CN117268771A - Tandem type bolt connection double-rotor test bed and test method thereof - Google Patents
Tandem type bolt connection double-rotor test bed and test method thereof Download PDFInfo
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- CN117268771A CN117268771A CN202311252646.4A CN202311252646A CN117268771A CN 117268771 A CN117268771 A CN 117268771A CN 202311252646 A CN202311252646 A CN 202311252646A CN 117268771 A CN117268771 A CN 117268771A
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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
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H11/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties
- G01H11/06—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means
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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
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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
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Abstract
The invention provides a tandem type bolt connection double-rotor test bed and a test method thereof. The test bed comprises a T-shaped groove base, a low-pressure driving device, a low-pressure rotor system, a central coupling supporting structure, a high-pressure rotor system and a high-pressure driving device, wherein the low-pressure rotor system comprises a low-pressure turbine disc, the high-pressure rotor system comprises a high-pressure turbine disc, and the T-shaped groove base is used for fixing a double-rotor system and providing stable experimental conditions. According to the invention, the research on the vibration characteristics of the bolted double rotors of the aeroengine can be realized, meanwhile, the strong nonlinear behavior caused by the coupled vibration of the bolted double rotors and the elastic element can be considered, the structural design is more concise and reasonable, the vibration transmissibility is good, the defects of the design and the vibration testing method of the bolted double rotors are overcome, and the related experimental researches such as the influence of the pretightening force of the bolts on the vibration characteristics of the double rotors, the influence of the rigidity of the elastic element on the vibration transmission characteristics, the influence of the position of the low-pressure turbine disk on the vibration transmission characteristics of the system and the like can be carried out.
Description
Technical Field
The invention relates to the technical field of aero-engine dynamic performance experiments and tests, in particular to a tandem type bolt connection double-rotor test bed and a test method thereof.
Background
With the development of modern aeroengines in the directions of high thrust-weight ratio, low fuel efficiency, easy maintenance, compactness and the like, the rotor-case clearance requirement is continuously improved, the rotor is used as a main excitation source for the vibration of the whole aeroengine, the rotor-case rub-impact fault is easily caused by the excessive or abnormal vibration of the rotor, and the flight reliability and safety are directly affected. Therefore, there is an urgent need for research on vibration characteristics of an aircraft engine rotor system and vibration prediction thereof, and intensive research is needed. For the double-rotor system of the aero-engine, the vibration characteristic and abnormal vibration cause of the rotor system are still not clear due to the complexity and the specificity of the structure, the vibration law and vibration influence factors are not clear, and particularly, the double-rotor system which is represented by the bolted double-rotor and comprises a plurality of connecting structures and elastic units has more complicated vibration behaviors due to the existence of time-varying connecting rigidity and coupling vibration of the connecting structures, and the mechanism research of the vibration characteristic of the system is difficult. From the research of mechanism, further improving the design level of the bolted double-rotor system, grasping the system vibration rule and influencing the main vibration factors, reducing the generation of system vibration faults and improving the flight stability are the centers of gravity in the current aeroengine research field. Therefore, the design of the dual-rotor experiment table with the bolt connection and the coupling vibration can be considered has important significance.
The internal structure of the real aero-engine is complex, the working condition is bad, and the existing experimental method and the existing testing means cannot directly measure the vibration data of the internal rotor in consideration of the experimental cost and period. In addition, because the real aero-engine is complex in structure and numerous in vibration influence factors, related experimental study and measured data have numerous limitations, and the influence of the bolt connection structure and the coupling vibration on the vibration characteristics of the system cannot be highlighted; the current numerical simulation technology still has certain limitation, the working condition of the rotor inside the aero-engine cannot be accurately simulated, and the strong nonlinear behavior caused by the bolt connection and the coupling vibration of the elastic element is more difficult to accurately analyze; the existing aero-engine double-rotor test bed generally adopts parallel connection type, most of the test bed is designed into an integral rotor system, but the test bed is limited to the characteristics of parallel connection type design, the internal structure is more complex, the nonlinear behavior is not introduced by considering the connection structure, and the vibration characteristic of the real aero-engine bolted double-rotor cannot be well simulated. Therefore, based on the theory of structural similarity and dynamics similarity, the design of the tandem type bolt connection double-rotor test bed and the test method thereof have innovation and important significance for the research on the vibration mechanism of the bolt connection double-rotor.
Disclosure of Invention
According to the technical problems, the series-connection type bolt connection double-rotor test stand and the test method thereof can be used for researching the vibration characteristics of the bolt connection double-rotor of the aero-engine, and meanwhile, the strong nonlinear behavior caused by the coupling vibration of the bolt connection and the elastic element can be considered. Compared with the existing test bed, the test bed has the advantages that the structural design is simpler and more reasonable, the vibration transmissibility is good, the defects of the design and the vibration testing method of the bolt connection double-rotor test bed are overcome, and related experimental researches such as the influence of the bolt pretightening force on the vibration characteristics of the double-rotor system, the influence of the rigidity of the elastic element on the vibration transmission characteristics, the influence of the position of the low-pressure turbine disk on the vibration transmission characteristics of the system and the like can be carried out.
The invention adopts the following technical means:
a tandem bolted birotor test stand comprising: the device comprises a T-shaped groove base, a low-pressure driving device, a low-pressure rotor system, a central coupling supporting structure, a high-pressure rotor system and a high-pressure driving device, wherein the low-pressure driving device, the low-pressure rotor system, the central coupling supporting structure, the high-pressure rotor system and the high-pressure driving device are transversely and sequentially arranged on the T-shaped groove base; the low pressure rotor system includes a low pressure turbine disk and the high pressure rotor system includes a high pressure turbine disk.
Further, the low-pressure rotor system further comprises a low-pressure bearing seat, a low-pressure turbine shaft and a low-pressure bearing seat support, and the low-pressure driving device comprises a low-pressure driving motor, a low-pressure shaft coupling and a low-pressure driving motor base;
the low-pressure driving motor base is fixed on the T-shaped groove base, the low-pressure driving motor is arranged on the low-pressure driving motor base, the low-pressure shaft coupler is connected to the output end of the low-pressure driving motor, the left end of the low-pressure turbine shaft is connected with the low-pressure shaft coupler, the right end of the low-pressure turbine shaft is connected with the central coupling supporting structure, a low-pressure bearing seat is connected to the left side, close to the low-pressure shaft coupler, of the low-pressure turbine shaft, a bearing arranged in the low-pressure bearing seat is connected with the low-pressure turbine shaft in a matched mode, the low-pressure bearing seat is arranged on the low-pressure bearing seat support, and the low-pressure bearing seat support is fixed on the T-shaped groove base; the low pressure turbine disk is connected to the low pressure turbine shaft and is located between the low pressure bearing housing and the central coupling support structure.
Further, the low-pressure turbine disc is of a disc structure with edges, a plurality of threaded through holes are circumferentially arranged in the center, and the unbalance amount of the low-pressure turbine disc is changed by matching with bolts with different numbers and different weights; the low-pressure turbine disc is fixed on the low-pressure turbine shaft through the Z1 type tensioning sleeve and used for adjusting the position of the low-pressure turbine disc.
Further, the high-pressure rotor system further comprises a high-pressure turbine left shaft with a conical shell, a high-pressure turbine right shaft without the conical shell, a high-pressure bearing seat and a high-pressure bearing seat support, and the high-pressure driving device comprises a high-pressure shaft coupler, a high-pressure driving motor and a high-pressure driving motor base;
the high-voltage driving motor base is fixed on the T-shaped groove base, the high-voltage driving motor is arranged on the high-voltage driving motor base, the high-voltage shaft coupler is connected to the output end of the high-voltage driving motor, the right end of the right shaft of the high-voltage turbine is connected with the high-voltage shaft coupler, and the left end of the right shaft of the high-voltage turbine is connected with the high-voltage turbine disc; the right end of the left shaft of the high-pressure turbine is connected with the high-pressure turbine disc, and the conical shell at the left end is rotationally connected with the central coupling supporting structure; the right side of the high-pressure turbine right shaft, which is close to the high-pressure shaft coupling, is connected with a high-pressure bearing seat, a bearing arranged in the high-pressure bearing seat is connected with the high-pressure turbine right shaft in a matched manner, the high-pressure bearing seat is arranged on a high-pressure bearing seat support, and the high-pressure bearing seat support is fixed on a T-shaped groove base.
Further, the high-pressure turbine disc comprises a high-pressure turbine disc left disc and a high-pressure turbine disc right disc which are connected through a plurality of bolts, and the high-pressure turbine disc left disc and the high-pressure turbine disc right disc are connected through seam allowance interference fit, so that coaxiality is ensured, and meanwhile, the high-pressure turbine disc is consistent with a high-pressure turbine disc structure connected with a real aeroengine through bolts; the center positions of the left disc of the high-pressure turbine disc and the right disc of the high-pressure turbine disc are respectively provided with an annular protrusion and two screw holes, the two annular protrusions are respectively used for being in interference fit with the left shaft of the high-pressure turbine and the right shaft of the high-pressure turbine, and the screw holes are used for further fastening the shafts and the right shaft of the high-pressure turbine disc through bolt connection.
Further, the central coupling support structure comprises a central coupling support structure bearing seat, a central coupling support structure bearing seat support, a high-pressure turbine shaft connecting sleeve, a squirrel cage, an intermediate bearing and a central coupling support bearing, wherein the central coupling support structure bearing seat support is fixed on a T-shaped groove base, the central coupling support structure bearing seat is arranged on the central coupling support structure bearing seat support, the central coupling support bearing is arranged on the central coupling support structure bearing seat, and the high-pressure turbine shaft connecting sleeve is fixed in the central coupling support bearing; the squirrel cage is an elastic element, is inserted into the left side of the high-pressure turbine shaft connecting sleeve and is connected with the high-pressure turbine shaft connecting sleeve to form an elastic supporting structure; the middle bearing is arranged in the mouse cage, and the right end of the low-pressure turbine shaft is connected with the middle bearing in a matching way;
screw holes are formed at two ends of the high-pressure turbine shaft connecting sleeve and are respectively used for being connected with the squirrel cage and the conical shell of the left shaft of the high-pressure turbine, so that the low-pressure rotor and the high-pressure rotor are elastically connected; the high-pressure rotor system and the low-pressure rotor system can work independently based on the existence of the central coupling support bearing and the intermediate bearing.
Further, the squirrel cage is of a cylindrical structure with a hollowed design and is used for transmitting vibration from a low-pressure turbine shaft to a high-pressure rotor and damping the vibration; the high-pressure turbine shaft connecting sleeve is of a stepped cylinder structure; a certain gap is reserved between the squirrel cage and the high-pressure turbine shaft connecting sleeve.
Further, the low-voltage driving motor base, the low-voltage bearing seat support, the central coupling supporting structure bearing seat support, the high-voltage bearing seat support and the high-voltage driving motor base are all fixed on the T-shaped groove base through the special bolts and the locknuts of the T-shaped groove base, the influence on experimental results due to loosening of the bolts caused by vibration in the testing process is avoided, and meanwhile the high-low voltage rotor system is further guaranteed to have higher coaxiality.
The invention also provides a testing method of the tandem type bolt connection double-rotor test stand, which comprises the following steps:
s1, installing two eddy current sensors at the position of a high-pressure rotor, which is close to a high-pressure turbine disc connected with a bolt, and respectively measuring vibration response signals of the rotor in the horizontal direction and the vertical direction in real time; the method comprises the steps of sequentially connecting an eddy current sensor with an eddy current pre-processor and a signal conditioner, and finally connecting the eddy current sensor to a workstation through a data acquisition system to correspondingly process and display measured data; setting a specified sampling frequency and sampling points in a data acquisition system;
s2, applying the same pretightening force to each bolt of the bolted high-pressure turbine disk by using a fixed torque wrench, wherein the tightening mode adopts a diagonal tightening mode so as to ensure that the high-pressure rotor has proper coaxiality; the rotating speeds of the high-low pressure rotors are regulated through a frequency converter, vibration signals at all the rotating speeds are measured in sequence, an amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotors are analyzed; changing the pretightening force of the bolt connected high-pressure turbine disk, sequentially measuring vibration signals at each rotating speed, and analyzing the influence of the pretightening force of the bolt on the vibration characteristics of the double-rotor system by comparing and analyzing the amplitude-frequency characteristic curve, the waterfall diagram and the time domain response under different pretightening forces;
s3, using a fixed torque wrench to apply the same pretightening force to each bolt of the bolted high-pressure turbine disk in a diagonal tightening mode, so as to ensure a stable assembly state; three different thickness squirrel cages are selected for changing the rigidity of the elastic element; the rotating speed of the high-low pressure rotor is regulated by a frequency converter, vibration signals of a double-rotor system with squirrel-cages with different thicknesses in a safe rotating speed interval are sequentially measured, and a frequency amplitude characteristic curve, a waterfall diagram and a time domain response are drawn; analyzing the law of the evolution of the vibration transmission characteristics of the bolted double-rotor system with different elastic element rigidities to analyze the law of the influence on the inherent frequency, the vibration characteristics and the motion state of the double-rotor system;
s4, using a fixed torque wrench to apply the same pretightening force to each bolt of the bolted high-pressure turbine disk in a diagonal tightening mode, so as to ensure a stable assembly state; the rotating speeds of the high-low pressure rotors are regulated through a frequency converter, vibration signals at all the rotating speeds are measured in sequence, an amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotors are analyzed; changing the position of the low-pressure turbine disc on the low-pressure turbine shaft, sequentially measuring vibration signals at each rotating speed, and analyzing the influence rules of the low-pressure turbine disc position on the vibration characteristics and the vibration transfer characteristics of the double-rotor system by comparing and analyzing amplitude-frequency characteristic curves, waterfall diagrams and time domain responses at different low-pressure turbine disc positions;
s5, using a fixed torque wrench to apply the same pretightening force to each bolt of the bolted high-pressure turbine disk in a diagonal tightening mode, so as to ensure a stable assembly state; the rotating speeds of the high-low pressure rotors are regulated through a frequency converter, vibration signals at all the rotating speeds are measured in sequence, an amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotors are analyzed; different weight bolts are arranged on the low-pressure turbine disk to change the eccentric excitation size, and vibration signals at each rotating speed are measured in sequence; and analyzing the influence rule of the eccentric excitation amplitude on the vibration characteristics and the vibration transfer characteristics of the double-rotor system by comparing and analyzing the amplitude-frequency characteristic curve, the waterfall diagram and the time domain response under different eccentric excitation.
Compared with the prior art, the invention has the following advantages:
1. the tandem type bolt connection double-rotor test bed and the test method thereof can realize the research on the vibration characteristics and the transmission characteristics of the bolt connection double-rotor of the aeroengine, and simultaneously consider the strong nonlinear behavior caused by the coupling vibration of the bolt connection and the elastic element; the invention can provide a certain reference meaning for the design, fault diagnosis and assembly process of the aeroengine.
2. Compared with the existing test bed, the test bed provided by the invention has the advantages that the structural design is simpler and more reasonable by using the serial design method; a reasonable central coupling support structure is designed to provide stable and reasonable vibration transmission behavior for the rotor test bed; according to the characteristic point of a real high-pressure turbine bolt-spigot connection structure of the aero-engine, the high-pressure rotor is simplified and designed, so that the defects of the design of a bolt connection double-rotor test bed and a vibration test method at present are overcome; meanwhile, related experimental researches such as the influence of bolt pretightening force on the vibration characteristics of the double-rotor system, the influence of the rigidity of the elastic element on the vibration transmission characteristics, the influence of the position of the low-pressure turbine disk on the vibration transmission characteristics of the system and the like can be carried out.
Based on the reasons, the method can be widely popularized in the fields of aeroengine dynamic performance experiments and tests and the like.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to the drawings without inventive effort to a person skilled in the art.
FIG. 1 is a schematic illustration of a tandem type bolted dual rotor test stand system of the present invention.
FIG. 2 is a schematic diagram of the overall structure of the tandem type bolt connection dual-rotor test stand of the present invention.
FIG. 3 is a schematic view of a low-voltage rotor and its supporting structure of the tandem type bolt connection dual-rotor test stand of the present invention.
FIG. 4 is a schematic view of a high-pressure rotor and its supporting structure of the tandem-type bolted dual-rotor test stand of the present invention.
FIG. 5 is a schematic view of a structure of a bolted high-pressure turbine disk with a spigot of a tandem type bolted birotor test stand of the present invention.
FIG. 6 is a cross-sectional view of a bolted high pressure turbine disk with a spigot of the tandem bolted birotor test stand of the present invention.
FIG. 7 is a schematic view of the structure of the low-pressure turbine disc of the tandem type bolt connection dual-rotor test stand.
FIG. 8 is a cross-sectional view of a center coupling support structure of a tandem type bolted dual rotor test stand of the present invention.
FIG. 9 is a schematic view of a tandem type bolt connection dual-rotor test stand high-pressure turbine shaft connection sleeve.
FIG. 10 is a schematic diagram of a tandem type bolted birotor test stand squirrel cage according to the present invention.
FIG. 11 is a cross-sectional view of a tandem type bolted birotor test stand squirrel cage of the present invention.
FIG. 12 is a schematic diagram of the wiring scheme of the tandem type bolt connection dual-rotor test stand of the present invention.
In the figure: A. a low pressure rotor system; B. a central coupling support structure; C. a high pressure rotor system; 1. a low-voltage driving motor; 2. a low pressure shaft coupling; 3. a low pressure bearing seat; 4. a low pressure turbine shaft; 5. a low pressure turbine disk; 6. a central coupling support structure bearing seat; 7. a high pressure turbine shaft connection sleeve; 8. a high pressure turbine left shaft; 9. a high pressure turbine disk; 10. a high pressure turbine right shaft; 11. a high-pressure bearing seat; 12. a high pressure shaft coupling; 13. a high voltage driving motor; 14. a low-voltage driving motor base; 15. a low pressure bearing seat support; 16. a central coupling support structure bearing seat support; 17. a high-pressure bearing seat support; 18. a T-shaped groove base; 19. a high-voltage driving motor base; 20. a left disk of the high-pressure turbine disk; 21. a high pressure turbine disk right disc; 22. a squirrel cage; 23. an intermediate bearing; 24. a central coupling support bearing; 25. a signal conditioner; 26. a frequency converter; 27. a data acquisition system; 28. a workstation.
Detailed Description
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present invention. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be clear that the dimensions of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present invention: the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The invention provides a tandem type bolt connection double-rotor test stand, which is shown in figure 1. The low-voltage rotor system comprises a low-voltage driving device, a low-voltage rotor system A, a central coupling supporting structure B, a high-voltage rotor system C and a high-voltage driving device which are transversely and sequentially arranged on a T-shaped groove base 18, wherein the low-voltage rotor system A and the high-voltage rotor system C form a double-rotor system, the low-voltage driving device is connected with the left side of the low-voltage rotor system A, the right side of the low-voltage rotor system A is connected with the left side of the central coupling supporting structure B, the right side of the central coupling supporting structure B is connected with the left side of the high-voltage rotor system C, and the right side of the high-voltage rotor system C is connected with the high-voltage driving device. Wherein: the T-slot mount 18 is used to secure the dual rotor system and provide stable experimental conditions; the left side of the low-pressure rotor system A and the right side of the high-pressure rotor system C are fixed through bearing blocks and supports; the right side of the low-pressure rotor system a and the left side of the high-pressure rotor system C are connected and fixed by a central coupling support structure B comprising an intermediate bearing 23 and an elastic support structure. Each support is fixed on the T-shaped groove bottom seat 18 through a special bolt and a locknut of the T-shaped groove bottom seat 18, so that the influence on an experimental result caused by loosening of the bolt due to vibration in the testing process is avoided, and meanwhile, the high-low pressure rotor system is further ensured to have higher coaxiality. The invention can realize the research on the vibration characteristics of the double rotors of the bolted connection of the aeroengine, and simultaneously can consider the strong nonlinear behavior caused by the coupled vibration of the bolted connection and the elastic element. The structure design is more concise and reasonable, the vibration transmissibility is good, the defects of the design and the vibration testing method of the bolt connection double-rotor test bed are overcome, and related experimental researches of considering the influence of the bolt pretightening force on the vibration characteristics of the double-rotor system, the influence of the rigidity of the elastic element on the vibration transmission characteristics, the influence of the position of the low-pressure turbine disk on the vibration transmission characteristics of the system and the like can be carried out.
Specifically, as shown in fig. 3, the low-pressure rotor system a includes a low-pressure turbine shaft 4, a low-pressure bearing seat 3, a low-pressure bearing seat support 15, and a low-pressure turbine disk 5, and the low-pressure driving device includes a low-pressure driving motor 1, a low-pressure shaft coupling 2, and a low-pressure driving motor base 14; the left side of the low-pressure turbine shaft 4 is fixed on a T-shaped groove bottom seat 18 through a low-pressure bearing seat 3 and a low-pressure bearing seat support 15, and is connected with a low-pressure driving motor 1 through a low-pressure shaft coupling 2, the low-pressure driving motor 1 is arranged on a low-pressure driving motor base 14, and the low-pressure driving motor base 14 is fixed on the T-shaped groove base 18; the right side of the low-pressure turbine shaft 4 is provided with an intermediate bearing 23 which is fixed in the high-pressure turbine shaft connecting sleeve 7 of the central coupling supporting structure B through an elastic element-mouse cage 22, namely the right side of the low-pressure turbine shaft 4 is provided with an intermediate bearing 23 which is connected with the elastic element-mouse cage 22, and the mouse cage 22 is connected with the high-pressure turbine shaft connecting sleeve 7 of the central coupling supporting structure B through an edge screw hole through bolts, so that an elastic supporting structure is formed; as shown in fig. 7, the low-pressure turbine disk 5 has a disk structure with edges, and 6 threaded through holes are circumferentially arranged in the center, so that the unbalance amount of the low-pressure turbine disk 5 can be changed by matching with bolts of different numbers and different weights. The low-pressure turbine disc 5 is fixed on the low-pressure turbine shaft 4 through a Z1 type tensioning sleeve, and then the position of the low-pressure turbine disc 5 can be adjusted.
Specifically, as shown in fig. 4, the high-pressure rotor system C of the present invention comprises a high-pressure turbine left shaft 8 with a conical shell, a high-pressure turbine right shaft 10 without a conical shell, a bolt-connected high-pressure turbine disk 9 with a spigot, a high-pressure bearing seat 11, a high-pressure bearing seat support 17, and a high-pressure driving device comprises a high-pressure shaft coupling 12, a high-pressure driving motor 13 and a high-pressure driving motor base 19; the left end of the right high-pressure turbine shaft 10 is connected with a high-pressure turbine disc 9, the right side of the right high-pressure turbine shaft 10 is fixed on a T-shaped groove base 18 through a high-pressure bearing seat 11 and a high-pressure driving motor 13 through a high-pressure shaft coupler 12, the high-pressure driving motor 13 is arranged on a high-pressure driving motor base 19, and the high-pressure driving motor base 19 is fixed on the T-shaped groove base 18; the conical shell is arranged at the left end of the left shaft 8 of the high-pressure turbine, and the edge of the conical shell of the left shaft 8 of the high-pressure turbine is connected with the high-pressure turbine shaft connecting sleeve 7 of the central coupling supporting structure B through bolts to form a whole; the right end of the high-pressure turbine left shaft 8 is connected to a high-pressure turbine disk 9. As shown in fig. 5 and 6, the bolted high-pressure turbine disk 9 with the spigot includes a high-pressure turbine disk left disk 20 and a high-pressure turbine disk right disk 21 connected by 8 bolts. The left disc and the right disc are connected through the spigot interference fit, so that the coaxiality of the two discs is guaranteed, and meanwhile, the high-pressure turbine disc structure is consistent with that of a real aeroengine in bolt connection. In addition, the center positions of the left disc and the right disc are respectively provided with an annular protrusion and two screw holes, the annular protrusions are used for interference fit with the left shaft and the right shaft of the high-pressure turbine, the screw holes are used for further fastening the shafts and the high-pressure turbine disc 9 through bolt connection, the influence on experimental results caused by loose connection of the left shaft and the right shaft of the high-pressure turbine and the high-pressure turbine disc 9 is prevented, and the safety of the experimental process is ensured.
Specifically, as shown in fig. 8, the central coupling support structure B includes a central coupling support structure bearing seat 6, a central coupling support structure bearing seat support 16, a squirrel cage 22, an intermediate bearing 23, a central coupling support bearing 24, and a high-pressure turbine shaft connecting sleeve 7, the central coupling support structure bearing seat support 16 is fixed on the T-shaped groove bottom seat 18, the central coupling support structure bearing seat 6 is mounted on the central coupling support structure bearing seat support 16, and the central coupling support bearing 24 is mounted on the central coupling support structure bearing seat 6; as shown in fig. 10 and 11, the squirrel cage 22 is a cylindrical structure with a hollowed design, has smaller rigidity and better elasticity, and can transmit the vibration from the low-pressure turbine shaft 4 to the high-pressure rotor and play a role in damping; as shown in fig. 9, the high-pressure turbine shaft connecting sleeve 7 is of a stepped cylindrical structure and is fixed in the central coupling support bearing 24, and the squirrel cage 22 is an elastic element and is inserted into the left side of the high-pressure turbine shaft connecting sleeve 7 to be connected with the high-pressure turbine shaft connecting sleeve 7 to form an elastic support structure. The intermediate bearing 23 is installed inside the squirrel cage 22, and the right end of the low-pressure turbine shaft 4 is connected with the intermediate bearing 23 in a matching manner. Screw holes are formed at two ends of the high-pressure turbine shaft connecting sleeve 7 and are respectively used for being connected with the squirrel cage 22 and the conical shell of the left shaft 8 of the high-pressure turbine, so that the low-pressure rotor and the high-pressure rotor are elastically connected; a certain gap is designed between the squirrel cage 22 and the high-pressure turbine shaft connecting sleeve 7, so that rub-impact faults of the squirrel cage 22 and the high-pressure turbine shaft connecting sleeve due to overlarge unbalanced excitation in the test process are prevented; the high and low pressure rotor systems can operate independently due to the presence of the central coupling support bearing 24 and the intermediate bearing 23.
The invention provides a testing method based on the tandem type bolt connection double-rotor test bed, which specifically comprises the following steps:
(1) Two eddy current sensors are arranged at the position of the high-pressure rotor system C, which is close to the position where the high-pressure turbine disk 9 is connected with a bolt, and are respectively used for measuring vibration response signals of the rotor in the horizontal direction and the vertical direction in real time; the electric vortex sensor is sequentially connected with the electric vortex front-end processor and the signal conditioner 25, and finally is connected to the workstation 28 through the data acquisition system 27 to correspondingly process and display the measured data; a prescribed sampling frequency and sampling point number are set in the data acquisition system 27.
(2) The same pretightening force is applied to each bolt of the bolted high-pressure turbine disk 9 by using a fixed torque wrench, wherein the tightening mode adopts a diagonal tightening mode so as to ensure that the high-pressure rotor has proper coaxiality; the rotating speed of the high-low pressure rotor is regulated through a frequency converter 26, vibration signals at each rotating speed are measured in sequence, an amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotor are analyzed; the pretightening force of the bolt-connected high-pressure turbine disk 9 is changed, vibration signals at all rotating speeds are sequentially measured, an amplitude-frequency characteristic curve, a waterfall diagram, a time domain response and an axis track which are drawn by the vibration signals under different pretightening forces are compared and analyzed, and the influence rule of the bolt pretightening force on the inherent frequency, the vibration characteristics and the motion state of the dual-rotor system is analyzed.
(3) The bolts connected with the high-pressure turbine disk 9 through bolts are applied with the same pretightening force in a diagonal tightening mode by using a fixed torque wrench, so that a stable assembly state is ensured; three different thicknesses of the cage 22 are chosen for varying the stiffness of the elastic element; the rotating speed of the high-low pressure rotor is regulated through a frequency converter 26, vibration signals of the double-rotor system with the squirrel cage 22 with different thicknesses in a safe rotating speed interval are sequentially measured, and an amplitude-frequency characteristic curve, a waterfall diagram and a time domain response axis track are drawn; analyzing the law of evolution of the vibration transmission characteristics of the bolted double-rotor system with different elastic element rigidities to analyze the law of influence on the inherent frequency, vibration characteristics and motion state of the double-rotor system;
(4) The bolts connected with the high-pressure turbine disk 9 through bolts are applied with the same pretightening force in a diagonal tightening mode by using a fixed torque wrench, so that a stable assembly state is ensured; the rotating speed of the high-low pressure rotor is regulated through a frequency converter 26, vibration signals at each rotating speed are measured in sequence, an amplitude-frequency characteristic curve, a waterfall diagram, a time domain response and a poincare interface diagram are drawn, and the motion state and the vibration characteristics of the rotor are analyzed; the position of the low-pressure turbine disc 5 on the low-pressure turbine shaft 4 is changed, vibration signals at each rotating speed are sequentially measured, and the influence rules of the position of the low-pressure turbine disc 5 on the vibration characteristics and the vibration transmission characteristics of the dual-rotor system, the natural frequency of the system, the vibration characteristics and the motion state are analyzed by comparing and analyzing the amplitude-frequency characteristic curves, the waterfall diagrams, the axle center tracks and the time domain responses of the positions of the different low-pressure turbine discs 5.
(5) The bolts connected with the high-pressure turbine disk 9 through bolts are applied with the same pretightening force in a diagonal tightening mode by using a fixed torque wrench, so that a stable assembly state is ensured; the rotating speed of the high-low pressure rotor is regulated through a frequency converter 26, vibration signals at each rotating speed are measured in sequence, an amplitude-frequency characteristic curve, a waterfall diagram axis track and a time domain response are drawn, and the rotor motion state and the vibration characteristics are analyzed; different weight bolts are mounted on the low pressure turbine disk 5 to vary the eccentric excitation magnitude and vibration signals at each rotational speed are measured in turn. And analyzing the influence rule of the eccentric excitation amplitude on the vibration characteristics and the vibration transfer characteristics of the double-rotor system by comparing and analyzing the amplitude-frequency characteristic curve, the waterfall diagram and the time domain response under different eccentric excitation.
The invention provides a tandem type bolt connection double-rotor test bed and a test method thereof, which can realize the research on the vibration characteristics and the transmission characteristics of the bolt connection double-rotor of an aeroengine, and simultaneously consider the strong nonlinear behavior caused by the coupling vibration of the bolt connection and an elastic element; compared with the existing test bed, the structure design is simpler and more reasonable, the vibration transmissibility is good, the defects of the design and vibration testing method of the bolt connection double-rotor test bed are overcome, and related experimental researches which consider the influence of the bolt pretightening force on the vibration characteristics of the double-rotor system, the influence of the rigidity of the elastic element on the vibration transmission characteristics, the influence of the position of the low-pressure turbine disc 5 and the eccentric excitation amplitude on the vibration transmission characteristics, the vibration characteristics and the motion state of the system can be carried out. Based on the invention, related theoretical results are obtained, and theoretical support and technical support can be provided for structural design, fault prevention and vibration stability analysis of the aero-engine, so that the method has higher practical significance.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (9)
1. A tandem bolted birotor test stand, comprising: the device comprises a T-shaped groove bottom seat (18), and a low-pressure driving device, a low-pressure rotor system (A), a central coupling supporting structure (B), a high-pressure rotor system (C) and a high-pressure driving device which are transversely and sequentially arranged on the T-shaped groove bottom seat (18), wherein the low-pressure rotor system (A) and the high-pressure rotor system (C) form a double-rotor system, the T-shaped groove bottom seat (18) is used for fixing the double-rotor system and providing stable experimental conditions, the low-pressure driving device is connected with one side of the low-pressure rotor system (A), the other side of the low-pressure rotor system (A) is connected with one side of the central coupling supporting structure (B), the other side of the central coupling supporting structure (B) is connected with one side of the high-pressure rotor system (C), and the other side of the high-pressure rotor system (C) is connected with the high-pressure driving device; the low pressure rotor system (a) comprises a low pressure turbine disc (5) and the high pressure rotor system (C) comprises a high pressure turbine disc (9).
2. The tandem bolted birotor test stand according to claim 1, wherein the low pressure rotor system (a) further comprises a low pressure bearing housing (3), a low pressure turbine shaft (4) and a low pressure bearing housing support (15), the low pressure drive means comprising a low pressure drive motor (1), a low pressure shaft coupling (2) and a low pressure drive motor mount (14);
the low-voltage driving motor base (14) is fixed on a T-shaped groove base (18), the low-voltage driving motor (1) is installed on the low-voltage driving motor base (14), the low-voltage shaft coupler (2) is connected to the output end of the low-voltage driving motor (1), the left end of the low-voltage turbine shaft (4) is connected with the low-voltage shaft coupler (2), the right end of the low-voltage turbine shaft (4) is connected with a central coupling supporting structure (B), a low-voltage bearing seat (3) is connected to the left side, close to the low-voltage shaft coupler (2), of the low-voltage turbine shaft (4), a bearing installed inside the low-voltage bearing seat (3) is connected with the low-voltage turbine shaft (4) in a matched mode, the low-voltage bearing seat (3) is installed on a low-voltage bearing seat support (15), and the low-voltage bearing seat support (15) is fixed on the T-shaped groove base (18); the low-pressure turbine disk (5) is connected to the low-pressure turbine shaft (4) and is located between the low-pressure bearing seat (3) and the central coupling support structure (B).
3. The tandem type bolted double-rotor test stand according to claim 2, wherein the low pressure turbine disc (5) is of a disc structure with edges, and a plurality of threaded through holes are circumferentially arranged in the center, and the unbalance amount of the low pressure turbine disc (5) is changed by matching with different numbers of bolts and different weight bolts; the low-pressure turbine disc (5) is fixed on the low-pressure turbine shaft (4) through a Z1 type tensioning sleeve and used for adjusting the position of the low-pressure turbine disc (5).
4. The tandem bolted birotor test stand according to claim 2, wherein the high pressure rotor system (C) further comprises a high pressure turbine left shaft (8) with cone shell, a high pressure turbine right shaft (10) without cone shell, a high pressure bearing housing (11) and a high pressure bearing housing support (17), the high pressure drive means comprising a high pressure shaft coupling (12), a high pressure drive motor (13) and a high pressure drive motor base (19);
the high-voltage driving motor base (19) is fixed on the T-shaped groove base (18), the high-voltage driving motor (13) is arranged on the high-voltage driving motor base (19), the high-voltage shaft coupler (12) is connected to the output end of the high-voltage driving motor (13), the right end of the high-voltage turbine right shaft (10) is connected with the high-voltage shaft coupler (12), and the left end of the high-voltage turbine right shaft is connected with the high-voltage turbine disc (9); the right end of the left shaft (8) of the high-pressure turbine is connected with a high-pressure turbine disc (9), and the conical shell at the left end is rotationally connected with a central coupling supporting structure (B); the right side, close to the high-pressure shaft coupling (12), of the high-pressure turbine right shaft (10) is connected with a high-pressure bearing seat (11), a bearing mounted in the high-pressure bearing seat (11) is connected with the high-pressure turbine right shaft (10) in a matched mode, the high-pressure bearing seat (11) is mounted on a high-pressure bearing seat support (17), and the high-pressure bearing seat support (17) is fixed on a T-shaped groove bottom seat (18).
5. The tandem type bolted double-rotor test stand according to claim 4, wherein the high-pressure turbine disc (9) comprises a high-pressure turbine disc left disc (20) and a high-pressure turbine disc right disc (21) which are connected through a plurality of bolts, the high-pressure turbine disc left disc (20) and the high-pressure turbine disc right disc (21) are connected through spigot interference fit, and the coaxiality is ensured while the high-pressure turbine disc structure is consistent with a real aeroengine bolted high-pressure turbine disc structure; the center positions of the left high-pressure turbine disc (20) and the right high-pressure turbine disc (21) are respectively provided with an annular protrusion and two screw holes, the two annular protrusions are respectively used for being in interference fit with the left high-pressure turbine shaft (8) and the right high-pressure turbine shaft (10), and the screw holes are used for further fastening the shaft and the right high-pressure turbine disc (9) through bolt connection.
6. The tandem bolted birotor test stand according to claim 4, wherein the central coupling support structure (B) comprises a central coupling support structure bearing seat (6), a central coupling support structure bearing seat support (16), a high pressure turbine shaft connection sleeve (7), a squirrel cage (22), an intermediate bearing (23) and a central coupling support bearing (24), the central coupling support structure bearing seat support (16) is fixed on a T-shaped groove bottom seat (18), the central coupling support structure bearing seat (6) is mounted on the central coupling support structure bearing seat (16), the central coupling support bearing (24) is mounted on the central coupling support structure bearing seat (6), the high pressure turbine shaft connection sleeve (7) is fixed in the central coupling support bearing (24); the squirrel cage (22) is an elastic element, is inserted into the left side of the high-pressure turbine shaft connecting sleeve (7), and is connected with the high-pressure turbine shaft connecting sleeve (7) to form an elastic supporting structure; the middle bearing (23) is arranged in the mouse cage (22), and the right end of the low-pressure turbine shaft (4) is connected with the middle bearing (23) in a matching way;
screw holes are formed at two ends of the high-pressure turbine shaft connecting sleeve (7) and are respectively used for being connected with the squirrel cage (22) and the conical shell of the left shaft (8) of the high-pressure turbine, so that the low-pressure rotor and the high-pressure rotor are elastically connected; the high-pressure and low-pressure rotor systems can operate independently based on the presence of the central coupling support bearing (24) and the intermediate bearing (23).
7. The tandem type bolt connection dual-rotor test stand according to claim 6, wherein the squirrel cage (22) is a cylindrical structure with a hollowed design, and is used for transmitting vibration from a low-pressure turbine shaft (4) to a high-pressure rotor and damping the vibration; the high-pressure turbine shaft connecting sleeve (7) is of a stepped cylinder structure; a certain gap is reserved between the squirrel cage (22) and the high-pressure turbine shaft connecting sleeve (7).
8. The tandem type bolted connection dual-rotor test stand according to claim 6, wherein the low-voltage driving motor base (14), the low-voltage bearing seat support (15), the central coupling supporting structure bearing seat support (16), the high-voltage bearing seat support (17) and the high-voltage driving motor base (19) are all fixed on the T-shaped groove bottom seat (18) through special bolts and locknuts of the T-shaped groove bottom seat (18), so that the experimental result is prevented from being influenced due to loosening of bolts caused by vibration in the test process, and meanwhile, higher coaxiality of the high-voltage and low-voltage rotor system is further ensured.
9. A method of testing a tandem bolted twin rotor test bench according to any of claims 1 to 8, comprising the steps of:
s1, installing two eddy current sensors at the position of a high-pressure rotor close to a high-pressure turbine disc (9) connected with a bolt, wherein the eddy current sensors are respectively used for measuring vibration response signals of the rotor in the horizontal direction and the vertical direction in real time; the electric vortex sensor is sequentially connected with the electric vortex front-end processor and the signal conditioner (25), and finally is connected to a workstation (28) through a data acquisition system (27) to correspondingly process and display measured data; setting a prescribed sampling frequency and sampling point number in a data acquisition system (27);
s2, applying the same pretightening force to each bolt of the bolted high-pressure turbine disc (9) by using a constant torque wrench, wherein the tightening mode adopts a diagonal tightening mode so as to ensure that the high-pressure rotor has proper coaxiality; the rotating speed of the high-low pressure rotor is regulated through a frequency converter (26), vibration signals at each rotating speed are measured in sequence, a amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotor are analyzed; changing the pretightening force of a bolt connected high-pressure turbine disc (9) and sequentially measuring vibration signals at each rotating speed, and analyzing the influence of the pretightening force of the bolt on the vibration characteristics of the double-rotor system by comparing and analyzing amplitude-frequency characteristic curves, waterfall diagrams and time domain responses under different pretightening forces;
s3, using a fixed torque wrench to apply the same pretightening force to each bolt of the bolted high-pressure turbine disk (9) in a diagonal tightening mode, so as to ensure a stable assembly state; three different thicknesses of the squirrel cage (22) are selected for changing the rigidity of the elastic element; the rotating speed of the high-low pressure rotor is regulated through a frequency converter (26), vibration signals of the double-rotor system with the squirrel-cage (22) with different thicknesses in a safe rotating speed interval are sequentially measured, and an amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn; analyzing the law of the evolution of the vibration transmission characteristics of the bolted double-rotor system with different elastic element rigidities to analyze the law of the influence on the inherent frequency, the vibration characteristics and the motion state of the double-rotor system;
s4, using a fixed torque wrench to apply the same pretightening force to each bolt of the bolted high-pressure turbine disk (9) in a diagonal tightening mode, so as to ensure a stable assembly state; the rotating speed of the high-low pressure rotor is regulated through a frequency converter (26), vibration signals at each rotating speed are measured in sequence, a amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotor are analyzed; changing the position of the low-pressure turbine disc (5) on the low-pressure turbine shaft (4) and sequentially measuring vibration signals at each rotating speed, and analyzing the influence rule of the position of the low-pressure turbine disc (5) on the vibration characteristics and the vibration transfer characteristics of the double-rotor system by comparing and analyzing amplitude-frequency characteristic curves, waterfall diagrams and time domain responses at the positions of different low-pressure turbine discs (5);
s5, using a fixed torque wrench to apply the same pretightening force to each bolt of the bolted high-pressure turbine disk (9) in a diagonal tightening mode, so as to ensure a stable assembly state; the rotating speed of the high-low pressure rotor is regulated through a frequency converter (26), vibration signals at each rotating speed are measured in sequence, a amplitude-frequency characteristic curve, a waterfall diagram and a time domain response are drawn, and the motion state and the vibration characteristics of the rotor are analyzed; different weight bolts are arranged on the low-pressure turbine disk (5) to change the eccentric excitation size, and vibration signals at each rotating speed are sequentially measured; and analyzing the influence rule of the eccentric excitation amplitude on the vibration characteristics and the vibration transfer characteristics of the double-rotor system by comparing and analyzing the amplitude-frequency characteristic curve, the waterfall diagram and the time domain response under different eccentric excitation.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN118090048A (en) * | 2024-04-29 | 2024-05-28 | 山东泰力达电机有限公司 | Motor rotor balance detection device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN118090048A (en) * | 2024-04-29 | 2024-05-28 | 山东泰力达电机有限公司 | Motor rotor balance detection device |
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