CN113530878A - Main shaft connecting structure of turbocharger - Google Patents
Main shaft connecting structure of turbocharger Download PDFInfo
- Publication number
- CN113530878A CN113530878A CN202110888065.4A CN202110888065A CN113530878A CN 113530878 A CN113530878 A CN 113530878A CN 202110888065 A CN202110888065 A CN 202110888065A CN 113530878 A CN113530878 A CN 113530878A
- Authority
- CN
- China
- Prior art keywords
- main shaft
- shaft
- thrust bearing
- triangular
- sleeve
- 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
- 229910000838 Al alloy Inorganic materials 0.000 abstract description 7
- 229910000831 Steel Inorganic materials 0.000 abstract description 5
- 239000010959 steel Substances 0.000 abstract description 5
- 239000003921 oil Substances 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
- F04D29/054—Arrangements for joining or assembling shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a turbocharger spindle connecting structure which comprises a spindle, a thrust bearing body, a pressure end shaft sleeve, a nut, a spindle bolt, a triangular shaft, a compressor impeller, a wheel disc, a central positioning table, a pin and a positioning surface, wherein the thrust bearing body is arranged on the spindle; one end of the main shaft is fixedly connected with the wheel disc through a pin, a central positioning table and a bolt, the other end of the main shaft is connected with the thrust bearing body and the end pressing shaft sleeve through a triangular shaft, positioning surfaces are arranged among the end pressing shaft sleeve, the main shaft and the thrust bearing body, the compressor impeller is connected with the main shaft through the end pressing shaft sleeve, the compressor impeller, the end pressing shaft sleeve and the thrust bearing body are axially pressed on the main shaft through a main shaft bolt, and a nut is arranged at one end of the main shaft bolt. The compressor impeller is in interference fit with the steel pressing end shaft sleeve and is positioned on the pressing end shaft sleeve together with the main shaft, so that the problems that an inner hole of the aluminum alloy compressor impeller with an old structure expands due to the centrifugal force when the rotor rotates, the aluminum alloy compressor impeller cannot be positioned with the main shaft and the like are solved, and the energy at the turbine end is transmitted to the compressor impeller through the connection of the main shaft to compress air.
Description
Technical Field
The invention relates to the field of diesel engine accessories, in particular to a main shaft connecting structure of a turbocharger.
Background
In the existing turbocharger rotor structure, a turbine wheel disc is positioned with a main shaft through a pin and a central positioning table, and the main shaft and the wheel disc are connected through bolts. The other end of the main shaft is assembled and connected through an impeller of the gas compressor to transmit torque. The bearing sleeve presses the upper part of the shaft by the transition fit of the bearing sleeve and the main shaft and by a main shaft nut. The air guide wheel and the impeller are connected into a working wheel of the gas compressor through the pin and the bushing in an interference fit manner. Therefore, the existing structure is complex in installation and structure, the positioning precision of a single part is poor, the dynamic balance of the rotor is greatly influenced, and the dynamic balance repeatability is poor; the impeller of the air compressor is positioned by adopting the inner hole and the main shaft, because the impeller of the air compressor is aluminum alloy, the inner hole expands under the action of centrifugal force when the rotor rotates, a gap is generated between the inner hole of the impeller of the air compressor and the lining, the dynamic unbalance of the rotor is increased, and the bearing burning loss and the fault are caused.
Disclosure of Invention
The invention provides a main shaft connecting structure of a turbocharger, which aims to solve the problem of increase of dynamic unbalance of a rotor.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a turbocharger spindle connection structure, characterized by comprising: the thrust bearing comprises a main shaft, a thrust bearing body, a pressure end shaft sleeve, a nut, a main shaft bolt, a triangular shaft and a compressor impeller;
triangular holes are formed in the thrust bearing body and the pressure end shaft sleeve;
one end of the main shaft is provided with a triangular shaft;
the thrust bearing body is connected with the triangular shaft through a triangular hole, the pressure end shaft sleeve is connected with the triangular shaft through a triangular hole, and the triangular shaft is connected with the main shaft through a bolt;
the compressor impeller and the pressure end shaft sleeve are assembled on the main shaft in an interference fit mode, the compressor impeller, the pressure end shaft sleeve and the thrust bearing body are sleeved on the main shaft and are tightly pressed on the main shaft through the main shaft bolt, and the nut is arranged at one end of the main shaft bolt.
Furthermore, the thrust bearing further comprises a positioning surface, and the positioning surface is arranged among the end pressing shaft sleeve, the main shaft and the thrust bearing body.
Furthermore, both ends of the main shaft bolt are provided with threads, and one end connected with the main shaft is also provided with a positioning table and a stopping table.
Furthermore, an oil blocking edge is arranged on the outer side, close to the turbine end, of the pressure end shaft sleeve.
Further, the oil blocking edge has an angle of 110-150 degrees relative to the thrust end face of the pressure end shaft sleeve.
Furthermore, the spindle bolt further comprises a flow guide sleeve, and the flow guide sleeve is located at one end, provided with the nut, of the spindle bolt.
Further, the flow guide sleeve is conical.
Furthermore, the outer end face of the pressure end shaft sleeve is reverse threads.
Furthermore, the flange surface of the nut is triangular, an inner hole is provided with threads, and the lower part of the flange surface is a cylindrical surface.
Furthermore, the device also comprises a central positioning table and a pin, wherein one end of the spindle is fixedly connected with the wheel disc through the pin and the central positioning table.
Further, the main shaft is connected with the turbine disc through a pin and the central positioning table.
Has the advantages that: the compressor impeller is in interference fit with the steel pressing end shaft sleeve, and is positioned on the pressing end shaft sleeve together with the main shaft, so that the problems that the dynamic unbalance is increased, the rotor rotates unstably, the bearing abrasion is aggravated or even fails and the like caused by the fact that an inner hole of the aluminum alloy compressor impeller with an old structure expands due to the centrifugal force and cannot be positioned with the main shaft when the rotor rotates are solved. The triangular shaft structure increases the shaft rigidity, the positioning and the processing among the main shaft, the pressure end shaft sleeve and the thrust bearing body can ensure the consistency of assembly, and the repeatability and the quality stability of the dynamic balance of the rotor are ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic cross-sectional view of the structure of the apparatus of the present invention;
FIG. 2 is a schematic view of the assembly of the rotor and the spindle of the apparatus of the present invention;
FIG. 3 is a schematic view of a locating surface of the present invention;
FIG. 4 is a triangular axial cross-sectional view of the present invention;
FIG. 5 is a schematic front view of the nut of the present invention;
FIG. 6 is a schematic side view of the nut of the present invention;
fig. 7 is a cross-sectional view of a pressure end sleeve of the present invention.
Wherein, 1, a main shaft; 2. a thrust bearing body; 3. a pressing end shaft sleeve; 4. a nut; 5. a spindle bolt; 6. a triangular shaft; 7. an air compressor impeller; 8. a flow guide sleeve; 9. a wheel disc; 10. a central positioning table; 11. a pin; 12. positioning the surface; 13. a positioning table; 14. a stop table; 15. oil blocking edges; 16. a thrust end face; 17. and (4) reverse threading.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment provides a turbocharger main shaft connecting structure, as shown in fig. 1 to 7, comprising: the method comprises the following steps: the thrust bearing comprises a main shaft 1, a thrust bearing body 2, a pressure end shaft sleeve 3, a nut 4, a main shaft bolt 5, a triangular shaft 6 and a compressor impeller 7;
triangular holes are formed in the thrust bearing body 2 and the pressure end shaft sleeve 3;
one end of the main shaft 1 is provided with a triangular shaft 6;
the thrust bearing body 2 is connected with the triangular shaft 6 through a triangular hole, the pressure end shaft sleeve 3 is connected with the triangular shaft 6 through a triangular hole, and the triangular shaft 6 is connected with the main shaft bolt 5;
the compressor impeller 7 and the pressure end shaft sleeve 3 are assembled on the main shaft 1 in an interference fit mode, the compressor impeller 7, the pressure end shaft sleeve 3 and the thrust bearing body 2 are sleeved on the main shaft 1 and are tightly pressed on the main shaft 1 through the main shaft bolt 5, and the nut 4 is arranged at one end of the main shaft bolt 5.
The compressor impeller is in interference fit with the steel pressing end shaft sleeve, and is positioned on the pressing end shaft sleeve together with the main shaft, so that the problems that the dynamic unbalance is increased, the rotor rotates unstably, the bearing abrasion is aggravated or even fails and the like caused by the fact that an inner hole of the aluminum alloy compressor impeller with an old structure expands due to the centrifugal force and cannot be positioned with the main shaft when the rotor rotates are solved.
In the specific embodiment, the compressor impeller 7 and the main shaft 1 are positioned through the steel pressing end shaft sleeve 3, so that the problem that the inner hole of the aluminum alloy compressor impeller in the old scheme is deformed (the hole is expanded, the hole diameter is enlarged, interference is changed into excessive connection, and the dynamic unbalance is enlarged) and cannot be accurately positioned is solved.
The compressor impeller is in interference fit with the steel pressing end shaft sleeve, and is positioned on the pressing end shaft sleeve together with the main shaft, so that the problems that the dynamic unbalance is increased, the rotor rotates unstably, the bearing abrasion is aggravated or even fails and the like caused by the fact that an inner hole of the aluminum alloy compressor impeller with an old structure expands due to the centrifugal force and cannot be positioned with the main shaft when the rotor rotates are solved. The triangular shaft structure increases the shaft rigidity, the positioning and the processing among the main shaft, the pressure end shaft sleeve and the thrust bearing body can ensure the consistency of assembly, and the repeatability and the quality stability of the dynamic balance of the rotor are ensured.
In the specific embodiment, the thrust bearing further comprises a positioning surface 12, and the positioning surface 12 is arranged among the pressure end sleeve 3, the spindle 1 and the thrust bearing body 2. The positioning surface 12 is used for ensuring the concentricity of the pressure end shaft sleeve and the impeller during assembly, and the accuracy of dynamic unbalance during rotation during assembly of the thrust bearing body and the main shaft, and reducing the influence of assembly on rotor unbalance.
In the embodiment, the spindle bolt 5 has threads at both ends, wherein a positioning table 13 and a stop table 14 are further provided at one end connected with the spindle 1.
In a specific embodiment, the pressure end sleeve 3 is provided with an oil baffle 15 near the outer side of the turbine end for sealing the lubricating oil from the bearing.
In a specific embodiment, the oil baffle 15 has an angle of 110 ° to 150 ° with respect to the thrust end face 16 of the pressure end sleeve 3.
In a specific embodiment, one end of the spindle bolt 5, which is provided with the nut 4, is provided with 1 flow guide sleeve 8, the outer surface of which is conical, so that air flow entering the compressor impeller is smooth, and the flow guide sleeve 8 is screwed on the spindle bolt 5.
In a specific embodiment, the spindle bolt 5 is a long bolt. The long bolt elastically deforms to enable the main shaft 1 and the compressor impeller 7 to be assembled and pressed tightly.
In a specific embodiment, the outer end face of the pressure end shaft sleeve 3 is reverse thread and can be used for lubricating oil sealing.
In the specific embodiment, the flange surface of the nut 4 is triangular for disassembly; the inner hole is a thread, the main shaft bolt 5 is screwed on the inner hole to tightly press the assembly, the lower part of the flange surface is a cylindrical surface, and the compressor impeller 7 is positioned in an auxiliary mode.
In a particular embodiment, the spindle 1 is connected to a turbine disk by means of pins and the centering station 10.
In the specific embodiment, the spindle further comprises a center positioning table 10 and a pin 11, and one end of the spindle 1 is fixedly connected with the wheel disc 9 through the pin 11 and the center positioning table 10. The main shaft 1 is connected with a turbine disc through a pin and the central positioning table 10.
By using the connecting structure of the main shaft of the turbocharger, in actual work, when a rotor dynamic balance test is repeatedly carried out, the difference of the residual unbalance amount at every interval is reduced from more than 1g to about 0.2g, the vibration value and the stability of the turbocharger in the test are improved, through statistics, the one-time qualification rate of batch turbocharger platform delivery tests is improved from 70-80% to 80-90%, the bearing burning failure rate is reduced from 5% to within 1%, and the maintenance period is prolonged from 2 years (or 30 km) to 5 years (90 km).
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention will be understood by reference to the foregoing embodiments: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A turbocharger spindle connection structure, characterized by comprising: the thrust bearing comprises a main shaft (1), a thrust bearing body (2), a pressure end shaft sleeve (3), a nut (4), a main shaft bolt (5), a triangular shaft (6) and a compressor impeller (7);
triangular holes are formed in the thrust bearing body (2) and the pressure end shaft sleeve (3);
one end of the main shaft (1) is provided with a triangular shaft (6);
the thrust bearing body (2) is connected with the triangular shaft (6) through a triangular hole, the pressure end shaft sleeve (3) is connected with the triangular shaft (6) through a triangular hole, and the triangular shaft (6) is connected with the spindle bolt (5);
the air compressor impeller (7) and the pressure end shaft sleeve (3) are assembled on the main shaft (1) in an interference fit mode, the air compressor impeller (7), the pressure end shaft sleeve (3) and the thrust bearing body (2) are sleeved on the main shaft (1) and are pressed on the main shaft (1) through the main shaft bolt (5), and the nut (4) is arranged at one end of the main shaft bolt (5).
2. A turbocharger main shaft connecting structure as defined in claim 1, wherein: the thrust bearing further comprises a positioning surface (12), wherein the positioning surface (12) is arranged among the end pressing shaft sleeve (3), the main shaft (1) and the thrust bearing body (2).
3. A turbocharger main shaft connecting structure as defined in claim 2, wherein: the two ends of the main shaft bolt (5) are provided with threads, and one end connected with the main shaft (1) is also provided with a positioning table (13) and a stopping table (14).
4. A turbocharger main shaft connecting structure according to claim 3, wherein: the oil retaining side (15) is arranged on the outer side, close to the turbine end, of the pressure end shaft sleeve (3), and the angle of the oil retaining side (15) relative to the thrust end face (16) of the pressure end shaft sleeve (3) is 110-150 degrees.
5. A turbocharger main shaft connecting structure according to claim 4, wherein: the spindle bolt is characterized by further comprising a flow guide sleeve (8), wherein the flow guide sleeve (8) is located at one end, provided with the nut (4), of the spindle bolt (5).
6. A turbocharger main shaft connecting structure according to claim 5, wherein: the flow guide sleeve (8) is conical.
7. A turbocharger main shaft connecting structure according to claim 6, wherein: the outer end face of the pressure end shaft sleeve (3) is provided with a reverse thread (17).
8. A turbocharger main shaft connecting structure according to claim 7, wherein: the flange surface of the nut (4) is triangular, an inner hole is provided with threads, and the lower part of the flange surface is a cylindrical surface.
9. A turbocharger main shaft connecting structure according to claim 8, wherein: the spindle is characterized by further comprising a center positioning table (10) and a pin (11), wherein one end of the spindle (1) is fixedly connected with the wheel disc (9) through the pin (11) and the center positioning table (10).
10. A turbocharger main shaft connecting structure according to claim 9, wherein: the main shaft (1) is connected with the central positioning table (10) through a pin to form a turbine disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110888065.4A CN113530878B (en) | 2021-08-03 | 2021-08-03 | Main shaft connecting structure of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110888065.4A CN113530878B (en) | 2021-08-03 | 2021-08-03 | Main shaft connecting structure of turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113530878A true CN113530878A (en) | 2021-10-22 |
| CN113530878B CN113530878B (en) | 2024-06-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110888065.4A Active CN113530878B (en) | 2021-08-03 | 2021-08-03 | Main shaft connecting structure of turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113530878B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114278606A (en) * | 2021-12-28 | 2022-04-05 | 北京动力机械研究所 | Multi-working-medium helium gas compressor main shaft structure |
| CN114941661A (en) * | 2022-06-13 | 2022-08-26 | 贵州永红航空机械有限责任公司 | Combined shaft for dynamic balance test of oil mist separator impeller |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200949485Y (en) * | 2006-09-05 | 2007-09-19 | 大连经济技术开发区泽通机械有限公司 | Improvement of turbocharger structure used in vehicle diesel engine |
| CN107387174A (en) * | 2017-07-25 | 2017-11-24 | 湖南天雁机械有限责任公司 | Turbocharger with angular contact ceramic ball bearing |
| CN207297108U (en) * | 2017-10-10 | 2018-05-01 | 大连恒通机车配件有限公司 | A kind of rotor structure of exhaust-driven turbo-charger exhaust-gas turbo charger |
| CN112360573A (en) * | 2020-10-26 | 2021-02-12 | 北京动力机械研究所 | Compact radial flow turbine thermoelectric conversion system rotating assembly |
| CN112360574A (en) * | 2020-10-26 | 2021-02-12 | 北京动力机械研究所 | Rotating assembly structure of high-speed low-stress turbine power generation system |
| CN215719752U (en) * | 2021-08-03 | 2022-02-01 | 中车大连机车研究所有限公司 | Main shaft connecting structure of turbocharger |
-
2021
- 2021-08-03 CN CN202110888065.4A patent/CN113530878B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200949485Y (en) * | 2006-09-05 | 2007-09-19 | 大连经济技术开发区泽通机械有限公司 | Improvement of turbocharger structure used in vehicle diesel engine |
| CN107387174A (en) * | 2017-07-25 | 2017-11-24 | 湖南天雁机械有限责任公司 | Turbocharger with angular contact ceramic ball bearing |
| CN207297108U (en) * | 2017-10-10 | 2018-05-01 | 大连恒通机车配件有限公司 | A kind of rotor structure of exhaust-driven turbo-charger exhaust-gas turbo charger |
| CN112360573A (en) * | 2020-10-26 | 2021-02-12 | 北京动力机械研究所 | Compact radial flow turbine thermoelectric conversion system rotating assembly |
| CN112360574A (en) * | 2020-10-26 | 2021-02-12 | 北京动力机械研究所 | Rotating assembly structure of high-speed low-stress turbine power generation system |
| CN215719752U (en) * | 2021-08-03 | 2022-02-01 | 中车大连机车研究所有限公司 | Main shaft connecting structure of turbocharger |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114278606A (en) * | 2021-12-28 | 2022-04-05 | 北京动力机械研究所 | Multi-working-medium helium gas compressor main shaft structure |
| CN114941661A (en) * | 2022-06-13 | 2022-08-26 | 贵州永红航空机械有限责任公司 | Combined shaft for dynamic balance test of oil mist separator impeller |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113530878B (en) | 2024-06-04 |
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