CN113933041A - Bearing rigidity simulation rotor test device and support assembly verification method - Google Patents
Bearing rigidity simulation rotor test device and support assembly verification method Download PDFInfo
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- CN113933041A CN113933041A CN202111291226.8A CN202111291226A CN113933041A CN 113933041 A CN113933041 A CN 113933041A CN 202111291226 A CN202111291226 A CN 202111291226A CN 113933041 A CN113933041 A CN 113933041A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
Abstract
The application belongs to the field of aircraft engine tests, and particularly relates to a method for verifying a supporting component of a supporting rigidity simulation rotor test device, which structurally comprises the following steps: a rotor (1); the bearing assembly comprises a base (4) and a bearing assembly (2), wherein the bearing assembly (2) comprises a bearing (21), a bearing seat (22) and an elastic supporting assembly (5) arranged between the bearing (21) and the bearing seat (22); the vibration characteristic of the engine in the experimental process can be well simulated by depending on the elasticity of the elastic support assembly, and the support rigidity simulation is realized by only replacing the elastic support assembly aiming at the rotors with different support rigidities, so that the elastic support assembly has strong applicability and economy.
Description
Technical Field
The application belongs to the field of aircraft engine tests, and particularly relates to a supporting rigidity simulation rotor test device.
Background
The aircraft engine is a complex thermal machine with high temperature, high pressure and high-speed rotation, is composed of tens of thousands of parts, has compact structure and narrow space, is severe in temperature change and extremely complex in internal flow during working, causes severe environment of each structural part, and has great influence on the reliability of the engine, so that the aircraft engine is classified as a machine with low service life, high cost and easy failure at home and abroad. Statistically, a 70% reliability failure is manifested in the form of rotor vibration. However, due to the limitation of the existing vibration testing means, the rotor vibration cannot be directly measured, and the sensor is mounted on the engine case for testing, so that the difficulty is brought to vibration signal analysis and fault diagnosis.
The uk engine design specification DEF STAN 0097011 section indicates that the design analysis of the complete machine vibration analysis is not only based on the engine complete machine power model, but also emphasizes the importance of performing simulation test validation and modification of the analytical model in the rotor tester. In order to improve the effectiveness of the vibration diagnosis of the aircraft engine, the dynamic characteristic test research of a typical engine rotor is required. The whole rotor system has a complex structure and variable working load, and is difficult to carry out experimental research on dynamic characteristics and a test method, so that simulation of the vibration condition of a typical engine rotor on a rotor tester is very necessary. At present, rotor vibration characteristic research is mainly carried out on a rigid rotor tester, but the supporting rigidity of the rigid rotor tester is too strong and is obviously higher than the actual supporting rigidity of an engine, and the vibration state of a real engine rotor cannot be simulated.
The existing rotor tester mainly adopts a rigid bearing mode, a rotor is supported on a bearing bush through a shaft neck, oil film lubrication is formed between the shaft neck and the bearing bush when the rotor runs, the rigidity of the rigid bearing is very high, so that the critical rotation speed of the rotor on the tester is very high, even the first-order critical rotation speed is out of the working range, and the rotor can not effectively simulate the vibration characteristic under the condition of an engine under the condition of the tester. The existing rotor tester adopts a rigid coupling to transmit torque, and when a tested rotor shaft is poorly aligned with an output shaft of a driving motor, the rotor can vibrate to be obviously increased, so that the operation of the tester is influenced.
The existing rotor tester has a prominent vibration problem, and once a working state is in a problem, the maintenance cost is high, the period is long, and the test process is seriously influenced.
In rotating machines, flexible bearings are often used to regulate critical rotational speeds and reduce structural vibrations. The elastic ring type vibration reduction structure is an important flexible support, has the characteristics of simple structure, small occupied space, high reliability, low cost and the like, can effectively reduce the amplitude of the rotor during resonance, enables the rotor to smoothly pass through the critical rotating speed, and is widely applied to rotating machinery.
Disclosure of Invention
In order to solve the above problem, the present application provides a supporting rigidity simulation rotor test device, which simulates the vibration characteristics of an aeroengine to be tested, and the structure of the device comprises:
a rotor including a first end and a second end;
the base comprises a first base and a second base;
a bearing assembly, comprising: the first bearing assembly is arranged at the first end of the rotor and is erected on the first base; the second bearing assembly is arranged at the second end of the rotor and is erected on the second base;
one end of the simulation turbine shaft is connected with the first end of the rotor, and the other end of the simulation turbine shaft is connected with the driving shaft;
the bearing assembly comprises a bearing, a bearing seat and an elastic supporting assembly arranged between the bearing and the bearing seat;
the elastic support assembly includes: an elastic ring; the elastic ring outer bushing is sleeved on the outer side of the elastic ring; the elastic ring inner bushing is sleeved on the inner side of the elastic ring; the inner side of the inner lining of the elastic ring contacts the bearing, and the outer side of the outer lining of the elastic ring contacts the bearing seat.
Preferably, the drive shaft comprises a flexible drive shaft, which is of thin walled cylindrical construction.
Preferably, the edge of the elastic ring inner bushing is provided with an axial boss, the corresponding position of the bearing seat is provided with a groove, and the boss is matched with the groove to limit the rotation of the elastic ring inner bushing.
Preferably, the bearing comprises a first bearing and a second bearing, and the first bearing is a deep groove ball bearing; the second bearing is a roller bearing.
Preferably, the end of the second bearing assembly is provided with a spiral sealing aluminum sleeve structure, and the spiral sealing aluminum sleeve structure is connected with the second bearing assembly in a matching way through a spigot; the first bearing assembly end has an end cap compression seal arrangement.
Preferably, the number of the bosses of the elastic ring inner lining is 4-6, and the bosses are uniformly distributed along the circumferential direction of the elastic ring inner lining.
Preferably, the spiral sealing aluminum sleeve structure and the end cover compression sealing structure are both provided with an oil injection pipe mounting hole, an oil injection pipe is mounted in the oil injection pipe mounting hole, and a sealing rubber ring is arranged between the oil injection pipe mounting hole and the oil injection pipe.
Wherein, corresponding to the rigidity test verification method of the elastic supporting component,
step S1: establishing a finite element model of the elastic support assembly;
step S2: presetting the load of a finite element model of the elastic support assembly, extracting the average displacement of the outer surface of the inner bushing of the elastic ring and the average displacement of the inner surface of the outer bushing of the elastic ring, and taking the difference of the average displacements as the deformation of the elastic ring under the action of the preset load;
step S3: determining a ratio of the preset load to the deformation amount as a stiffness of the elastic ring.
The method for testing and verifying the rigidity of the elastic support component comprises the step of establishing a finite element model of the elastic support component in step S1, specifically establishing a half finite element model of the elastic support component.
The advantages of the present application include: the elastic supporting structure is designed to simulate the supporting rigidity of the engine in a working state, so that the rotor has the same vibration characteristic on a tester under the engine condition;
an effective lubricating and sealing system is designed to ensure the running safety of the bearing;
the vibration caused by the misalignment of the rotor in the torque transmission process of the rotor tester is reduced;
the tester is ensured to operate stably, and has good maintainability.
Drawings
FIG. 1 is a schematic view of a bearing stiffness simulation rotor test device according to the present application;
FIG. 2 is a schematic view of a resilient support assembly;
FIG. 3 is a schematic view of a finite element model of the flexible support assembly;
FIG. 4 is a schematic view of a stiffness testing apparatus for the resilient support assembly;
FIG. 5 is a schematic view of a spray bar installation;
the bearing comprises a rotor 1, a bearing assembly 2a, a bearing assembly 2b, a bearing 21a, a bearing 21b, a bearing seat 22, a simulated turbine shaft 3, a base 4 comprising a first base, a base 4b and a second base 5, an elastic support assembly 51, an elastic ring 52, an elastic ring outer bushing 53, an elastic ring inner bushing 54, a boss 54, a driving shaft 6, a spiral sealing aluminum sleeve structure 71, an end cover pressing sealing structure 7, an oil injection pipe 8 and a sealing rubber ring 81.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
Aiming at the technical problems, the invention designs a supporting rigidity simulation rotor test device by taking a certain type of fan rotor as an example, which mainly comprises three parts of a rotor driving structure design, an elastic supporting structure design and a bearing lubricating and sealing structure design, wherein the structural schematic diagram of a tester is shown in figure 1,
the structure includes:
a rotor 1 comprising a first end 11 and a second end 12;
the base 4 comprises a first base 4a and a second base 4 b;
bearing assembly 2, comprising: a first bearing assembly 2a and a second bearing assembly 2b, wherein the first bearing assembly 2a is arranged at the first end 11 of the rotor 1 and is erected on the first base 4 a; a second bearing assembly 2b mounted on the second end 12 of the rotor 1 and mounted on the second base 4 b;
a simulated turbine shaft 3, one end of which is connected with the first end 11 of the rotor 1 and the other end of which is connected with the driving shaft 6;
the bearing assembly 2 comprises a bearing 21, a bearing seat 22 and an elastic supporting assembly 5 arranged between the bearing 21 and the bearing seat 22;
the elastic support assembly 5 comprises: an elastic ring 51; an elastic ring outer bushing 52 sleeved outside the elastic ring 51; an elastic ring inner bushing 53 sleeved on the inner side of the elastic ring 51; the inner side of the elastic ring inner bushing 53 contacts the bearing 21 and the outer side of the elastic ring outer bushing 52 contacts the bearing housing 22.
The supporting structure of the rotor 1 comprises a base, a bearing seat, an elastic supporting assembly 5 and a bearing. During installation, the bearing, the elastic support assembly 5 and the bearing seat are sequentially installed on the bearing, and the outer ring of the bearing is tightly pressed by the locking nut, so that the bearing is prevented from moving axially; a small gap is reserved between the elastic support assembly 5 and the locking nut, so that the influence of axial pressing force on bearing rigidity is avoided; then fix the base on the platform guide rail through the bolt, experimental rotor and bearing frame are installed on the base with integral hoisting's form, compress tightly the bearing frame through the base upper cover at last.
The bearing stiffness simulation of the rotor is mainly realized by an elastic ring assembly, which comprises an elastic ring inner lining 53, an elastic ring and an elastic ring outer lining 53, and an elastic support assembly 5 and an elastic ring structure which are shown in fig. 2. 4 bosses are designed on the inner lining 53 of the elastic ring and inserted into the grooves on the bearing block, so that the elastic ring assembly can be effectively prevented from rotating along the circumferential direction. When the supporting rigidity of the rotor needs to be adjusted, only the elastic supporting component 5 needs to be replaced, the supporting rigidity of the rotor can be quickly adjusted, and the rotor supporting device has good interchangeability.
Under the condition of an engine, the low-pressure turbine drives the fan to rotate through the turbine shaft; under the test condition, a simulation turbine shaft 3 is designed, and one end of the simulation turbine shaft simulates a local structure of a low-pressure turbine shaft, so that the installation rigidity of a fan rotor and the turbine shaft is ensured; the other end of the simulation turbine shaft is connected with the transmission shaft, axial and radial vibration amount is reserved for mounting the rotor, the coaxiality of the rotor and the equipment transmission shaft is detected, the simulation turbine shaft is connected with the equipment driving end through the adapter flange and the flexible driving shaft, and the flexible driving shaft is designed to be of a thin-wall cylindrical structure, so that vibration caused by misalignment of the rotor can be effectively reduced.
In some possible embodiments, the number of the bosses 54 of the elastic ring inner liner 53 is 4-6, and the bosses 54 are uniformly distributed along the circumference of the elastic ring inner liner 53.
In some possible embodiments, the spiral sealing aluminum sleeve structure 71 and the end cover compression sealing structure 7 are both provided with an oil spray pipe mounting hole, the oil spray pipe mounting hole is provided with an oil spray pipe 8, and a sealing rubber ring 81 is arranged between the oil spray pipe 8 mounting hole and the oil spray pipe 8.
Wherein, corresponding to the rigidity test verification method of the elastic supporting component 5,
step S1: establishing a finite element model of the elastic supporting component 5;
step S2: presetting the load of a finite element model of the elastic supporting component 5, extracting the average displacement of the outer surface of the inner liner 53 of the elastic ring and the average displacement of the inner surface of the outer liner 52 of the elastic ring, and taking the difference of the average displacements as the deformation of the elastic ring 51 under the action of the preset load;
step S3: the ratio of the preset load to the deformation amount is determined as the rigidity of the elastic ring 51.
The method specifically comprises the following steps:
in order to ensure the supporting rigidity of the rotor 1 under the condition of the tester, a finite element method is adopted for analysis, and the supporting rigidity is ensured to be the same as that of the rotor 1 by adjusting the structural parameters of the elastic ring 51. Considering the symmetry of the elastic ring 51 in terms of deformation under force, a half model was taken for analysis for the sake of simplicity of calculation, and a finite element model of the elastic support structure is shown in fig. 3.
The average displacement of the outer surface of the inner liner 53 of the elastic ring and the average displacement of the inner surface node of the outer liner 52 of the elastic ring are respectively extracted in calculation, the displacement difference of the two is used as the deformation amount of the elastic ring under the action of the F load, and the ratio of the load to the deformation amount is determined as the rigidity of the elastic ring.
In order to ensure that the elastic supporting structure meets the design requirements, a static stiffness test is designed for verification, and the static stiffness test device of the elastic ring is shown in fig. 4.
In the test, a test mandrel penetrates through the elastic support assembly, two ends of the mandrel are fixed on the supporting cushion block in a simple support mode, and radial load is applied to the elastic ring outer bushing 52 through a loading block; and respectively sticking meter striking blocks on the inner bushing 53 and the outer bushing 53 of the elastic ring, wherein the measured displacement difference of the two meter striking blocks is the radial deformation of the elastic ring 51, the radial load is measured by a dynamometer, and the ratio of the radial load to the meter striking block displacement difference is the measured rigidity of the elastic support component.
In order to effectively simulate the vibration characteristics of the rotor under the condition of the engine, an engine original bearing is adopted, a first end 11 is a ball bearing, and a second end 12 is a rolling rod bearing. The bearing is lubricated by a tester fulcrum oil supply and return system, the oil supply position, the oil supply amount and the local structure related to an oil injection pipe are consistent with that of an engine, an oil throwing hole is designed on a test shaft, and lubricating oil enters the bearing for lubrication along the oil throwing hole under the action of centrifugal load in operation; an oil return hole is designed at the bottom of the fulcrum bearing seat, and lubricating oil returns to an oil tank in a gravity oil return mode during operation.
In some possible embodiments, the second bearing assembly 2b ends with a spiral seal aluminum housing structure 71 that is matingly connected to the second bearing assembly 2b by a spigot; the first bearing assembly 2a has an end cap compression seal arrangement 7 at the end, embodied as:
because the rotor in the tester is in a vacuum environment, gas sealing under engine conditions cannot be achieved. The axial size of the front end shaft head of the second end 12 is short, the end cover is adopted for pressing and sealing, and the rear end of the second end 12 adopts a spiral sealing aluminum sleeve structure 71; the front end of the first end 11 adopts an original sealing structure of an engine, and the rear end of the second end 12 adopts a spiral sealing aluminum sleeve structure 71; the sealing aluminum sleeve is matched with the bearing seat through a spigot and is fixed on the bearing seat through a screw. The oil spraying pipe penetrates through the sealing aluminum sleeve and is compressed by the nut, and the oil spraying pipe and the sealing aluminum sleeve are sealed by a rubber ring, as shown in figure 5.
Aiming at a typical engine rotor, the invention designs a rotor tester for simulating the support rigidity of the engine, and effectively simulates the vibration characteristic of the rotor in the engine under the condition of the tester; at present, due to the limitation of a test means, a sensor can only be arranged on a casing to measure the rotor vibration in an aircraft engine test, and the rotor vibration can be directly tested on the tester; various rotor vibration characteristic tests can be carried out on the tester, such as a vibration response characteristic test of unbalance in a full rotating speed range, a dynamic influence test of a disc shaft connection state on a rotor and the like; the method for designing the elastic support structure based on the finite element method is provided, and an elastic support rigidity testing device is designed; for the rotors with different supporting rigidity, the supporting rigidity simulation is realized by only replacing the elastic supporting assembly, so that the method has strong applicability and economy.
Claims (9)
1. A supporting rigidity simulation rotor test device simulates the vibration characteristics of an aeroengine to be tested and structurally comprises:
a rotor (1) comprising a first end (11) and a second end (12);
the base (4) comprises a first base (4a) and a second base (4 b);
bearing assembly (2) comprising: a first bearing assembly (2a) and a second bearing assembly (2b), the first bearing assembly (2a) is arranged at the first end (11) of the rotor (1) and is erected on the first base (4 a); a second bearing assembly (2b) mounted at the second end (12) of the rotor (1) and mounted on the second base (4 b);
a simulated turbine shaft (3), one end of which is connected with the first end (11) of the rotor (1), and the other end of which is connected with the driving shaft (6);
the bearing assembly (2) is characterized by comprising a bearing (21), a bearing seat (22) and an elastic supporting assembly (5) arranged between the bearing (21) and the bearing seat (22);
the elastic support assembly (5) comprises: an elastic ring (51); an elastic ring outer bushing (52) sleeved outside the elastic ring (51); an elastic ring inner bushing (53) sleeved on the inner side of the elastic ring (51); the inner side of the elastic ring inner bushing (53) contacts the bearing (21), and the outer side of the elastic ring outer bushing (52) contacts the bearing seat (22).
2. The supporting stiffness simulation rotor test device according to claim 1, wherein the drive shaft (6) comprises a flexible drive shaft, and the flexible drive shaft is of a thin-walled cylinder structure.
3. The bearing stiffness simulation rotor test device according to claim 1, wherein the edge of the elastic ring inner bushing (53) is provided with an axial boss (54), the corresponding position of the bearing seat (22) is provided with a groove, and the boss (54) is matched with the groove to limit the rotation of the elastic ring inner bushing (53).
4. The supporting rigidity simulation rotor test device according to claim 1, wherein the bearing (21) comprises a first bearing (21a) and a second bearing (21b), the first bearing (21a) is a deep groove ball bearing; the second bearing (21b) is a roller bearing.
5. The bearing stiffness simulation rotor test device according to claim 1, wherein the second bearing assembly (2b) is terminated with a spiral sealing aluminum sleeve structure (71), and the spiral sealing aluminum sleeve structure is connected with the second bearing assembly (2b) in a spigot fit manner; the first bearing assembly (2a) has an end cap compression seal arrangement (7) at the end.
6. The bearing stiffness simulation rotor test device according to claim 1, wherein the number of the bosses (54) of the elastic ring inner bushing (53) is 4-6, and the bosses (54) are uniformly distributed along the circumference of the elastic ring inner bushing (53).
7. The supporting rigidity simulation rotor test device according to claim 5, wherein the spiral sealing aluminum sleeve structure (71) and the end cover compression sealing structure (7) are provided with oil spray pipe mounting holes, the oil spray pipe mounting holes are used for mounting oil spray pipes (8), and a sealing rubber ring (81) is arranged between the oil spray pipe (8) mounting holes and the oil spray pipes (8).
8. A rigidity test verification method of an elastic support component is characterized in that,
step S1: establishing a finite element model of the elastic support component (5);
step S2: presetting the load of a finite element model of the elastic support component (5), extracting the average displacement of the outer surface of an inner liner (53) of the elastic ring and the average displacement of the inner surface of an outer liner (52) of the elastic ring, and taking the difference of the average displacements as the deformation of the elastic ring (51) under the action of the preset load;
step S3: determining a ratio of the preset load to the deformation amount as a stiffness of the elastic ring (51).
9. Method for experimental verification of the stiffness of an elastic support member according to claim 8, wherein step S1 is performed to establish a finite element model of the elastic support member (5), specifically a half finite element model of the elastic support member (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111291226.8A CN113933041A (en) | 2021-10-28 | 2021-10-28 | Bearing rigidity simulation rotor test device and support assembly verification method |
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| CN202111291226.8A CN113933041A (en) | 2021-10-28 | 2021-10-28 | Bearing rigidity simulation rotor test device and support assembly verification method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115371989A (en) * | 2022-10-26 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Variable supporting rigidity simulation structure of shaft coupling rotor |
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2021
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| CN202811831U (en) * | 2012-07-17 | 2013-03-20 | 湖南航翔燃气轮机有限公司 | Elastic supporting device |
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