CN217586154U - Dynamic balancing device for aero-engine compressor rotor - Google Patents
Dynamic balancing device for aero-engine compressor rotor Download PDFInfo
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- CN217586154U CN217586154U CN202221167998.0U CN202221167998U CN217586154U CN 217586154 U CN217586154 U CN 217586154U CN 202221167998 U CN202221167998 U CN 202221167998U CN 217586154 U CN217586154 U CN 217586154U
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- shaft sleeve
- positioning shaft
- compressor
- compressor rotor
- dynamic balancing
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Abstract
The utility model discloses an aeroengine compressor rotor dynamic balance device, include: the first positioning shaft sleeve is in interference connection with the front end of a compressor shaft of the compressor rotor; the second positioning shaft sleeve is in interference connection with the rear end of the compressor shaft of the compressor rotor; the bearing is sleeved on the second positioning shaft sleeve and is in interference connection with the second positioning shaft sleeve; the bearing connecting support is arranged on the dynamic balancing machine; wherein: the first positioning shaft sleeve is placed on a V-shaped mounting block of the dynamic balancing machine and is driven to rotate by a belt; the bearing connecting support extends to the interior of the compressor disk and is connected with the bottom of the bearing. The problem of current aeroengine compressor rotor balancing unit can produce great dynamic unbalance amount, and the dynamic balance data of rotor causes the experiment failure when influencing dynamic balance test is solved.
Description
Technical Field
The invention belongs to the field of machining of aero-engine rotors, and relates to a dynamic balancing device for an aero-engine compressor rotor.
Background
The dynamic balancing work of the rotor of the aircraft engine is an important technological process in the rotor assembly process, the unbalance amount of the rotor exceeds the allowable unbalance amount to cause larger vibration of the engine, and the whole rotor assembly needs to be dynamically balanced after the assembly is finished, so that the dynamic balance amount of the rotor is improved. The stators and the rotors at all levels of the multistage axial flow compressor are sequentially assembled one by one, after the assembly is finished, the stators and the rotors form a soft connected whole, certain play quantity exists in the axial direction and the radial direction, but the stators and the rotors cannot be completely separated, so that the rotors of the compressor cannot be independently taken out for a dynamic balance test, a special dynamic balance tool needs to be designed to fix an engine stator shaft for the dynamic balance test, and the dynamic unbalance is eliminated.
At present, a long mandrel penetrates through a rotor of a compressor rotor balancing device of an aero-engine, and a positioning sleeve is assembled at two ends of the mandrel and connected with a dynamic balancing machine. The aero-engine compressor rotor balancing device compresses the positioning sleeve by using the screws to be matched with the pressing blocks, and the positioning sleeve is in clearance fit connection with the pressing blocks to fix the long mandrel and the rotor. This construction requires a long spindle through the rotor, which, due to its excessive length, produces a large deflection of the shaft under its own weight. The deflection of the long mandrel can generate larger downward displacement, and further can generate larger dynamic unbalance amount when the shaft rotates, so that the measurement of the unbalance amount of the engine rotor is influenced. Due to the existence of deflection, the processing coaxiality of the long mandrel is difficult to ensure; secondly, clearance fit is used in the middle of the tool part, unbalance is caused by the defects of bolts used for connecting the parts, and when a dynamic balance test is carried out, the long mandrel can generate larger dynamic unbalance, so that the dynamic balance test of the rotor of the gas compressor fails.
Disclosure of Invention
In order to solve the problems, the invention provides a dynamic balancing device for an aircraft engine compressor rotor, which aims to solve the problem that the conventional dynamic balancing device for the aircraft engine compressor rotor can generate larger dynamic unbalance amount, so that the dynamic balance data of the rotor during a dynamic balance test is influenced to cause experimental failure.
The technical scheme adopted by the invention is that the dynamic balancing device for the compressor rotor of the aircraft engine comprises:
the first positioning shaft sleeve is in interference connection with the front end of a compressor shaft of the compressor rotor;
the second positioning shaft sleeve is in interference connection with the rear end of the compressor shaft of the compressor rotor;
the bearing is sleeved on the second positioning shaft sleeve and is in interference connection with the second positioning shaft sleeve;
the bearing connecting support is arranged on the dynamic balancing machine;
wherein:
the first positioning shaft sleeve is placed on a V-shaped mounting block of the dynamic balancing machine and is driven to rotate by a belt;
the bearing connecting support extends to the interior of the compressor disk and is connected with the bottom of the bearing.
The invention has the beneficial effects that: the two tin bronze positioning shaft sleeves are respectively in interference connection with the front end and the rear end of a compressor shaft of a compressor rotor correspondingly, the tin bronze positioning shaft sleeve in interference connection with the rear end of the compressor shaft is in interference connection with a bearing, the bearing is fixedly connected with a dynamic balancing machine through a bearing connecting support, deflection of the two tin bronze positioning shaft sleeves is effectively avoided, due to the fact that the tin bronze positioning shaft sleeves are short in size, the problem that dynamic unbalance generated by deflection due to the fact that a long mandrel is used affects an experiment result is avoided, and the problem that the experiment failure is caused by dynamic balance data of a rotor when an existing aircraft engine compressor rotor balancing device is affected due to the fact that the large dynamic unbalance can be generated is solved. Simultaneously, do not use the effectual product manufacturing cost that has reduced of long mandrel, through location axle sleeve dismounting device and the cooperation of tin bronze location axle sleeve, can not cause the part damage when dismantling tin bronze location axle sleeve from the part smoothly with screw thread torsion for tin bronze location axle sleeve reuse.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a dynamic balancing device of an aircraft engine compressor rotor.
Fig. 2 is a schematic structural diagram of the dismounting device.
In the figure, 1, a first positioning shaft sleeve, 2, a second positioning shaft sleeve, 3, a bearing, 4, a bearing connecting support, 5, a clamping jaw, 6, a connecting rod, 7, an ejector rod, 8, a threaded sleeve and 9, an ejector block.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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 dynamic balancing device for an aircraft engine compressor rotor, as shown in fig. 1, a first positioning shaft sleeve 1 and a second positioning shaft sleeve 2 are directly connected with the front end and the rear end of a compressor shaft of the compressor rotor, the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are heated to expand inner holes of the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 through a thermal assembly method, the inner holes of the first positioning shaft sleeve 1 and the second positioning shaft sleeve are matched with the two ends of the compressor shaft of the compressor rotor, and when the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are cooled and shrunk, the matching shaft surface of the compressor shaft of the compressor rotor is tightly embraced, and gapless interference fit is achieved. The first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are directly connected with the compressor shaft of the compressor rotor in an interference fit mode to replace a long shaft, so that the processing difficulty is reduced, the influence of a dynamic balance device of the compressor rotor of the aircraft engine on the dynamic balance of the compressor rotor of the aircraft engine is reduced, and the detection precision of the dynamic balance degree is improved.
Firstly, according to the size of a compressor shaft, a first positioning shaft sleeve 1 and a second positioning shaft sleeve 2 are processed according to shaft-collecting interference fit h7/S6, and the tolerance grade S6 is guaranteed. Heating the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 to 120 ℃, and keeping for 30 minutes; after the sizes of the inner holes of the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are expanded, the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are rapidly pressed on the corresponding compressor shafts; and when the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are cooled to room temperature, the sizes of the inner holes of the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are shrunk, and the first positioning shaft sleeve and the second positioning shaft sleeve tightly hold the compressor shaft to realize connection with the compressor rotor.
The first positioning shaft sleeve 1 is placed on a V-shaped mounting block of the dynamic balancing machine, and the first positioning shaft sleeve 1 is driven to rotate through a belt. The dynamic balancing device of the air compressor rotor of the aero-engine of the embodiment is driven by a belt to rotate together with the air compressor rotor, and the dynamic unbalance of the air compressor rotor is detected by a sensor on a dynamic balancing machine.
The rear end of the compressor rotor is of a compressor disc structure, the second positioning shaft sleeve 2 is required to extend out and be supported on the V-shaped mounting block at the other end to form a cantilever supporting structure, the motion balance amount of the compressor rotor is measured after the compressor rotor rotates, the length of the second positioning shaft sleeve 2 needs to be increased at the moment, and the structure can generate deflection, so that the connection mode is not preferable. In the embodiment, a bearing 3 is installed on the second positioning shaft sleeve 2, the bearing 3 supports the second positioning shaft sleeve 2, a bearing connecting support 4 is designed on the dynamic balancing machine, and the bearing connecting support 4 extends into the compressor disk and is connected with the bearing 3, as shown in fig. 1. Through the design that bearing 3 and bearing connect support 4, effectively reduced the connection length of second location axle sleeve 2, avoided the production of unnecessary amount of deflection, reduced the influence to the dynamic balance experiment.
In some embodiments, the length to diameter ratio of the first and second positioning collars 1, 2 reaches 1.
Because the connection position is in the compressor disk, the V-shaped mounting block of the dynamic balancing machine cannot be directly connected with the second positioning shaft sleeve 2, and therefore the bearing 3 and the second positioning shaft sleeve 2 are connected in an interference fit manner, and the second positioning shaft sleeve 2 and the bearing 3 rotate synchronously; one end of the bearing connecting support 4 is connected with the bearing 3, and the other end of the bearing connecting support 4 is connected with the dynamic balancing machine outwards, so that the rear end of the compressor rotor is supported. Because a long shaft mechanism is not used, the measurement value of the dynamic balance device of the aircraft engine compressor rotor of the embodiment is more accurate, and the processing difficulty is lower.
Although the device solves the problem of large dynamic unbalance of the prior aeroengine compressor rotor balancing device, the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are in interference connection with the compressor rotor, so that a dismounting process needs to be designed, and the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are dismounted under the condition of ensuring the integrity of the compressor rotor. Consequently, first location axle sleeve 1 and second location axle sleeve 2 adopt tin bronze location axle sleeve, and tin bronze location axle sleeve hardness is lower, when having impurity between part and first location axle sleeve 1 and the second location axle sleeve 2, impurity can imbed first location axle sleeve 1 and second location axle sleeve 2 earlier in, can not harm the part. Secondly, the tin bronze location axle sleeve is more wear-resisting, possesses good processing property for first location axle sleeve 1 and second location axle sleeve 2 can repetitious usage. In addition, the positioning shaft sleeve dismounting device designed by the embodiment can smoothly dismount the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 from the parts by utilizing the thread torsion without damaging the parts.
The positioning shaft sleeve dismounting device is structurally shown in fig. 2 and comprises clamping jaws 5, a push rod 7 and a threaded sleeve 8, wherein the threaded sleeve 8 is sleeved on the push rod 7 and is in threaded connection with the push rod 7, the clamping jaws 5 are at least two, and the at least two clamping jaws 5 are movably connected with the threaded sleeve 8, so that the first positioning shaft sleeve 1/the second positioning shaft sleeve 2 can be clamped by the clamping jaws 5. And after the dynamic balance measurement and adjustment are completed, the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are disassembled by using the positioning shaft sleeve disassembling device. Taking the first positioning shaft sleeve 1 to be disassembled as an example, firstly, one end of the ejector rod 7 is made to abut against the end face of the compressor shaft, the jaw 5 is made to clamp the first positioning shaft sleeve 1, then the ejector rod 7 is made to abut against the end face of the compressor shaft and simultaneously the ejector rod 7 is rotated, and as the ejector rod 7 is in threaded connection with the threaded sleeve 8, the rotation of the ejector rod 7 enables the threaded sleeve 8 to drive the jaw 5 to pull and separate the first positioning shaft sleeve 1 and the compressor shaft.
In some embodiments, the jaw 5 is hingedly connected to the threaded sleeve 8, in particular, as shown in fig. 2, the jaw 5 may be hingedly connected to the threaded sleeve 8 by a connecting rod 6.
In some embodiments, in order to facilitate the rotation of the ejector rod 7 while the ejector rod is pressed against the end face of the compressor shaft, one end of the ejector rod 7 is provided with an ejector block 9, and when the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are disassembled, the ejector rod 7 is pressed against the end face of the compressor shaft through the ejector block 9; when the ejector rod 7 is rotated to enable the threaded sleeve 8 to drive the clamping jaws 5 to pull and separate the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 from the compressor rotor, the ejector rod 7 rotates in the ejector block 9.
In some embodiments, the ram 7 is rotatably connected to the ram block 9.
In some embodiments, a groove matched with the end of the mandril 7 is formed in the top block 9, and when the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are disassembled, the mandril 7 is inserted into the groove of the top block 9 and rotates in the groove.
In some embodiments, one end of the ejector rod 7 is set to be conical, and a conical groove matched with the conical end surface of the ejector rod 7 is formed in the ejector block 9; when the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 are disassembled, the conical end surface of the ejector rod 7 is inserted into the conical groove of the ejector block 9 to jack the ejector block 9; when the ejector rod 7 is rotated to enable the threaded sleeve 8 to drive the clamping jaw 5 to pull and separate the first positioning shaft sleeve 1 and the second positioning shaft sleeve 2 from the compressor rotor, the conical end face of the ejector rod 7 rotates in the conical groove of the ejector block 9.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention shall fall within the protection scope of the present invention.
Claims (4)
1. A dynamic balancing device for an aircraft engine compressor rotor is characterized by comprising:
the first positioning shaft sleeve (1), the first positioning shaft sleeve (1) is in interference connection with the front end of a compressor shaft of a compressor rotor;
the second positioning shaft sleeve (2) is in interference connection with the rear end of a compressor shaft of a compressor rotor of the second positioning shaft sleeve (2);
the bearing (3) is sleeved on the second positioning shaft sleeve (2) and is in interference connection with the second positioning shaft sleeve (2);
the bearing connecting support (4), the bearing connecting support (4) is installed on the dynamic balancing machine;
wherein:
the first positioning shaft sleeve (1) is placed on a V-shaped mounting block of the dynamic balancing machine, and the first positioning shaft sleeve (1) is driven to rotate through a belt;
the bearing connecting support (4) extends to the interior of the compressor disk and is connected with the bottom of the bearing (3).
2. The aircraft engine compressor rotor dynamic balancing device according to claim 1, characterized in that the first locating bush (1) and the second locating bush (2) are tin bronze locating bushes.
3. The aircraft engine compressor rotor dynamic balancing device according to claim 1, characterized in that the tolerance level of the first locating bush (1) and the second locating bush (2) is S6.
4. The aircraft engine compressor rotor dynamic balancing device according to claim 1, characterized in that the length-diameter ratio of the first locating shaft sleeve (1) and the second locating shaft sleeve (2) is 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221167998.0U CN217586154U (en) | 2022-05-16 | 2022-05-16 | Dynamic balancing device for aero-engine compressor rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221167998.0U CN217586154U (en) | 2022-05-16 | 2022-05-16 | Dynamic balancing device for aero-engine compressor rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217586154U true CN217586154U (en) | 2022-10-14 |
Family
ID=83550663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221167998.0U Active CN217586154U (en) | 2022-05-16 | 2022-05-16 | Dynamic balancing device for aero-engine compressor rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217586154U (en) |
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2022
- 2022-05-16 CN CN202221167998.0U patent/CN217586154U/en active Active
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