CN116558822A - Multifunctional gas foil bearing supporting rotor simulation test bed - Google Patents
Multifunctional gas foil bearing supporting rotor simulation test bed Download PDFInfo
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- CN116558822A CN116558822A CN202310516096.6A CN202310516096A CN116558822A CN 116558822 A CN116558822 A CN 116558822A CN 202310516096 A CN202310516096 A CN 202310516096A CN 116558822 A CN116558822 A CN 116558822A
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- rotor
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- 239000011888 foil Substances 0.000 title claims abstract description 96
- 238000012360 testing method Methods 0.000 title claims abstract description 33
- 238000004088 simulation Methods 0.000 title claims abstract description 17
- 238000006073 displacement reaction Methods 0.000 claims abstract description 10
- 230000007704 transition Effects 0.000 claims description 13
- 238000004364 calculation method Methods 0.000 abstract 1
- 239000007921 spray Substances 0.000 abstract 1
- 238000012545 processing Methods 0.000 description 4
- 238000005259 measurement Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000005489 elastic deformation Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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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
- G01M13/04—Bearings
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L9/00—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
- G01L9/08—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means by making use of piezoelectric devices, i.e. electric circuits therefor
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/42—Devices characterised by the use of electric or magnetic means
- G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
- G01P3/49—Devices characterised by the use of electric or magnetic means for measuring angular speed using eddy currents
Abstract
The invention discloses a multifunctional gas foil bearing supporting rotor simulation experiment table, which relates to the field of high-speed rotating machinery and mainly comprises a bearing-rotor system, a power system and a testing system. The power system mainly comprises an impact turbine device and an air supply device, and the air supply device sprays high-pressure air to the impact turbine device to generate enough driving moment for the rotor system so as to realize the rotation of the rotor system. The testing system mainly comprises an eddy current displacement sensor, a temperature sensor, a pressure sensor and a software program, and radial displacement of the rotor system is obtained by orthogonally arranging the eddy current sensor, so that a motion track of the rotor system is obtained by calculation; the temperature sensor can monitor the temperature change of the gas foil bearing in real time; the pressure sensor can directly obtain the air film pressure of the air foil bearing under the condition of not changing the bearing structure, so that the air film pressure of the air foil radial bearing can be detected, the air film pressure of the air foil thrust bearing can be detected, and the function diversity of the air foil support rotor simulation test bed is realized.
Description
Technical Field
The invention relates to the field of high-speed rotating machinery, in particular to a multifunctional gas foil bearing supporting rotor simulation test bed.
Background
The test stand is an indispensable tool for research work, and functions to present test phenomena, and to verify the feasibility of design by evaluating test pieces. The development of domestic gas bearings is more than ten years behind abroad, and experimental data of high-performance gas foil bearings are mastered in a few foreign scientific research institutions, such as NASA, miTi, texas university of agriculture, honeywell company and the like. High-performance bearing experimental data are urgently needed in China to assist in research of air foil bearings and development of high-speed rotating equipment adopting gas foil bearings. The current rotor test bed is mainly used for measuring the movement track of the rotor, the temperature of the bearing and the rotating speed of the rotor.
The existing air foil support rotor test bed has the following problems: on the one hand: the function is comparatively single, can't measure the experimental data of air foil radial bearing and air foil thrust bearing simultaneously, can only carry out the experiment with air foil radial bearing and air foil thrust alone in order to obtain experimental data. On the other hand, the conventional test bed supported by the air foil bearing cannot directly measure the air film pressure when the rotor rotates.
Disclosure of Invention
The invention provides a multifunctional gas foil bearing support rotor simulation test bed, which aims to overcome the defect that a gas foil bearing support rotor test bed has a single function and cannot measure the gas film pressure when a rotor rotates in real time.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: a multifunctional gas foil bearing supporting rotor simulation test bed is characterized in that: the device comprises a supporting seat device, a power system, a bearing-rotor system and a testing system.
The supporting seat device comprises a turbine shell supporting seat 4, a shell 1 and a front lower supporting seat 2; the upper part of the front lower support 2 is provided with a shell 1, and the shell 1 is positioned through two positioning holes 33 and 45 and fixedly connected through bolts; the front end of the shell 1 is provided with a front end cover 20; the rear end of the shell is sequentially provided with a thrust bearing shaft sleeve 21, a clearance ring 46 and a rear end cover 14, which are fixedly connected through bolts; bearing transition layers 9 and 47 are arranged on two sides of the interior of the shell 1; the inside of the bearing transition layer is respectively provided with a gas foil radial bearing 47 and a gas foil radial bearing 48; said gas foil radial bearings 47, 48 support the rotor system at both ends, respectively;
the rotor system comprises a shaft 3, a turbine 17, a thrust disc 13; the front end of the shaft is provided with a turbine 17, and the rear end of the shaft is provided with a thrust disc 13;
the power system comprises a turbine 17, a turbine shell 6 and a turbine shell supporting seat 4 which are arranged on the rotor system; the turbine housing 6 is arranged on the turbine housing supporting seat 4, and is fixedly connected with a nut through a bolt, and the inner surface of the turbine housing 6 is matched with the turbine 17 through a concentric shaft;
the test system comprises eddy current displacement sensors 7, 8, 11, 12, K-type thermocouple temperature sensors and piezoelectric film sensors 34 and 38;
the shell is provided with 4 through holes 22, 23, 28 and 29 which are arranged in a pairwise orthogonal mode; the opening directions of the through holes 22 and 28 are vertical, and the opening directions of the through holes 23 and 29 are horizontal; the eddy current displacement sensors 7, 8, 11, (12) are respectively inserted into the through holes;
the shell is provided with 2 screw holes 24 and 26 in the vertical direction and 2 screw holes 25 and 27 in the horizontal direction; 2 threaded holes 49 and 50 are formed in the bearing transition layer; the threaded holes of the shell are respectively corresponding to concentric shafts with the threaded holes 54, 55, 56 and 57 of the bearing transition layer, are matched through the studs 15, 16, 18 and 19, and clamp the bearing;
the foil gas radial bearings 48, 47 comprise a bearing housing 37, a convex foil 36, a top foil 35; the top foil 35 is provided with a piezoelectric film sensor 34; the foil gas thrust bearing 52 comprises a thrust disc 13, a convex foil 40, a top foil 39; the thrust bearing 53 is composed of a thrust bearing bush 41, a convex foil 40 and a top foil 39; a piezoelectric film sensor 38 is arranged on the top foil;
the housing 1 is provided with through holes 29, 30, through which holes 29, 30 leads of the piezoelectric film sensor 38 lead out.
The housing has a flat surface 52 below the lowest height of the air foil radial bearing to facilitate the extraction of leads from the piezoelectric film sensor 34 and the K-type temperature sensor.
An annular cavity 51 is arranged on a turbine housing supporting seat in the power system, an air inlet 43 is arranged outside the annular cavity 51 and connected with a pipe threaded joint 42, and 12 nozzles 44 are arranged inside the annular cavity.
The multifunctional test bed has the advantages that the measuring system can be divided into two measuring parts, so that the rotating speed and the temperature of the air foil radial bearing, the track of the rotor system and the air film pressure during rotor rotation can be directly measured, and the rotating speed and the temperature of the air foil thrust bearing and the axial air film pressure can be directly measured. Through the test bed, the air foil radial bearing and the foil air thrust bearing can be simultaneously used, and the air film pressure can be directly measured, so that the bearing capacity of the bearing can be obtained through data processing.
The multifunctional gas foil bearing supporting rotor simulation test bed can solve the defect of single function, can perform rotor test on the gas foil radial foil bearing, and directly measure the air film pressure through the piezoelectric film sensor; the gas foil thrust bearing can be subjected to experimental measurement, and the gas film pressure can be measured through the piezoelectric film sensor which is axially arranged, so that the bearing capacity of the gas foil bearing can be obtained through data processing, and the functional diversity of the test bed can be effectively improved.
Drawings
Fig. 1 is an assembly view of the present invention.
Fig. 2 is a quarter sectional view of fig. 1.
Fig. 3 is an exploded view of the gas foil radial bearing of fig. 2.
Fig. 4 is an exploded view of the gas foil thrust bearing of fig. 2.
FIG. 5 is a schematic view of a rotor
FIG. 6 is a schematic diagram of a powertrain system
FIG. 7 is a schematic view of a bearing shell transition sleeve
Detailed Description
The invention provides a multifunctional gas foil bearing supporting rotor simulation test bed, which is used for making the purposes, technical schemes and effects of the invention clearer and more definite, and is further described in detail below by referring to the accompanying drawings and examples. It should be understood that the specific examples described herein are intended to illustrate the invention and are not intended to limit the invention.
With reference to fig. 2, the multifunctional gas foil bearing supporting rotor simulation experiment table comprises a supporting seat device, a power system, a bearing-rotor system and a testing system. The supporting seat device consists of a front lower support 2, a turbine shell supporting seat 4 and a shell 1. The power system consists of a turbine housing 6 and a turbine 17. The bearing-rotor system consists of a gas foil radial bearing 48, a gas foil radial bearing 47, a gas foil thrust bearing 52, a gas foil thrust bearing 53, a rotor. The measuring system consists of 4 eddy current displacement sensors 7, 8, 11, 12, a radial piezoelectric film sensor, an axial piezoelectric film sensor and a K-type thermocouple sensor, and records the motion track of a laboratory rotor, the air film pressure and the temperature of a bearing, thereby realizing real-time monitoring of various experimental data when the rotor rotates.
With reference to fig. 5, the rotor consists of a shaft 3, a turbine 17, a thrust disk 13. Wherein the turbine 17 and the thrust disc 13 are mounted at both ends of the shaft 3, respectively.
With reference to fig. 1 and 2, the casing is provided with 4 through holes 22, 23, 28 and 29 which are arranged in a pairwise orthogonal manner, the eddy current displacement sensors 7, 8, 11 and 12 enter the inside of the casing through the through holes and are not in contact with the rotor, so that the non-contact displacement real-time measurement in the X, Y direction is realized, and the track of the rotor in the rotating process is obtained by processing data.
With reference to fig. 2 and 6, the pipe threaded interface 42 is connected with the threaded opening 43 of the turbine housing, the inner surface of the turbine housing is matched with the turbine 17 coaxially, high-pressure gas enters the annular cavity 51 of the turbine housing through the pipe threaded interface 42, 12 nozzles 44 are arranged on the inner wall of the annular cavity, the high-pressure gas is ejected from the nozzles and impacts the turbine 17, and enough driving torque is generated for the rotor, so that the turbine 17 drives the rotor to rotate.
With reference to fig. 1, 2 and 7, the housing is provided with screw holes 24, 25, 26 and 27 which are orthogonal in pairs, the bearing housing transition sleeve is provided with screw holes 54, 55, 56 and 57 which are orthogonal in pairs, the inner wall of the housing is matched with the bearing housing transition sleeves 9 and 10 and is concentrically aligned and positioned through the screw holes, the bearing housing transition sleeves 9 and 10 are positioned and clamped by the studs 15, 16, 18 and 19, and meanwhile, the gas foil radial bearings 47 and 48 in the bearing housing transition sleeves 9 and 10 are clamped, so that the looseness of the bearings in the experimental process is prevented.
With reference to fig. 2, 3 and 5, the turbine 17 rotates the whole rotor, the top foil of the shaft surface and the gas foil radial bearings 47 and 48 generates gas film pressure, the top foil 35 presses the convex foil 36 to generate elastic deformation, and the rotor is suspended in the gas foil radial bearings 47 and 48. The piezoelectric film sensor 34 on the top foil measures the air film pressure data in real time, recording the data in the measurement system.
Referring to fig. 2, 4 and 5, the thrust disk 13 is provided with a convex foil 40, a top foil 39 and a piezoelectric film sensor 38 to form a gas foil thrust bearing 52 capable of measuring the gas film pressure in real time, and similarly, the thrust bearing bush 14 is provided with the convex foil 40, the top foil 39 and the piezoelectric film sensor 38 to form a gas foil thrust bearing 53. When the rotor rotates, axial displacement can be generated, at the moment, air film pressure can be generated between the air foil thrust bearing and the rotor end face and between the air foil thrust bearing, the top foil extrudes the convex foil to generate elastic deformation, at the moment, the piezoelectric film sensor on the top foil can detect the air film pressure between the rotor end face and the air foil thrust bearing 52 and between the piezoelectric film sensor on the top foil and the air foil thrust bearings 52 and 53, and therefore functional diversification is achieved.
With reference to fig. 1, 2 and 4, through holes 29 and 30 are formed in the housing, and the circuit of the piezoelectric film sensor 38 can be led out through the through holes 29 and 30 and connected to the data processing port, so that real-time monitoring of the gas film pressure of the gas foil thrust bearing is realized, the circuit of the sensor for measuring the gas film 52 pressure of the gas foil thrust bearing is led out from the through hole 29, and the circuit of the sensor for measuring the gas film pressure of the gas foil thrust bearing 53 is led out from the through hole 30.
The present embodiment is merely illustrative of the present invention and not limiting, and it will be appreciated by those skilled in the art that modifications may be made to the present invention without departing from the spirit and scope of the invention, and it is intended to cover within the scope of the appended claims.
Claims (7)
1. A multifunctional gas foil bearing supporting rotor simulation test bed is characterized in that: the device comprises a supporting seat device, a power system, a bearing-rotor system and a testing system; the supporting seat device comprises a turbine shell supporting seat (4), a shell (1) and a front lower supporting seat (2); a shell (1) is arranged above the front lower support (2), is positioned through two positioning holes (33) and (45) of the shell (1), and is fixedly connected through bolts; the front end of the shell (1) is provided with a front end cover (20); the rear end of the shell is sequentially provided with a thrust bearing shaft sleeve (21), a clearance ring (46) and a rear end cover (14), and the thrust bearing shaft sleeve, the clearance ring and the rear end cover are fixedly connected through bolts; bearing transition layers (9) and (47) are arranged on two sides of the inner part of the shell (1); gas foil radial bearings (47) and (48) are respectively arranged in the bearing transition layer; the gas foil radial bearings (47), (48) support the rotor system at both ends, respectively; the rotor system comprises a shaft (3), a turbine (17), a thrust disc (13); the front end of the shaft is provided with a turbine (17), and the rear end of the shaft is provided with a thrust disc (13); the power system comprises a turbine (17), a turbine shell (6) and a turbine shell supporting seat (4) which are arranged on the rotor system; the turbine housing (6) is arranged on the turbine housing supporting seat (4), and is fixedly connected with the turbine housing through bolts and nuts, and the inner surface of the turbine housing (6) is matched with the turbine (17) through a concentric shaft; the test system comprises eddy current displacement sensors (7), (8), (11), (12), K-type thermocouple temperature sensors and piezoelectric film sensors (34), (38).
2. A multi-functional gas foil bearing supported rotor simulation test stand according to claim 1, wherein: the shell is provided with 4 through holes (22), (23), (28) and (29) which are arranged in a pairwise orthogonal mode; the opening directions of the through holes (22) and the through holes (28) are vertical, and the opening directions of the through holes (23) and the through holes (29) are horizontal; the eddy current displacement sensors (7), (8), (11), (12) are respectively inserted into the through holes.
3. A multi-functional gas foil bearing supported rotor simulation test stand according to claim 1, wherein: 2 screw holes (24) and (26) in the vertical direction and 2 screw holes (25) and (27) in the horizontal direction are formed in the shell; 2 threaded holes (49) and (50) are formed in the bearing transition layer; the threaded holes of the shell are respectively matched with the corresponding concentric shafts of the threaded holes (54), (55), (56) and (57) of the bearing transition layer through studs (15), (16), (18) and (19) and clamp the bearing.
4. A multi-functional gas foil bearing supported rotor simulation test stand according to claim 1, wherein: the foil gas radial bearings (48), (47) comprise a bearing shell (37), a convex foil (36) and a top foil (35); a piezoelectric film sensor (34) is arranged on the top foil (35); the foil gas thrust bearing (52) comprises a thrust disc (13), a convex foil (40) and a top foil (39); the thrust bearing (53) consists of a thrust bearing bush (41), a convex foil (40) and a top foil (39); a piezoelectric film sensor (38) is arranged on the top foil.
5. A multi-functional gas foil bearing supported rotor simulation test stand according to claim 4, wherein: the shell (1) is provided with through holes (29) and (30), and leads of the piezoelectric film sensor (38) are led out through the through holes (29) and (30).
6. A multi-functional gas foil bearing supported rotor simulation test stand according to claim 1, wherein: the housing is provided with a plane (51) lower than the lowest height of the air foil radial bearing, so that leads of the piezoelectric film sensor (34) and the K-type temperature sensor can be conveniently led out.
7. A multi-functional gas foil bearing supported rotor simulation test stand according to claim 1, wherein: an annular cavity (51) is arranged on a turbine housing supporting seat in the power system, an air inlet (43) is arranged outside the annular cavity (51), the annular cavity is connected with a pipe threaded joint (42), and 12 nozzles (44) are arranged inside the annular cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310516096.6A CN116558822A (en) | 2023-05-09 | 2023-05-09 | Multifunctional gas foil bearing supporting rotor simulation test bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310516096.6A CN116558822A (en) | 2023-05-09 | 2023-05-09 | Multifunctional gas foil bearing supporting rotor simulation test bed |
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| Publication Number | Publication Date |
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| CN116558822A true CN116558822A (en) | 2023-08-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202310516096.6A Pending CN116558822A (en) | 2023-05-09 | 2023-05-09 | Multifunctional gas foil bearing supporting rotor simulation test bed |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117189791A (en) * | 2023-11-07 | 2023-12-08 | 成都中科翼能科技有限公司 | Power turbine bearing casing assembly with sensor |
-
2023
- 2023-05-09 CN CN202310516096.6A patent/CN116558822A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117189791A (en) * | 2023-11-07 | 2023-12-08 | 成都中科翼能科技有限公司 | Power turbine bearing casing assembly with sensor |
| CN117189791B (en) * | 2023-11-07 | 2024-01-23 | 成都中科翼能科技有限公司 | Power turbine bearing casing assembly with sensor |
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