CN117345770A - Air inlet cabin system of air compressor tester - Google Patents
Air inlet cabin system of air compressor tester Download PDFInfo
- Publication number
- CN117345770A CN117345770A CN202311648391.3A CN202311648391A CN117345770A CN 117345770 A CN117345770 A CN 117345770A CN 202311648391 A CN202311648391 A CN 202311648391A CN 117345770 A CN117345770 A CN 117345770A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- sliding shoe
- semi
- inlet cabin
- support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000008093 supporting effect Effects 0.000 claims abstract description 21
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 4
- 230000003746 surface roughness Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 17
- 239000004519 grease Substances 0.000 abstract description 7
- 230000001050 lubricating effect Effects 0.000 abstract description 7
- 238000006073 displacement reaction Methods 0.000 abstract description 6
- 238000003754 machining Methods 0.000 abstract description 4
- 238000010521 absorption reaction Methods 0.000 abstract description 2
- 108010066114 cabin-2 Proteins 0.000 description 10
- 238000007789 sealing Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0629—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a liquid cushion, e.g. oil cushion
- F16C32/064—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a liquid cushion, e.g. oil cushion the liquid being supplied under pressure
- F16C32/0651—Details of the bearing area per se
- F16C32/0655—Details of the bearing area per se of supply openings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0681—Construction or mounting aspects of hydrostatic bearings, for exclusively rotary movement, related to the direction of load
- F16C32/0685—Construction or mounting aspects of hydrostatic bearings, for exclusively rotary movement, related to the direction of load for radial load only
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/02—Parts of sliding-contact bearings
- F16C33/04—Brasses; Bushes; Linings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M5/00—Engine beds, i.e. means for supporting engines or machines on foundations
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to the technical field of compressor tests, and discloses an air inlet cabin system of a compressor tester, which can realize the absorption of machining or mounting errors of an air inlet cabin in a thermal expansion process, so that the problem of angular displacement caused by asymmetric radial thermal deformation of two sides is avoided; in the thermal deformation process, the air inlet chamber realizes radial free expansion through the upper slide shoe and the lower slide shoe which are matched with each other by the end surfaces, and the air inlet chamber realizes directional expansion under the supporting action in the axial direction, so that the axial position of the air inlet chamber is not changed, and the coaxiality of the whole air inlet chamber is not changed; an oil film is formed between the upper sliding shoe and the lower sliding shoe, so that the upper sliding shoe and the lower sliding shoe can move relatively easily when the air inlet cabin is freely expanded due to high temperature of air inlet, the oil film pressure between the upper sliding shoe and the lower sliding shoe is changed due to the change of the viscosity of lubricating grease due to the change of temperature, dry friction between the upper sliding shoe and the lower sliding shoe is prevented, and the symmetrical free expansion of the left side and the right side of the air inlet cabin is further ensured.
Description
Technical Field
The invention relates to the technical field of compressor tests and discloses an air inlet cabin system of a compressor tester.
Background
The conventional air compressor test adopts an open atmosphere air inlet mode, and in the test process, the whole air inlet system is at the atmospheric environment temperature, so that the thermal deformation condition is hardly generated; meanwhile, the air inlet cabin of the air inlet system is usually connected with the tested air compressor through a rubber plate, and due to the fact that the rubber plate is large in plastic deformation, when the coaxiality of the air inlet cabin and the tested air compressor is deviated, displacement deviation generated by different axes can be absorbed by the rubber plate.
However, the working temperature range of the air inlet chamber of the warming and pressurizing compressor tester is up to 600K, and in the temperature change process, the air inlet chamber generates axial change quantity of about 20mm and radial change quantity of about 10mm, and the machining or mounting errors can cause asymmetric thermal expansion of the air inlet chamber, so that the test risk of the compressor is increased. And the temperature resistance of the rubber plate is generally not more than 50 ℃ because the temperature reaches 600K, and the requirement of a heating and pressurizing test cannot be met. Therefore, in the prior art, a non-contact sealing structure is designed between an air inlet cabin of the heating and pressurizing air compressor tester and the tested air compressor, but the radial deformation amount which can be absorbed by the structure is limited, when the axial lead change of the air inlet cabin exceeds the bearing capacity of the non-contact sealing structure, the non-contact sealing structure can transmit the axial lead change of the air inlet cabin to the tested air compressor, so that the front and rear different axialities of the tested air compressor are increased, and the safety of the air compressor in high-speed operation is further influenced.
Disclosure of Invention
The invention aims to provide an air inlet cabin system of a compressor tester, which can absorb the processing or mounting errors of an air inlet cabin in the thermal expansion process, and can realize the absorption of the processing or mounting errors of the air inlet cabin in the thermal expansion process, so that the problem of angular displacement caused by asymmetric radial thermal deformation of two sides is avoided; the axis position of the air inlet cabin is not changed, the coaxiality of the whole air inlet cabin is not changed, the contact area of the supporting surface is ensured, and the damage of the support is avoided.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
the air inlet cabin system of the air compressor tester comprises a base, a support frame and an air inlet cabin, wherein the air inlet cabin is arranged on the base through the support frame; the support frame comprises a fixed support arranged on the base and longitudinal rib plates axially arranged on the outer walls of two sides of the air inlet cabin along the air inlet cabin, a support plate is fixedly arranged on each longitudinal rib plate, and each support plate is movably arranged on the fixed support through a hinged support; an upper sliding shoe is fixed on each supporting plate, a lower sliding shoe is arranged on the end surface of each hinged support matched with the supporting plate, the upper sliding shoe is matched with the lower sliding shoe in an end surface manner, oil grooves which are communicated with each other are formed in the end surface of the lower sliding shoe matched with the upper sliding shoe, an oil injection nozzle communicated with the oil grooves is further arranged on the lower sliding shoe, and a plug is arranged on the oil injection nozzle; the two supporting plates are symmetrically distributed along the longitudinal central section of the air inlet cabin, the contact surface between the upper sliding shoe and the corresponding lower sliding shoe is coplanar with the axis of the air inlet cabin, and the included angle between the contact surfaces at the two sides of the air inlet cabin is 120 degrees.
Further, the surface roughness of the upper slide shoe and the lower slide shoe is smaller than R1.6.
Further, each hinge support comprises a hinge support fixed on the fixed support, a semi-cylindrical groove is formed in the hinge support, a hinge joint matched with the semi-cylindrical groove is arranged in the semi-cylindrical groove, a mounting block is arranged at one end, far away from the semi-cylindrical groove, of the hinge joint, and the lower sliding shoe is fixed on the mounting block through a screw.
Further, the semi-cylindrical grooves and the hinge joint contacted with the semi-cylindrical grooves are smaller than R1.6 in roughness.
Further, the depth of the semi-cylindrical groove is 87% of the radius of the semi-cylindrical groove; the diameter tolerance of the semi-cylindrical groove is between 0mm and 0.2mm, and the diameter tolerance of the semi-cylindrical surface of the hinge joint is between-0.2 mm and-0.1 mm.
Further, a reinforcing rib plate is arranged between the longitudinal rib plate and the supporting plate.
Compared with the prior art, the invention has the following beneficial effects:
1. the supporting plate on the longitudinal rib plate is arranged on the base through the hinged support, and supports the whole air inlet cabin, so that the air inlet cabin can absorb machining or installation errors in the thermal expansion process, and the problem of angular displacement caused by asymmetric radial thermal deformation of two sides is avoided.
2. The plane where the contact surfaces of the upper sliding shoe and the lower sliding shoe are positioned passes through the axis of the air inlet cabin, the included angle between the contact surfaces on two sides of the air inlet cabin is 120 degrees, when the air inlet temperature in the test process is up to 600K, the air inlet cabin realizes radial free expansion through the upper sliding shoe and the lower sliding shoe matched with the end surfaces in the thermal deformation process, the axial direction realizes directional expansion under the supporting effect, the axis position of the air inlet cabin is not changed, the coaxiality of the whole air inlet cabin is not changed, the contact area of the supporting surface is also ensured, and the support is prevented from being damaged.
3. In the radial expansion process, lubricating grease in the oil groove is brought into the contact surface of the upper sliding shoe and the lower sliding shoe, so that an oil film is formed between the upper sliding shoe and the lower sliding shoe, and the upper sliding shoe and the lower sliding shoe are easy to move relatively when the air inlet cabin is freely expanded due to high temperature of air inlet; and heat generated during the high-temperature test of air inlet is conducted to the lower slide shoe, and the viscosity of the lubricating grease changes the oil film pressure between the upper slide shoe and the lower slide shoe due to the change of the temperature, so that dry friction between the upper slide shoe and the lower slide shoe is prevented, and the left side and the right side of the air inlet cabin are further ensured to realize symmetrical free expansion.
Drawings
FIG. 1 is a schematic diagram of an air inlet cabin system of an air compressor tester according to an embodiment;
FIG. 2 is a schematic diagram of a cross-sectional structure of an air inlet cabin system of an air compressor tester according to an embodiment;
FIG. 3 is a schematic view of a mounting structure of a base and a fixing support in an embodiment;
FIG. 4 is a schematic view of a hinge base according to an embodiment;
1, a base; 2. an intake chamber; 3. a fixed support; 4. longitudinal rib plates; 5. a support plate; 6. a sliding shoe is arranged on the upper part; 7. a lower slide shoe; 8. an oil groove; 9. an anchor bolt; 10. a plug; 11. a hinged support; 12. a semi-cylindrical recess; 13. a hinge joint; 14. a mounting block; 15. reinforcing rib plates.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Examples
Referring to fig. 1-4, an air inlet cabin system of a compressor tester comprises a base 1, a support frame and an air inlet cabin, wherein the air inlet cabin is installed on the base 1 through the support frame; the support frame comprises a fixed support 3 arranged on the base 1 and longitudinal rib plates 4 arranged on the outer walls of two sides of the air inlet cabin along the axial direction of the air inlet cabin, a support plate 5 is fixedly arranged on each longitudinal rib plate 4, and each support plate 5 is movably arranged on the fixed support 3 through a hinged support; an upper slide shoe 6 is fixed on each supporting plate 5, a lower slide shoe 7 is arranged on the end surface of each hinged support matched with the supporting plate 5, the upper slide shoe 6 is matched with the lower slide shoe 7 in an end surface manner, oil grooves 8 which are communicated with each other are arranged on the end surface of the lower slide shoe 7 matched with the upper slide shoe 6, an oil filling nozzle communicated with the oil grooves 8 is further arranged on the lower slide shoe 7, and a plug 10 is arranged on the oil filling nozzle; the two support plates 5 are symmetrically distributed along the longitudinal central section of the air intake cabin, the contact surface between the upper sliding shoe 6 and the corresponding lower sliding shoe 7 is coplanar with the axis of the air intake cabin 2, and the included angle between the contact surfaces at the two sides of the air intake cabin is 120 degrees.
In the embodiment, a base 1 is fixed on a horizontal foundation by adopting foundation bolts 9, a hinged support is fixed on the base 1 by adopting hexagonal bolts, two longitudinal rib plates 4 are respectively positioned at the left side and the right side of an air inlet chamber 2 of the air compressor tester, and a pair of longitudinal rib plates are respectively symmetrically distributed at the front end and the rear end which are close to the air inlet chamber 2; the supporting plate 5 on the longitudinal rib plate 4 is arranged on the base 1 through a hinged support, and supports the whole air inlet cabin 2, so that the air inlet cabin 2 can absorb the machining or mounting errors in the thermal expansion process, and the problem of angular displacement caused by asymmetric radial thermal deformation of two sides is avoided; the plane where the contact surfaces of the upper slide shoe 6 and the lower slide shoe 7 are positioned passes through the axis of the air inlet cabin 2, the included angle between the contact surfaces at the two sides of the air inlet cabin is 120 degrees, when the air inlet temperature in the test process is up to 600K, the air inlet cabin 2 realizes radial free expansion through the upper slide shoe 6 and the lower slide shoe 7 matched with the end surfaces in the thermal deformation process, the axial direction realizes directional expansion under the supporting effect, the axis position of the air inlet cabin 2 is not changed, the coaxiality of the whole air inlet cabin 2 is not changed, the contact area of the supporting surface is ensured, and the support is prevented from being damaged; in addition, criss-cross oil grooves 8 are distributed on the end face of the lower slide shoe 7, an oil nozzle is arranged on the side face of the lower slide shoe 7, lubricating grease is injected into the lower slide shoe 7 from the oil nozzle, the lubricating grease is filled in the oil grooves 8 on the surface of the lower slide shoe 7, the lubricating grease in the oil grooves 8 is brought into the contact surface of the upper slide shoe 6 and the lower slide shoe 7 in the radial expansion process, an oil film is formed between the upper slide shoe 6 and the lower slide shoe 7, and the upper slide shoe 6 and the lower slide shoe 7 are easy to move relatively when the air inlet cabin 2 expands freely due to high air inlet temperature; and heat generated during the high-temperature test of air inlet is conducted to the lower slide shoe 7, and the viscosity of lubricating grease changes the oil film pressure between the upper slide shoe 6 and the lower slide shoe 7 due to the change of temperature, so that dry friction between the upper slide shoe 6 and the lower slide shoe 7 is prevented, and the left side and the right side of the air inlet cabin 2 are further ensured to realize symmetrical free expansion.
In this embodiment, the surface roughness of the upper sliding shoe 6 and the lower sliding shoe 7 is smaller than R1.6, so as to reduce the friction coefficient of the contact surface between the upper sliding shoe 6 and the lower sliding shoe 7 in the thermal deformation expansion process.
Each hinge support in this embodiment includes a hinge support 11 fixed on the fixed support 3, a semi-cylindrical groove 12 is provided on the hinge support 11, a hinge joint 13 matched with the semi-cylindrical groove 12 is installed in the semi-cylindrical groove 12, a mounting block 14 is provided at one end of the hinge joint 13 far away from the semi-cylindrical groove 12, and the lower sliding shoe 7 is fixed on the mounting block 14 through a screw, so as to realize movable installation of the support plate 5 and absorb angular deformation. In addition, the roughness of the semi-cylindrical surface of the semi-cylindrical groove 12 and the semi-cylindrical surface of the hinge 13 contacting with the semi-cylindrical groove 12 are smaller than R1.6, so that the surface friction coefficient in the thermal deformation axial expansion process can be reduced, and the support plate 5 can absorb angular deformation.
The depth of the semi-cylindrical groove 12 is 87% of the radius of the semi-cylindrical groove 12, the diameter tolerance of the semi-cylindrical groove 12 is between 0mm and 0.2mm, the diameter tolerance of the semi-cylindrical surface of the hinge joint 13 is between-0.2 mm and-0.1 mm, and the support plate 5 can absorb the angular displacement of the hinge joint 13.
In this embodiment, the reinforcing rib plates 15 are disposed between the longitudinal rib plates 4 and the supporting plate 5, so that the connection rigidity between the longitudinal rib plates 4 and the supporting plate 5 can be increased, and the overall stability of the supporting structure of the air inlet cabin 2 is ensured.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (6)
1. The air inlet cabin system of the air compressor tester is characterized by comprising a base (1), a support frame and an air inlet cabin, wherein the air inlet cabin is arranged on the base (1) through the support frame; the support frame comprises a fixed support (3) arranged on the base (1) and longitudinal rib plates (4) axially arranged on the outer walls of two sides of the air inlet cabin along the air inlet cabin, a support plate (5) is fixedly arranged on each longitudinal rib plate (4), and each support plate (5) is movably arranged on the fixed support (3) through a hinged support; an upper sliding shoe (6) is fixed on each supporting plate (5), a lower sliding shoe (7) is arranged on the end face of each hinged support matched with the supporting plate (5), the upper sliding shoe (6) is matched with the lower sliding shoe (7) in an end face manner, oil grooves (8) which are communicated with each other are formed in the end face of the lower sliding shoe (7) matched with the upper sliding shoe (6), an oil injection nozzle which is communicated with the oil grooves (8) is further arranged on the lower sliding shoe (7), and a plug (10) is arranged on the oil injection nozzle; the two supporting plates (5) are symmetrically distributed along the longitudinal central section of the air inlet cabin, the contact surface between the upper sliding shoe (6) and the corresponding lower sliding shoe (7) is coplanar with the axis of the air inlet cabin (2), and the included angle between the contact surfaces at the two sides of the air inlet cabin is 120 degrees.
2. The compressor tester intake compartment system of claim 1, wherein the surface roughness of both the upper slide shoe (6) and the lower slide shoe (7) is less than R1.6.
3. The air inlet cabin system of the air compressor tester according to claim 1, wherein each hinged support comprises a hinged support (11) fixed on the fixed support (3), a semi-cylindrical groove (12) is arranged on the hinged support (11), a hinge joint (13) matched with the semi-cylindrical groove (12) is arranged in the semi-cylindrical groove (12), a mounting block (14) is arranged at one end of the hinge joint (13) far away from the semi-cylindrical groove (12), and the lower sliding shoe (7) is fixed on the mounting block (14) through screws.
4. A compressor tester intake compartment system according to claim 3, wherein the semi-cylindrical recess (12) and the hinge joint (13) in contact with the semi-cylindrical recess (12) each have a semi-cylindrical surface roughness less than R1.6.
5. A compressor tester intake compartment system according to claim 3, wherein the depth of the semi-cylindrical recess (12) is 87% of the radius of the semi-cylindrical recess (12); the diameter tolerance of the semi-cylindrical groove (12) is between 0mm and 0.2mm, and the diameter tolerance of the semi-cylindrical surface of the hinge joint (13) is between-0.2 mm and-0.1 mm.
6. The air inlet cabin system of the compressor tester according to claim 1, characterized in that a reinforcing rib plate (15) is arranged between the longitudinal rib plate (4) and the supporting plate (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311648391.3A CN117345770B (en) | 2023-12-05 | 2023-12-05 | Air inlet cabin system of air compressor tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311648391.3A CN117345770B (en) | 2023-12-05 | 2023-12-05 | Air inlet cabin system of air compressor tester |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117345770A true CN117345770A (en) | 2024-01-05 |
| CN117345770B CN117345770B (en) | 2024-02-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311648391.3A Active CN117345770B (en) | 2023-12-05 | 2023-12-05 | Air inlet cabin system of air compressor tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117345770B (en) |
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| CN113390646A (en) * | 2021-07-13 | 2021-09-14 | 哈尔滨工业大学 | Test device and test method for simulating tilting pad bearing and pad beating fault of tilting pad bearing of heavy gas turbine |
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