of the dual-rotor system. Therefore, the rotor system without bolt connection cannot reflect the real dynamic situation of the high-pressure and low-pressure double-rotor systems of the aircraft engine.
At present, a plurality of scholars at home and abroad recognize the important influence of the bolt connection structure on the double rotor system of the aircraft engine and carry out corresponding theoretical research, but no complete theoretical system exists, so that the theory and experimental research for researching the influence of the bolt connection structure on the dynamic characteristics of the double rotor system have important significance aiming at the characteristic that the high and low pressure rotors of the double rotor system of the aircraft engine are mutually coupled. In order to achieve the above objective and to further analyze the influence of the bolt connection structure by combining the structural characteristics of the dual rotor system, it is necessary to study that the high-pressure and low-pressure rotors have the bolt connection structure at the same time, and the high-pressure or low-pressure rotors have the bolt connection structure alone, and the high-pressure and low-pressure rotors do not have the bolt connection structure as a comparison. Therefore, in order to save the test cost, a bolt-on dual-rotor test bed capable of realizing all the above conditions is needed.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a dual-rotor-supporting system test bed with a detachable bolt connection structure and a test method thereof. In structural aspect, the invention is a simplified model of an aircraft engine dual-rotor system, and a bolt connecting structure is designed as a bolt-hub connecting structure in the aircraft engine rotor system; meanwhile, the bolt connecting structure is designed to be a detachable shaft section, the bolt connecting structures in the high-pressure rotor and the low-pressure rotor are replaced by the bolt-free connecting structures respectively to realize contrast tests of various conditions, so that test research on the situation that the high-pressure rotor and the low-pressure rotor are provided with the bolt connecting structures simultaneously, the high-pressure rotor or the low-pressure rotor is provided with the bolt connecting structures independently can be carried out, the contrast tests that the high-pressure rotor and the low-pressure rotor are not provided with the bolt connecting structures are not required, a manufacturing test bench is not required to be processed again, and the test cost is. On the basis, the number of bolts and the installation pretightening force of each bolt connection structure are further changed, and the influence of bolt connection on the double-rotor system under different working conditions and different bolt connection parameters is researched; the invention not only can satisfy the static inherent characteristics and bolt pretightening force test of the high-pressure rotor of the aero-engine, but also can satisfy the dynamic vibration test of the high-pressure rotor of the aero-engine.
In order to achieve the purpose, the invention adopts the following technical scheme:
the dual-rotor-supporting system test bed with the detachable bolt connection structure comprises an electric driving system, a dual-rotor-supporting system, a single-rotor-supporting system, a belt transmission system, a sensing test system and a base; the electric driving system comprises an electric control box arranged on the ground through an electric box support, and a first rotor variable frequency motor and a second rotor variable frequency motor which are controlled by the electric control box; a first rotor variable frequency motor control system and a second rotor variable frequency motor control system are arranged in the electric control box and comprise a frequency converter, a control panel, a contactor and a circuit breaker, and the frequency converter is used for adjusting the rotating speed of the variable frequency motor; the first rotor variable frequency motor and the second rotor variable frequency motor are respectively fixed on the first motor support and the second motor support, and torque is transmitted to the single rotor-supporting system and the double rotor-supporting system through the first flexible coupling and the second flexible coupling;
the dual rotor-bearing system comprises a low pressure rotor system, a high pressure rotor system and an intermediate bearing; the low-pressure rotor system and the high-pressure rotor system are assembled together through an intermediate bearing; the high-pressure rotor system is of a hollow structure, and the low-pressure rotor system is arranged in the high-pressure rotor system in a penetrating mode; the low-pressure rotor system comprises a first low-pressure shaft, a fourth double-rotor bearing and bearing seat, a bolt connecting shaft section A, a second low-pressure shaft, a third double-rotor bearing and bearing seat, a low-pressure disc and a first double-rotor bearing and bearing seat which are connected in sequence; the high-pressure rotor system comprises a first high-pressure shaft, a second double-rotor bearing and bearing block, a bolt connecting shaft section B, a second high-pressure shaft and a high-pressure plate which are connected in sequence; the bolt is connected with the shaft sections A and B and is respectively arranged in the low-pressure rotor system and the high-pressure rotor system through parallel keys; the bolt connecting shaft sections A and B respectively comprise a shaft with a flange edge, an optical axis and a rotary table, and the rotary table is fixed on the optical axis through a Z1 type expansion sleeve and an expansion sleeve end cover and is connected with the flange edge through bolts;
the single rotor-supporting system comprises a single rotor shaft, a first single rotor bearing and bearing seat and a second single rotor bearing and bearing seat and is used for providing power for a high-pressure rotor system in the double-rotor-supporting system;
the belt transmission system comprises a transmission belt, a driving belt wheel and a driven belt wheel; the driving belt wheel and the driven belt wheel are respectively fixed on the rotor shaft and the second high-pressure shaft through a Z1 type expansion sleeve; the driving pulley transmits torque from the single rotor-bearing system to the high-pressure rotor system of the double rotor-bearing system through a transmission belt;
the test sensing system comprises a sensor bracket fixed on the base, an eddy current displacement sensor fixed on the sensor bracket, a force sensor, an acceleration sensor, a modal force hammer, vibration test software, a force sensor signal acquisition card, an eddy current sensor signal acquisition card and LMS (least mean square) test equipment, and is used for exciting a rotor or acquiring vibration signals; the sensor support and the eddy current displacement sensor are divided into two groups which are respectively used for testing vibration signals of the low-voltage rotor system and the high-voltage rotor system; the acceleration sensor is adhered to the low-pressure shaft, the high-pressure shaft and the connecting shaft section; the LMS vibration test system is used for testing the inherent characteristics of the rotor system, such as vibration mode, inherent frequency and the like; the force sensor and the eddy current sensor are used for acquiring data, are respectively connected with the force sensor and the eddy current sensor and transmit the data to the computer.
The bolt connecting shaft section can be detached and replaced by a bolt-free connecting shaft section A or a bolt-free connecting shaft section B for a comparison test, and only the shaft section is replaced, so that the test cost is saved. The non-bolt connecting shaft section comprises an optical axis and a rotary table, wherein the size and the hole site of the disc in the non-connecting shaft section are the same as those of the disc in the non-connecting shaft section after being connected with the flange, the disc is still fixed on the shaft through a Z1 type expansion sleeve, the rationality of a contrast test is ensured, and the difference lies in that the disc in the non-connecting shaft section is processed into a whole.
Further, the dual-rotor supporting system realizes a bolted dual-rotor experiment under multiple working conditions by replacing the bolted connecting shaft section with a non-bolted connecting shaft section; the multiple working conditions are as follows: the high-pressure rotor system and the low-pressure rotor system are both provided with bolt connecting shaft sections, and the bolt connecting shaft sections of the low-pressure rotor system or the high-pressure rotor system are replaced by bolt-free connecting shaft sections, so that the influence of the bolt connecting structure of the high-pressure rotor system and the low-pressure rotor system and the influence of the bolt connecting structure of the high-pressure rotor system or the low-pressure rotor system on the dynamic characteristics of the double-rotor system can be respectively researched; and the bolt connection shaft sections of the high-pressure rotor system and the low-pressure rotor system are completely replaced by the bolt-free connection shaft sections, so that a contrast test can be carried out, and the influence of a bolt connection structure is further analyzed.
Further, the dual-rotor-bearing system simulates a dual-rotor system of an aircraft engine, wherein a bolt connecting shaft section A in the low-pressure rotor system simulates a low-pressure compressor part; a bolt connecting shaft section B in the high-pressure rotor system simulates a high-pressure compressor part; the low pressure disc and the high pressure disc respectively simulate a low pressure turbine part and a high pressure turbine part; the bolt-flange connection mode of the bolt connection shaft section simulates the bolt-hub connection mode in the high-pressure and low-pressure gas compressors of the aircraft engine.
The base is provided with a plurality of foundation bolts for fixing the motor support, the bearing seat and the eddy current sensor bracket, and the bottom of the base is provided with six rubber foot pads;
the force sensors are arranged between the nut and the disc;
the LMS vibration testing equipment is used for testing the inherent characteristics of the rotor system, such as the vibration mode, the inherent frequency and the like;
the signal converter and the signal acquisition card are used for acquiring data, are respectively connected with the force sensor and the eddy current sensor and transmit the data to the computer;
the vibration testing software comprises three pieces, namely LabVIEW self-writing software based on graphical programming language, LMS testing software and bolt pre-tightening force testing software. LabVIEW self-writing software mainly tests vibration displacement, acceleration and strain; the LMS test software mainly tests the vibration mode and the inherent frequency of the rotor in the test of the test bed; the bolt pretightening force test software is used for testing and recording the pretightening force of bolt connection;
the acquisition card case is an NIC-DAQ 9188 acquisition card case and is used for connecting LabVIEW test software and the acquisition card.
The model of the modal force hammer is L-YD-312A, and one end of the modal force hammer is connected with LMS vibration testing equipment.
A test method of a double-rotor-supporting system test bed with a detachable bolt connection structure is used for testing inherent characteristics, pretightening force and dynamic characteristics of a double-rotor system with the bolt connection structure, and comprises the following steps:
1) static vibration test of bolt connection birotor system test bed
A plurality of groups of acceleration sensors are adsorbed on a high-pressure shaft, a low-pressure shaft and a bolt connecting shaft section of the double-rotor supporting system at equal intervals, and the other ends of the acceleration sensors are connected with an LMS (least mean square) testing system; knocking is carried out by using a modal force hammer in the direction opposite to the acceleration sensor, the knocking is transmitted to a computer through a data line, and data acquisition and processing are carried out by using an LMS (least mean square) test system, so that inherent characteristic test results of the dual-rotor system, including the vibration mode and the inherent frequency, are obtained; replacing the bolt connecting shaft section in the high-pressure or low-pressure rotor system with a bolt-free connecting shaft section respectively, and arranging acceleration sensors at the same positions to perform two tests in the same way to obtain the inherent characteristic test result of the double-rotor system with the high-pressure or low-pressure rotor independently provided with the bolt connecting structure; finally, replacing all the bolt connecting shaft sections of the high-pressure and low-pressure rotor systems with bolt-free connecting shaft sections to obtain the inherent characteristic test result of the double-rotor system of the bolt-free connecting structure; comparing four groups of test data to analyze the influence of the bolt flange connection structure on the inherent characteristics of the double-rotor system;
2) static pretightening force test of bolt connection dual-rotor system test bed
Completely loosening bolts of the bolt connecting shaft section, placing the force sensor between the nut and the disc, and connecting the other end of the force sensor with the acquisition card; tightening the nut to record the pre-tightening force data; sequentially tightening the other bolts on the disc, recording the pretightening force change condition of the bolt connection in the tightening process, and analyzing to obtain the elastic interaction between the bolts; by changing the pre-tightening force of the bolts, the tightening sequence of the bolts, the number of the bolts, the models of the bolts, and the gap parameters between the bolts and the screw holes, the test process is repeated, and the influence rule of each parameter and different combination parameters on the elastic interaction between the bolts is researched.
3) Dynamic vibration characteristic test of bolt connection dual-rotor system test bed
Arranging a plurality of groups of eddy current displacement sensors in the horizontal and vertical directions of a high-pressure shaft, a low-pressure shaft and a bolt connecting shaft section of the double-rotor supporting system through sensor supports; respectively starting a first variable frequency motor and a second variable frequency motor, setting the rotating speed of the variable frequency motors, continuously acquiring data by an eddy current displacement sensor and transmitting the acquired data to a computer in the rotating process of a rotor system, and processing the acquired data by the computer to finally obtain the axial center track, time domain response, frequency domain response and dynamic vibration characteristics of a bifurcation diagram of the rotor system; replacing a bolt connecting shaft section in a high-pressure rotor system or a low-pressure rotor system with a bolt-free connecting shaft section, and arranging sensors at the same positions for testing to obtain the dynamic vibration characteristics of an axis track, time domain response, frequency domain response and a bifurcation diagram of the model rotor system; finally, replacing all the bolt connecting shaft sections of the high-pressure rotor system and the low-pressure rotor system with bolt-free connecting shaft sections to obtain the axle center track, time domain response, frequency domain response and branch diagram dynamic vibration characteristics of the double-rotor system of the bolt-free connecting structure; and comparing the dynamic vibration responses of the four conditions, and analyzing to obtain the influence of the high-pressure rotor and the low-pressure rotor which are simultaneously provided with the bolt connecting structure and the high-pressure rotor system or the low-pressure rotor system which is independently provided with the bolt connecting structure on the double-rotor system.
The invention has the beneficial effects that:
compared with the existing test bed of the double-rotor system, the test bed of the invention considers the bolt-hub connection structure in the low-pressure and high-pressure air compressors of the aero-engine, and can reflect the real dynamic situation of the high-pressure and low-pressure double-rotor systems of the aero-engine; the bolt connecting shaft section in the double-rotor system can be replaced by the bolt-free connecting shaft section, so that the experimental research that the high-pressure rotor and the low-pressure rotor are provided with the bolt connecting structure simultaneously and the high-pressure rotor or the low-pressure rotor is provided with the bolt connecting structure independently is realized, the comparison test that the high-pressure rotor and the low-pressure rotor are not provided with the bolt connecting structure can be carried out, and the rotor system does not need to be machined and manufactured again; on the basis, the number of bolts of each bolt connecting shaft section and the installation pretightening force are further changed, and the influence of the bolt connecting structure on the inherent characteristics and the vibration characteristics of the aircraft engine double-rotor system under different working conditions and different bolt connecting parameters is conveniently obtained.
Drawings
FIG. 1 is a system configuration of a laboratory bench according to the present invention;
FIG. 2 is a schematic structural view of a detachable dual-rotor system test bed of the bolt connection structure of the present invention;
FIG. 3 is a schematic structural view of the dual rotor-bearing system of the present invention with both high and low pressure rotors having bolted shaft segments;
FIG. 4 is a schematic structural view of a dual rotor-bearing system of the present invention with bolted shaft segments for high pressure rotors;
FIG. 5 is a schematic view of a dual rotor-bearing system of the present invention with bolted shaft segments for low pressure rotors
FIG. 6 is a schematic structural view of the dual rotor-bearing system of the present invention with both the high and low pressure rotors replaced with non-bolted shaft sections;
FIG. 7 is a schematic view of a single rotor-bearing system of the present invention
FIG. 8 is a schematic structural view of a bolted shaft segment of the present invention;
FIG. 9 is a schematic structural view of a boltless connecting shaft segment in accordance with the present invention;
FIG. 10 is a schematic view of a flexible coupling construction of the present invention;
FIG. 11 is a schematic view of a sensor holder configuration of the present invention;
in the figure: 1, an electric control box; 2, a first rotor variable frequency motor; a first motor support; a flexible coupling No. 4; 5 a single rotor shaft; no. 6 single rotor bearing and bearing seat; 7, a transmission belt; 8, a driving belt wheel; 9, a second single-rotor bearing and a bearing seat; 10 a base; 11 a rubber foot pad; 12, a first double-rotor bearing and a bearing seat; 13 a low pressure plate; 14 high pressure disks; 15 a driven pulley; a number 16 first eddy current sensor; 17, a first eddy current sensor bracket; 18, a second double-rotor bearing and a bearing seat; 19, a third double-rotor bearing and a bearing seat; 20 force sensors; no. 21 four double-rotor bearing and bearing seat; a No. 22 second flexible coupling; 23, a second motor support; 24 a second rotor variable frequency motor; a low pressure shaft 25; 26 parallel bonds; 27 bolt connecting shaft section A; a number 28 second low pressure shaft; 29 high pressure shaft; the shaft section B is connected with a bolt 30; 31 intermediate bearings; a number 32 high pressure shaft; 33 expanding the end cover of the sleeve; 34Z1 type expansion sleeve; 35 no connecting shaft section a; 36 without connecting shaft segment B.
Detailed Description
The following further describes a specific embodiment of the present invention with reference to the drawings and technical solutions.
As shown in fig. 1 and 2, a dual-rotor-support system test bed with a detachable bolt connection structure mainly comprises an electric drive system, a dual-rotor-support system, a single-rotor-support system, a belt drive system, a sensing test system and a base 10; the electric driving system comprises an electric control box 1 arranged on the ground through an electric box support, and a first rotor variable frequency motor 2 and a second rotor variable frequency motor 24 which are controlled by the electric control box; the first rotor variable frequency motor and the second rotor variable frequency motor are respectively fixed on the first motor support 3 and the second motor support 23, and transmit torque to the single rotor-supporting system and the double rotor-supporting system through the first flexible coupling 4 and the second flexible coupling 22, as shown in fig. 10;
the dual rotor-bearing system, including a low pressure rotor system, a high pressure rotor system, and an intermediate bearing 31; the low-pressure rotor system and the high-pressure rotor system are assembled together through an intermediate bearing 31; the high-pressure rotor system is of a hollow structure, and the low-pressure rotor system is arranged in the high-pressure rotor system in a penetrating mode;
the low-pressure rotor system comprises a first low-pressure shaft 25, a fourth double-rotor bearing and bearing seat 21, a bolt connecting shaft section A27, a second low-pressure shaft 28, a third double-rotor bearing and bearing seat 19, a low-pressure disc 13 and a first double-rotor bearing and bearing seat 12 which are connected in sequence; the high-pressure rotor system comprises a first high-pressure shaft 29, a second double-rotor bearing and bearing seat 18, a bolt connecting shaft section B30, a second high-pressure shaft 32 and a high-pressure plate 14 which are connected in sequence; wherein the bolt is connected with the shaft sections A and B and is respectively arranged in the low-pressure rotor system and the high-pressure rotor system through a parallel key 26; the bolt connecting shaft sections A and B respectively comprise a shaft with a flange edge, an optical axis and a rotary table, and the rotary table is fixed on the optical axis through a Z1 type expansion sleeve 34 and an expansion sleeve end cover 33 and is connected with the flange edge through bolts;
the bolt connecting shaft section can be detached and can be replaced by a bolt-free connecting shaft section A35 or a bolt-free connecting shaft section B36 for a comparison test, and the test cost is saved because only the shaft section is replaced. The non-bolt connecting shaft section comprises an optical axis and a rotary table, wherein the size and the hole site of a disc in the non-connecting shaft section are the same as those of the disc in the bolt connecting shaft section after being connected with a flange, and the disc is still fixed on the shaft through a Z1 type expansion sleeve, so that the reasonability of a comparison test is ensured, and the difference lies in that the disc in the non-connecting shaft section is processed into a whole.
The dual-rotor-supporting system realizes a multi-condition bolt connection dual-rotor experiment by replacing a bolt connection shaft section with a non-bolt connection shaft section; the multiplex condition, its characterized in that: the high-pressure rotor system and the low-pressure rotor system are both provided with bolt connecting shaft sections, and the bolt connecting shaft sections of the low-pressure rotor system or the high-pressure rotor system are replaced by bolt-free connecting shaft sections, so that the influence of the bolt connecting structure of the high-pressure rotor system and the low-pressure rotor system and the influence of the bolt connecting structure of the high-pressure rotor system or the low-pressure rotor system on the dynamic characteristics of the double-rotor system can be respectively researched, as shown in fig. 3, 4, 5, 8 and 9; a comparison test can be performed by replacing all the bolted shaft sections of the high-and low-pressure rotor systems with the non-bolted shaft sections, and the influence of the bolted structure is further analyzed, as shown in fig. 6, 8 and 9.
As shown in fig. 7, the single rotor system includes a single rotor shaft 5, a single rotor bearing and bearing seat No. one 6 and a single rotor bearing and bearing seat No. two 9, which are used for providing power for the high-pressure rotor system in the dual rotor-support system;
the belt transmission system comprises a transmission belt 7, a driving belt wheel 8 and a driven belt wheel 15; the driving belt wheel and the driven belt wheel are respectively fixed on the rotor shaft 5 and the second high-pressure shaft 32 through a Z1 type expansion sleeve 34; the driving belt wheel transmits torque from the single rotor system to a high-pressure rotor system of the double-rotor system through a driving belt;
a plurality of foundation bolts are arranged on the base 10 and used for fixing a motor support, a bearing seat and an eddy current sensor support 17, and six rubber foot pads 11 are arranged at the bottom of the base;
the test sensing system comprises a sensor bracket 17 fixed on the base, as shown in fig. 11, an eddy current displacement sensor 16 fixed on the sensor bracket, a force sensor 20, an acceleration sensor, a modal force hammer, vibration test software, a signal converter, a signal acquisition card, an acquisition card case and LMS vibration test equipment, and is used for exciting a rotor or acquiring vibration signals; the sensor support and the eddy current displacement sensor are divided into two groups which are respectively used for testing vibration signals of the low-voltage rotor system and the high-voltage rotor system; the plurality of acceleration sensors are adhered to the low-pressure shaft, the high-pressure shaft and the connecting shaft section; the force sensors are arranged between the nut and the disc; the LMS vibration testing equipment is used for testing the intrinsic characteristics of the rotor system, such as vibration mode, natural frequency and the like; the signal converter and the signal acquisition card are used for acquiring data, are respectively connected with the force sensor 20 and the eddy current sensor 16, and transmit the data to the computer;
the method for testing the static and dynamic characteristics of the system after early preparation is made is used for testing the influence of the inherent characteristics, pretightening force and dynamic characteristics of the dual-rotor system of the bolted flange connection structure, and comprises the following steps:
1) static vibration test of bolt connection birotor system test bed
A plurality of groups of acceleration sensors are adsorbed on a high-pressure shaft, a low-pressure shaft and a bolt connecting shaft section of the double-rotor supporting system at equal intervals, and the other ends of the acceleration sensors are connected with an LMS (least mean square) testing system; knocking is carried out by using a modal force hammer in the direction opposite to the acceleration sensor, the knocking is transmitted to a computer through a data line, and data acquisition and processing are carried out by using an LMS (least mean square) test system, so that inherent characteristic test results of the dual-rotor system, including the vibration mode and the inherent frequency, are obtained; replacing the bolt connecting shaft section in the high-pressure or low-pressure rotor system with a bolt-free connecting shaft section respectively, and arranging acceleration sensors at the same positions to perform two tests in the same way to obtain the inherent characteristic test result of the double-rotor system with the high-pressure or low-pressure rotor independently provided with the bolt connecting structure; finally, replacing all the bolt connecting shaft sections of the high-pressure and low-pressure rotor systems with bolt-free connecting shaft sections to obtain the inherent characteristic test result of the double-rotor system of the bolt-free connecting structure; comparing four groups of test data to analyze the influence of the bolt connection structure on the inherent characteristics of the dual-rotor system;
2) static pretightening force test of bolt connection dual-rotor system test bed
Completely loosening bolts of the bolt connecting shaft section, placing the force sensor between the nut and the disc, and connecting the other end of the force sensor with the acquisition card; tightening the nut to record the pre-tightening force data; sequentially tightening the other bolts on the disc, recording the pretightening force change condition of the bolt connection in the tightening process, and analyzing to obtain the elastic interaction between the bolts; by changing the pre-tightening force of the bolts, the tightening sequence of the bolts, the number of the bolts, the models of the bolts, and the gap parameters between the bolts and the screw holes, the test process is repeated, and the influence rule of each parameter and different combination parameters on the elastic interaction between the bolts is researched.
3) Dynamic vibration characteristic test of bolt connection dual-rotor system test bed
Arranging a plurality of groups of eddy current displacement sensors in the horizontal and vertical directions of a high-pressure shaft, a low-pressure shaft and a bolt connecting shaft section of the double-rotor supporting system through sensor supports; respectively starting a first variable frequency motor and a second variable frequency motor, setting the rotating speed of the variable frequency motors, continuously acquiring data by an eddy current displacement sensor and transmitting the acquired data to a computer in the rotating process of a rotor system, and processing the acquired data by the computer to finally obtain the axial center track, time domain response, frequency domain response and dynamic vibration characteristics of a bifurcation diagram of the rotor system; replacing a bolt connecting shaft section in a high-pressure rotor system or a low-pressure rotor system with a bolt-free connecting shaft section, and arranging sensors at the same positions for testing to obtain the dynamic vibration characteristics of an axis track, time domain response, frequency domain response and a bifurcation diagram of the model rotor system; finally, replacing all the bolt connecting shaft sections of the high-pressure rotor system and the low-pressure rotor system with bolt-free connecting shaft sections to obtain the axle center track, time domain response, frequency domain response and branch diagram dynamic vibration characteristics of the double-rotor system of the bolt-free connecting structure; and comparing the dynamic vibration responses of the four conditions, and analyzing to obtain the influence of the high-pressure rotor and the low-pressure rotor which are simultaneously provided with the bolt connecting structure and the high-pressure rotor system or the low-pressure rotor system which is independently provided with the bolt connecting structure on the double-rotor system.
Based on the test method, the invention mainly aims at researching the structural characteristics of the double-rotor system of the aircraft engine, the change of the characteristics of the double-rotor-supporting system of the bolt connection structure under different connection conditions and different connection parameters is illustrated as follows:
the main test condition changes are as follows: the bolt connecting shaft section can be detached and can be replaced by a bolt-free connecting shaft section, so that a test study that the high-pressure rotor and the low-pressure rotor are provided with bolt connecting structures simultaneously, as shown in fig. 3, and the high-pressure rotor or the low-pressure rotor is provided with the bolt connecting structures independently, as shown in fig. 4 and 5, can be carried out, and a comparison test study that the high-pressure rotor and the low-pressure rotor are not provided with the bolt connecting structures can also be carried out, as shown in fig. 6; meanwhile, the number of bolts of each bolt connection shaft section and the installation pretightening force can be further changed, and the influence of the bolt connection structure on the inherent characteristics and the vibration characteristics of the double-rotor system of the aircraft engine under different working conditions and different bolt connection parameters is obtained.
On the basis, the bolt tightening sequence such as a sequential tightening mode, a diagonal tightening mode and a combined tightening mode combining the sequential tightening mode and the diagonal tightening mode can be changed, and the influence of different tightening modes and tightening torque on the pre-tightening force of other bolts and the inherent characteristic and the dynamic characteristic of a rotor system can be researched.
Claims (4)
1. The dual-rotor-supporting system test bed with the detachable bolt connection structure is characterized by comprising an electric driving system, a dual-rotor-supporting system, a single-rotor-supporting system, a belt transmission system, a sensing test system and a base (10); the electric driving system comprises an electric control box (1) arranged on the ground through an electric box support, and a first rotor variable frequency motor (2) and a second rotor variable frequency motor (24) controlled by the electric control box; a first rotor variable frequency motor control system and a second rotor variable frequency motor control system are arranged in the electric control box and comprise a frequency converter, a control panel, a contactor and a circuit breaker, and the frequency converter is used for adjusting the rotating speed of the variable frequency motor; the first rotor variable frequency motor and the second rotor variable frequency motor are respectively fixed on a first motor support (3) and a second motor support (23), and torque is transmitted to the single rotor-supporting system and the double rotor-supporting system through a first flexible coupling (4) and a second flexible coupling (22);
the double rotor-bearing system comprises a low-pressure rotor system, a high-pressure rotor system and an intermediate bearing (31); the low-pressure rotor system and the high-pressure rotor system are assembled together through an intermediate bearing (31); the high-pressure rotor system is of a hollow structure, and the low-pressure rotor system is arranged in the high-pressure rotor system in a penetrating mode; the low-pressure rotor system comprises a first low-pressure shaft (25), a fourth double-rotor bearing and bearing seat (21), a bolt connecting shaft section A (27), a second low-pressure shaft (28), a third double-rotor bearing and bearing seat (19), a low-pressure disc (13) and a first double-rotor bearing and bearing seat (12) which are connected in sequence; the high-pressure rotor system comprises a first high-pressure shaft (29), a second double-rotor bearing and bearing seat (18), a bolt connecting shaft section B (30), a second high-pressure shaft (32) and a high-pressure plate (14) which are connected in sequence; wherein the bolt is connected with the shaft sections A and B and is respectively arranged in the low-pressure rotor system and the high-pressure rotor system through parallel keys (26); the bolt connecting shaft sections A and B respectively comprise a shaft with a flange edge, an optical axis and a rotary table, and the rotary table is fixed on the optical axis through a Z1 type expansion sleeve (34) and an expansion sleeve end cover (33) and is connected with the flange edge through bolts;
the single rotor-supporting system comprises a single rotor shaft (5), a first single rotor bearing and bearing seat (6) and a second single rotor bearing and bearing seat (9) and is used for providing power for a high-pressure rotor system in the double-rotor-supporting system;
the belt transmission system comprises a transmission belt (7), a driving belt wheel (8) and a driven belt wheel (15); the driving belt wheel and the driven belt wheel are respectively fixed on the rotor shaft (5) and the second high-pressure shaft (32) through a Z1 type expansion sleeve (34); the driving pulley transmits torque from the single rotor-bearing system to the high-pressure rotor system of the double rotor-bearing system through a transmission belt;
the test sensing system comprises a sensor support (17) fixed on the base, an eddy current displacement sensor (16) fixed on the sensor support, a force sensor (20), an acceleration sensor, a modal force hammer, vibration test software, a force sensor signal acquisition card, an eddy current sensor signal acquisition card and LMS (least mean square) test equipment, and is used for exciting a rotor or acquiring vibration signals; the sensor support and the eddy current displacement sensor are divided into two groups which are respectively used for testing vibration signals of the low-voltage rotor system and the high-voltage rotor system; the acceleration sensor is adhered to the low-pressure shaft, the high-pressure shaft and the connecting shaft section; the LMS vibration test system is used for testing the intrinsic characteristics of the rotor system, such as vibration mode, natural frequency and the like; the force sensor and the eddy current sensor signal acquisition card are used for acquiring data, are respectively connected with the force sensor (20) and the eddy current sensor (16), and transmit the data to a computer.
2. The dual rotor-bearing system test stand with a detachable bolt connection structure according to claim 1, wherein: the bolt connecting shaft section is detachable and can be replaced by a bolt-free connecting shaft section A (35) or a bolt-free connecting shaft section B (36) for a comparison test; the non-bolt connecting shaft section comprises an optical axis and a rotary table, wherein the size and the hole site of the disc in the non-connecting shaft section are the same as those of the disc in the non-connecting shaft section after being connected with the flange, the disc is still fixed on the shaft through a Z1 type expansion sleeve, the rationality of a contrast test is ensured, and the difference lies in that the disc in the non-connecting shaft section is processed into a whole.
3. The dual rotor-bearing system test stand with a detachable bolt connection structure according to claim 1, wherein: the dual rotor-bearing system simulates a dual rotor system of an aircraft engine, wherein a bolted connecting shaft section A (27) in the low pressure rotor system simulates a low pressure compressor part; a bolt connecting shaft section B (30) in the high-pressure rotor system simulates a high-pressure compressor part; the low pressure plate (13) and the high pressure plate (14) respectively simulate a low pressure turbine part and a high pressure turbine part; the bolt-flange connection mode of the bolt connection shaft section simulates the bolt-hub connection mode in the high-pressure and low-pressure gas compressors of the aircraft engine.
4. A test method using a dual rotor-bearing system test stand with a detachable bolt joint structure according to any one of claims 1 to 3, comprising the following tests:
1) the static vibration test of the birotor-bearing system test bed with a detachable bolt connecting structure;
a plurality of groups of acceleration sensors are adsorbed on a high-pressure shaft, a low-pressure shaft and a bolt connecting shaft section of the double-rotor supporting system at equal intervals, and the other ends of the acceleration sensors are connected with an LMS (least mean square) testing system; knocking is carried out by using a modal force hammer in the direction opposite to the acceleration sensor, the knocking is transmitted to a computer through a data line, and data acquisition and processing are carried out by using an LMS (least mean square) test system, so that inherent characteristic test results of the dual-rotor system, including the vibration mode and the inherent frequency, are obtained; replacing the bolt connecting shaft section in the high-pressure or low-pressure rotor system with a bolt-free connecting shaft section respectively, and arranging acceleration sensors at the same positions to perform two tests in the same way to obtain the inherent characteristic test result of the double-rotor system with the high-pressure or low-pressure rotor having a bolt connecting structure independently; finally, replacing all bolt connecting shaft sections of the high-pressure rotor system and the low-pressure rotor system with bolt-free connecting shaft sections to obtain the inherent characteristic test result of the double-rotor system with the bolt-free connecting structure; comparing four groups of test data to analyze the influence of the bolt connection structure on the inherent characteristics of the dual-rotor system;
2) the method comprises the following steps of (1) testing the static pre-tightening force of a dual-rotor-supporting system test bed with a detachable bolt connection structure;
completely loosening bolts of the bolt connecting shaft section, placing the force sensor between the nut and the disc, and connecting the other end of the force sensor with the acquisition card; tightening the nut to record the pre-tightening force data; sequentially tightening the other bolts on the disc, recording the pretightening force change condition of the bolt connection in the tightening process, and analyzing to obtain the elastic interaction between the bolts; by changing the bolt pretightening force, the bolt tightening sequence, the number of bolts, the types of the bolts and the parameters of the gap between the bolts and screw holes, repeating the test process, and researching the influence rule of each parameter and different combination parameters on the elastic interaction between the bolts;
3) the dynamic vibration characteristic test of the birotor-bearing system test bed with a detachable bolt connecting structure;
arranging a plurality of groups of eddy current displacement sensors in the horizontal and vertical directions of a high-pressure shaft, a low-pressure shaft and a bolt connecting shaft section of the double-rotor supporting system through sensor supports; respectively starting a first variable frequency motor and a second variable frequency motor, setting the rotating speed of the variable frequency motors, continuously acquiring data by an eddy current displacement sensor and transmitting the acquired data to a computer in the rotating process of a rotor system, and processing the acquired data by the computer to finally obtain the axial center track, time domain response, frequency domain response and dynamic vibration characteristics of a bifurcation diagram of the rotor system; replacing a bolt connecting shaft section in a high-pressure rotor system or a low-pressure rotor system with a bolt-free connecting shaft section, and arranging sensors at the same positions for testing to obtain the axial center track, time domain response, frequency domain response and bifurcation diagram dynamic vibration characteristics of the model rotor system; finally, replacing all bolt connecting shaft sections of the high-pressure rotor system and the low-pressure rotor system with bolt-free connecting shaft sections to obtain the axial center track, time domain response, frequency domain response and bifurcation diagram dynamic vibration characteristics of the double-rotor system of the bolt-free connecting structure; comparing dynamic vibration responses of four conditions, and analyzing to obtain the influence of the high-pressure rotor and the low-pressure rotor which are simultaneously provided with the bolt connecting structure and the high-pressure rotor system or the low-pressure rotor system which is independently provided with the bolt connecting structure on the double-rotor system;
on the basis, the number of bolts of each bolt connecting shaft section and the installation pretightening force are further changed, and the rule of the influence of the bolt connecting structure and the parameters thereof on the vibration characteristics of the double-rotor system of the aircraft engine under different working conditions and different bolt connecting parameters is obtained.
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| CN114526705A (en) * | 2022-01-18 | 2022-05-24 | 哈尔滨工业大学 | Method for measuring dynamic non-concentricity of double rotors of aero-engine |
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