CN216464390U - Aeroengine screws up frock - Google Patents
Aeroengine screws up frock Download PDFInfo
- Publication number
- CN216464390U CN216464390U CN202123158622.1U CN202123158622U CN216464390U CN 216464390 U CN216464390 U CN 216464390U CN 202123158622 U CN202123158622 U CN 202123158622U CN 216464390 U CN216464390 U CN 216464390U
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- engine
- bearing
- connecting disc
- rotor shaft
- mounting groove
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Abstract
The utility model discloses an aeroengine tightening tool, which comprises a fixed seat, wherein the upper end of the fixed seat is detachably connected with a connecting disc, the middle part of the connecting disc is provided with a bearing matched with an engine rotor shaft, a locking block is arranged above the bearing, and the locking block is detachably connected on the connecting disc; the locking block is provided with a key groove for key connection of an engine rotor shaft, and the connecting disc is provided with a first mounting groove for mounting an engine casing and a first threaded hole for detachably connecting the engine casing. The utility model discloses in, keyway and bearing can restrict engine rotor shaft, avoid engine rotor shaft to rotate taking place, sideslip or deflect, and the engine casket is fixed on the connection pad to make the rotor shaft and the casket relatively fixed of engine, can make parts such as engine bearing, compressor obtain the protection like this, and then improve the assembly quality, can also realize single moment of beating, avoid leading to personnel injured because of skidding simultaneously with raise the efficiency.
Description
Technical Field
The utility model relates to an aeroengine frock technical field, concretely relates to aeroengine screws up frock.
Background
The rotor of the micro turbojet engine is a high-speed rotating part, so a rotor shaft of the rotor and an air compressor are generally fastened by using a locking nut, and a torque value of more than 50N.m is applied. The tightening torque method adopted by the traditional engine needs two operators, wherein one operator fixes one end of the engine by using a tool, and the other operator tightens the engine by using a torque wrench. However, the screwing mode has no limit tool, the screwing torque is large, the bearing is easily damaged due to misoperation, the compressor and the stator casing are scratched, and even personnel can be injured due to slipping.
SUMMERY OF THE UTILITY MODEL
Not enough to the above-mentioned of prior art, the utility model provides a do not damage part, safe aeroengine and screw up frock.
In order to achieve the purpose of the invention, the technical scheme adopted by the utility model is as follows:
the tightening tool for the aero-engine comprises a fixed seat, wherein the upper end of the fixed seat is detachably connected with a connecting disc, the middle part of the connecting disc is provided with a bearing matched with an engine rotor shaft, and a locking block is arranged above the bearing and detachably connected to the connecting disc; the locking block is provided with a key groove for key connection of an engine rotor shaft, and the connecting disc is provided with a first mounting groove for mounting an engine casing and a plurality of first threaded holes for detachably connecting the engine casing.
The beneficial effects of adopting the above technical scheme are: the locking block is detachably connected to the connecting disc, the connecting disc is detachably connected to the fixed seat, and the fixed seat is detachably connected to the workbench, so that the whole tool is fixedly connected to the workbench, and the stability of the whole tool is ensured; the latch segment is provided with the keyway that is used for key-type connection engine rotor shaft, and be provided with the bearing that matches with engine rotor shaft on the connection pad, when engine rotor shaft installs in the middle of keyway and the bearing, keyway and bearing can restrict engine rotor shaft, avoid engine rotor shaft rotating taking place, sideslip or deflection, and the connection pad can be dismantled and connect the engine casket, make the engine casket fix on the connection pad, thereby make the rotor shaft and the casket relatively fixed of engine, can make engine bearing like this, parts such as compressor are protected, and then improve the assembly quality, can also realize single moment of beating, avoid leading to personnel's injury because of skidding simultaneously with raise the efficiency.
Furthermore, the middle part of the connecting disc is provided with a second mounting groove for mounting a bearing, and the second mounting groove is in clearance fit with the bearing.
The beneficial effects of adopting the above technical scheme are: the second mounting groove is used for installing the bearing, and the second mounting groove is convenient to install the bearing into the second mounting groove with bearing clearance fit, and guarantees that the bearing can not take place to rock in the second mounting groove.
Further, the depth of the second mounting groove is larger than the thickness of the process bearing.
The beneficial effects of adopting the above technical scheme are: the depth of the second mounting groove is larger than the thickness of the bearing, so that the bearing is prevented from interfering the mounting of the locking block.
Further, the middle part of connection pad still is provided with the third mounting groove that is used for installing the latch segment, and the third mounting groove is located the top of second mounting groove.
The beneficial effects of adopting the above technical scheme are: the third mounting groove is used for mounting a locking block; the third mounting groove is located the top of second mounting groove, makes things convenient for the installation of latch segment.
Furthermore, a counter bore used for being detachably connected with the workbench is arranged on the fixed seat.
The beneficial effects of adopting the above technical scheme are: the counter bore is formed in the fixing seat, so that the fixing seat can be conveniently fixed on the workbench through the bolt.
Furthermore, a plurality of matched second threaded holes and third threaded holes are respectively formed in the fixing seat and the connecting disc.
The beneficial effects of adopting the above technical scheme are: and the fixing seat and the connecting disc are respectively provided with a second threaded hole and a third threaded hole which are matched, so that the connecting disc is conveniently fixed on the fixing seat through bolts.
The utility model has the advantages that: the latch segment is provided with the keyway that is used for key-type connection engine rotor shaft, and be provided with the bearing that matches with engine rotor shaft on the connection pad, when engine rotor shaft installs in the middle of keyway and the bearing, keyway and bearing can restrict engine rotor shaft, avoid engine rotor shaft rotating taking place, sideslip or deflection, and the connection pad can be dismantled and connect the engine casket, make the engine casket fix on the connection pad, thereby make the rotor shaft and the casket relatively fixed of engine, can make engine bearing like this, parts such as compressor are protected, and then improve the assembly quality, can also realize single moment of beating, avoid leading to personnel's injury because of skidding simultaneously with raise the efficiency.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the present invention before operation;
FIG. 3 is a schematic structural view after the operation of the present invention;
the engine comprises a fixed seat 1, a fixed seat 101, a second threaded hole 102, a counter bore 2, a connecting disc 201, a third threaded hole 202, a first threaded hole 203, a first mounting groove 204, a second mounting groove 205, a third mounting groove 3, a bearing 4, a locking block 401, a key groove 5, an engine casing 6, an engine rotor shaft 7, a gas compressor 8, an engine bearing 9 and a locking nut.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and various changes may be made apparent to those skilled in the art within the spirit and scope of the present invention as defined and defined by the appended claims.
As shown in fig. 1-3, an aeroengine screwing tool comprises a fixed seat 1, wherein the upper end of the fixed seat 1 is connected with a connecting disc 2 through a bolt, a bearing 3 matched with an engine rotor shaft 6 is arranged in the middle of the connecting disc 2, a locking block 4 is arranged above the bearing 3, and the locking block 4 is connected to the connecting disc 2 through a bolt; the locking block 4 is provided with a through hole, six key slots 401 for key connection of the engine rotor shaft 6 are formed in the through hole, and the connecting disc 2 is provided with a first mounting groove 203 for mounting the engine casing 5 and four first threaded holes 202 for bolt connection of the engine casing 5; the fixing seat 1 is a cylinder, the connecting disc 2 is a disc, the locking block 4 is of a boss structure, and the type of the bearing 3 is consistent with that of the engine bearing 8; the key slot 401 is connected to a spline on the engine rotor shaft 6.
The locking block 4 is connected to the connecting disc 2 through a bolt, the connecting disc 2 is connected to the fixing seat 1 through a bolt, and the fixing seat 1 is connected to the workbench through a bolt, so that the whole tool is fixedly connected to the workbench, and the stability of the whole tool is guaranteed; the latch segment 4 is provided with keyway 401 that is used for key-type connection engine rotor shaft 6, and be provided with the bearing 3 that matches with engine rotor shaft 6 on the connection pad 2, when engine rotor shaft 6 installs in keyway 401 and bearing 3 in the middle of, keyway 401 and bearing 3 can restrict engine rotor shaft 6, avoid engine rotor shaft 6 rotating taking place, sideslip or deflection, and connection pad 2 bolted connection engine casket 5, make engine casket 5 fix on connection pad 2, thereby make engine rotor shaft 6 and engine casket 5 relatively fixed, can make engine bearing 8 like this, parts such as compressor 7 obtain the protection, and then improve the assembly quality, can also realize single moment of beating, avoid leading to personnel's injury because of skidding simultaneously with the raise the efficiency.
As an optional implementation manner, the middle part of the connecting disc 2 is provided with a second mounting groove 204 for mounting the bearing 3, the second mounting groove 204 is in clearance fit with the bearing 3, the bearing 3 is conveniently mounted in the second mounting groove 204, and the bearing 3 is ensured not to shake in the second mounting groove 204; further, a through hole having a diameter smaller than the diameter of the outer ring of the bearing 3 and larger than the shaft diameter of the engine rotor shaft 6 is also provided below the second mounting groove 204, and the axis of the second mounting groove 204 coincides with the axis of the first mounting groove 203.
As an alternative embodiment, the depth of the second mounting groove 204 is greater than the thickness of the bearing 3, so as to avoid the bearing 3 from interfering with the mounting of the locking block 4.
As an optional embodiment, the middle part of the connecting disc 2 is further provided with a third mounting groove 205 for mounting the locking block 4, and the third mounting groove 205 is positioned above the second mounting groove 204, so that the locking block 4 is conveniently mounted; in addition, the bottom of the third mounting groove 205 is provided with a threaded hole, and the locking block 4 is provided with a through hole matched with the threaded hole, so that the locking block 4 can be conveniently fixed in the third mounting groove 205 through a bolt.
As an optional implementation manner, a counter bore 102 for detachable connection with a workbench is arranged on the fixed seat 1, so that the fixed seat 1 can be conveniently fixed on the workbench through bolts; in addition, the fixed seat 1 is also provided with a through hole, and the aperture of the through hole is larger than the shaft diameter of the engine rotor shaft 6.
As an optional implementation manner, the fixing seat 1 and the connecting disc 2 are respectively provided with a second threaded hole 101 and a third threaded hole 201 which are matched with each other, so that the connecting disc 2 can be conveniently fixed on the fixing seat 1 through bolts; wherein, the fixing base 1 is provided with four second threaded holes 101, and the connecting disc 2 is provided with two third threaded holes 201.
The utility model discloses a working process does:
the fixed seat 1 is connected to a heavy workbench through bolts;
the bearing 3 is installed in the second installation groove 204, and then the locking block 4 is connected to the third installation groove 205 through bolts;
vertically fixing the engine, aligning a key groove 401 of a locking block 4 with a spline of a rotor shaft, and then connecting a connecting disc 2 with an engine casing 5 through bolts;
connecting the connecting disc 2 with the fixed seat 1 through bolts, so that the engine is installed on the workbench; finally, a torque wrench is used for applying torque to the locking nut 9.
Claims (6)
1. The tightening tool for the aero-engine is characterized by comprising a fixed seat (1), wherein the upper end of the fixed seat (1) is detachably connected with a connecting disc (2), a bearing (3) matched with an engine rotor shaft (6) is arranged in the middle of the connecting disc (2), a locking block (4) is arranged above the bearing (3), and the locking block (4) is detachably connected to the connecting disc (2); the locking block (4) is provided with a key groove (401) for key connection of an engine rotor shaft (6), and the connecting disc (2) is provided with a first mounting groove (203) for mounting an engine casing (5) and a plurality of first threaded holes (202) for detachably connecting the engine casing (5).
2. The aircraft engine tightening tool according to claim 1, characterized in that a second mounting groove (204) for mounting a bearing (3) is formed in the middle of the connecting disc (2), and the second mounting groove (204) is in clearance fit with the bearing (3).
3. The aircraft engine tightening tool according to claim 2, characterized in that the depth of the second mounting groove (204) is greater than the thickness of the bearing (3).
4. The aircraft engine tightening tool according to claim 2, characterized in that a third mounting groove (205) for mounting the locking block (4) is further formed in the middle of the connecting disc (2), and the third mounting groove (205) is located above the second mounting groove (204).
5. The aircraft engine tightening tool according to claim 1, characterized in that a counter bore (102) for detachable connection with a workbench is arranged on the fixed seat (1).
6. The aircraft engine tightening tool according to claim 1, characterized in that a plurality of second threaded holes (101) and third threaded holes (201) which are matched with each other are respectively formed in the fixing seat (1) and the connecting disc (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123158622.1U CN216464390U (en) | 2021-12-15 | 2021-12-15 | Aeroengine screws up frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123158622.1U CN216464390U (en) | 2021-12-15 | 2021-12-15 | Aeroengine screws up frock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216464390U true CN216464390U (en) | 2022-05-10 |
Family
ID=81423778
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123158622.1U Active CN216464390U (en) | 2021-12-15 | 2021-12-15 | Aeroengine screws up frock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216464390U (en) |
-
2021
- 2021-12-15 CN CN202123158622.1U patent/CN216464390U/en active Active
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