CN217965964U - Tool for machining cylinder cover of aircraft engine - Google Patents
Tool for machining cylinder cover of aircraft engine Download PDFInfo
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- CN217965964U CN217965964U CN202222201270.1U CN202222201270U CN217965964U CN 217965964 U CN217965964 U CN 217965964U CN 202222201270 U CN202222201270 U CN 202222201270U CN 217965964 U CN217965964 U CN 217965964U
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- machining
- pinion
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Abstract
The utility model discloses a frock of aeroengine cylinder cap processing, including base, transmission case, motor two and carousel, base upper end both sides all are fixed with the transmission case, a side wall mounting has in the transmission case motor two, be connected with on the output shaft of motor two the carousel, be provided with the loading board between the carousel, loading board upper end bilateral symmetry is provided with the fixed plate, the fixed plate is L type structure. The beneficial effects are that: the utility model discloses a set up the drive mechanism that motor one, master gear, pinion and pivot are constituteed, when the fixed end cover, motor one drives the pinion through the master gear and rotates, and the pinion drives the clamp plate through the pivot and rotates, and then can adjust the position of clamp plate to the four corners department of end cover, adopts two sets of motors to drive four clamp plates as power unit and rotate simultaneously, can effectively reduce the energy consumption of device to make device simple structure, guarantee the performance of device, improve the device practicality.
Description
Technical Field
The utility model relates to an aeroengine cylinder cap processingequipment technical field, concretely relates to frock of aeroengine cylinder cap processing.
Background
An aero-engine (aero-engine), which is a highly complex and precise thermodynamic machine, provides the aircraft with the power needed for flight. The heart of the aircraft is known as 'industrial flower', the heart directly affects the performance, reliability and economy of the aircraft, and a clamp tool is needed in the machining process of an aircraft engine cylinder cover.
The frock of present aeroengine cylinder cap processing drives the pivot through four motors and rotates when fixing the cylinder cap, and then fixes it with the position control of clamp plate to the four corners of cylinder cap, and adopts four sets of motors as power unit for the energy consumption that increases the device to lead to the device structure complicated, deal with the performance of device, reduce the device practicality.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
In order to overcome prior art not enough, now provide a frock of aeroengine cylinder cap processing, the frock of having solved present aeroengine cylinder cap processing is when fixing the cylinder cap through four motor drive pivots and rotates, and then fixes it with the position control of clamp plate to the four corners of cylinder cap, and adopts four sets of motors as the energy consumption of power unit for increasing the device to lead to the device structure complicated, deal with the performance of device, reduce the problem of device practicality.
(II) technical scheme
The utility model discloses a following technical scheme realizes: the utility model provides a frock of aeroengine cylinder cap processing, including base, transmission case, motor two and carousel, base upper end both sides all are fixed with the transmission case, a lateral wall installs in the transmission case motor two, be connected with on the output shaft of motor two the carousel, be provided with the loading board between the carousel, loading board upper end bilateral symmetry is provided with the fixed plate, the fixed plate is L type structure, motor one is installed to the fixed plate upper end, be provided with the master gear on the output shaft of motor one, the master gear both sides all are provided with the pinion, a pinion lateral wall with install the pivot between the loading board, a pivot lateral wall installs electric putter, electric putter one end is provided with the connecting plate, the connecting plate is L type structure, be provided with the screw rod on the connecting plate, screw rod one end is provided with the clamp plate.
Further, the transmission case with the base passes through bolted connection, motor two with the transmission case passes through bolted connection, motor two with the carousel key-type connection.
By adopting the technical scheme, the motor II can drive the engine end cover fixed on the bearing plate to rotate through the turntable, so that the machining position of the motor II is changed.
Further, the bearing plate is connected with the turntable through bolts, and the fixing plate is connected with the bearing plate through bolts.
Through adopting above-mentioned technical scheme, the loading board provides the support for the engine end cover.
Furthermore, the first motor is in key connection with the main gear, and the secondary gear is meshed with the main gear.
By adopting the technical scheme, the motor drives the main gear to rotate, and the main gear drives the auxiliary gear to rotate.
Furthermore, one end of the rotating shaft is connected with the pinion through a bolt, and the other end of the rotating shaft is rotatably connected with the bearing plate.
By adopting the technical scheme, the pinion drives the rotating shaft to rotate.
Furthermore, the electric push rod is connected with the rotating shaft through a screw, and the connecting plate is connected with the electric push rod through a screw.
By adopting the technical scheme, the rotating shaft drives the electric push rod to rotate, so that the direction of the pressing plate is adjusted, and meanwhile, the electric push rod adjusts the position of the pressing plate.
Furthermore, the screw rod is connected with the connecting plate through threads, and the pressing plate is connected with the screw rod in a rotating mode.
By adopting the technical scheme, the screw rod is rotated to enable the pressing plate to fix four corners of the end cover of the engine.
(III) advantageous effects
Compared with the prior art, the utility model, following beneficial effect has:
when fixing the cylinder cap, the frock for solving current aeroengine cylinder cap processing drives the pivot through four motors and rotates, and then fixes it with the position control of clamp plate to the four corners of cylinder cap, and adopts four sets of motors as power unit for increasing the energy consumption of device to lead to the device structure complicacy, reply the performance of device, reduce the problem of device practicality, the utility model discloses a set up the drive mechanism that motor one, master gear, pinion and pivot are constituteed, when fixed end cover, motor one drives pinion through the master gear and rotates, and pinion drives the clamp plate through the pivot and rotate, and then can adjust the position of clamp plate to the four corners department of end cover, adopt two sets of motors to drive four clamp plate rotations as power unit simultaneously, can effectively reduce the energy consumption of device, and make device simple structure, guarantee the performance of device, improve the device practicality.
Drawings
Fig. 1 is a schematic structural diagram of a tool for machining an aircraft engine cylinder head according to the present invention;
fig. 2 is an enlarged view of a position a in the tool for machining the cylinder cover of the aircraft engine according to the present invention;
fig. 3 is a right sectional view of a fixing plate in the tool for machining an aircraft engine cylinder head according to the present invention;
figure 4 is a main section view of transmission case in frock of aeroengine cylinder cap processing.
The reference numerals are explained below:
1. a rotating shaft; 2. an electric push rod; 3. a base; 4. a transmission case; 5. a turntable; 6. a first motor; 7. carrying a plate; 8. a fixing plate; 9. a connecting plate; 10. a screw; 11. pressing a plate; 12 a main gear; 13. a pinion gear; 14. and a second motor.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1-4, the present embodiment of a tool for machining an aircraft engine cylinder head, includes a base 3, a transmission case 4, a second motor 14 and a rotary table 5, the transmission case 4 is fixed on both sides of the upper end of the base 3, the second motor 14 is installed on a side wall in the transmission case 4, the rotary table 5 is connected on an output shaft of the second motor 14, the second motor 14 can drive an engine end cover fixed on the support plate 7 to rotate through the rotary table 5, and further change the machining position thereof, a support plate 7 is installed between the rotary tables 5, fixing plates 8 are symmetrically installed on both sides of the upper end of the support plate 7, the fixing plates 8 are of an L-shaped structure, the support plate 7 provides support for the engine end cover, the first motor 6 is installed on the upper end of the fixing plates 8, a main gear 12 is installed on an output shaft of the first motor 6, sub-gears 13 are installed on both sides of the main gear 12, the main gear 6 drives the main gear 12 to rotate, the main gear 12 drives the sub-gear 13 to rotate, a rotary shaft 1 is installed between a side wall of the sub-gear 13 and the support plate 7, the sub-gear 13 drives a rotary shaft 1 to rotate, an electric push rod 2 is installed on a side wall of the rotary shaft 1, a connecting plate 11 is installed on a side wall of the electric push rod 11, and a four-push-rod 11 is installed on the electric-adjusting plate 10 for adjusting screw rod 10 for adjusting the electric push rod.
As shown in fig. 1-4, in this embodiment, the transmission case 4 is connected to the base 3 by bolts, the second motor 14 is connected to the transmission case 4 by bolts, the second motor 14 is connected to the rotary table 5 by keys, the bearing plate 7 is connected to the rotary table 5 by bolts, the fixing plate 8 is connected to the bearing plate 7 by bolts, the first motor 6 is connected to the main gear 12 by keys, and the pinion 13 is engaged with the main gear 12.
As shown in fig. 1-4, in this embodiment, one end of the rotating shaft 1 is connected to the pinion 13 through a bolt, the other end of the rotating shaft 1 is rotatably connected to the bearing plate 7, the electric push rod 2 is connected to the rotating shaft 1 through a screw, the connecting plate 9 is connected to the electric push rod 2 through a screw, the screw 10 is connected to the connecting plate 9 through a thread, and the pressing plate 11 is rotatably connected to the screw 10.
The specific implementation process of this embodiment is as follows: when the end cover machining device is used, the base 3 is fixed on a milling machine, then an external power supply is connected, the engine end cover is placed on the bearing plate 7, the first motor 6 drives the pinion 13 to rotate through the main gear 12, the pinion 13 drives the pressing plate 11 to rotate through the rotating shaft 1, the position of the pressing plate 11 is adjusted to the four corners of the end cover by matching with the electric push rod 2, then the screw rod 10 is rotated to enable the pressing plate 11 to fix the end cover, and in the machining process, the second motor 14 can drive the engine end cover fixed on the bearing plate 7 to rotate through the rotary table 5 to further change the machining position of the engine end cover.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. The utility model provides a frock of aeroengine cylinder cap processing which characterized in that: including base (3), transmission case (4), two (14) motors and carousel (5), base (3) upper end both sides all are fixed with transmission case (4), a lateral wall installs in transmission case (4) motor two (14), be connected with on the output shaft of motor two (14) carousel (5), be provided with loading board (7) between carousel (5), loading board (7) upper end bilateral symmetry is provided with fixed plate (8), fixed plate (8) are L type structure, motor (6) are installed to fixed plate (8) upper end, be provided with master gear (12) on the output shaft of motor (6), master gear (12) both sides all are provided with pinion (13), pinion (13) a lateral wall with install pivot (1) between loading board (7), pivot (1) a lateral wall installs electric putter (2), electric putter (2) one end is provided with connecting plate (9), connecting plate (9) are L type structure, be provided with screw rod (10) on connecting plate (9), screw rod (10) one end is provided with clamp plate (11).
2. The tooling for machining the cylinder cover of the aircraft engine according to claim 1, characterized in that: the transmission case (4) is connected with the base (3) through a bolt, the motor II (14) is connected with the transmission case (4) through a bolt, and the motor II (14) is connected with the rotary table (5) in a key mode.
3. The tooling for machining the cylinder cover of the aircraft engine according to claim 1, characterized in that: the bearing plate (7) is connected with the rotary table (5) through bolts, and the fixing plate (8) is connected with the bearing plate (7) through bolts.
4. The tooling for machining the cylinder cover of the aircraft engine according to claim 1, characterized in that: the first motor (6) is in key connection with the main gear (12), and the secondary gear (13) is meshed with the main gear (12).
5. The tooling for machining the cylinder cover of the aircraft engine according to claim 1, characterized in that: one end of the rotating shaft (1) is connected with the pinion (13) through a bolt, and the other end of the rotating shaft (1) is rotatably connected with the bearing plate (7).
6. The tooling for machining the cylinder cover of the aircraft engine according to claim 1, characterized in that: the electric push rod (2) is connected with the rotating shaft (1) through a screw, and the connecting plate (9) is connected with the electric push rod (2) through a screw.
7. The tooling for machining the cylinder cover of the aircraft engine according to claim 1, characterized in that: the screw rod (10) is connected with the connecting plate (9) through threads, and the pressing plate (11) is rotationally connected with the screw rod (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222201270.1U CN217965964U (en) | 2022-08-22 | 2022-08-22 | Tool for machining cylinder cover of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222201270.1U CN217965964U (en) | 2022-08-22 | 2022-08-22 | Tool for machining cylinder cover of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217965964U true CN217965964U (en) | 2022-12-06 |
Family
ID=84260484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222201270.1U Active CN217965964U (en) | 2022-08-22 | 2022-08-22 | Tool for machining cylinder cover of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217965964U (en) |
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2022
- 2022-08-22 CN CN202222201270.1U patent/CN217965964U/en active Active
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