CN221716746U - Front bearing stop shaft penetrating device of small turbojet engine - Google Patents
Front bearing stop shaft penetrating device of small turbojet engine Download PDFInfo
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- CN221716746U CN221716746U CN202323271521.4U CN202323271521U CN221716746U CN 221716746 U CN221716746 U CN 221716746U CN 202323271521 U CN202323271521 U CN 202323271521U CN 221716746 U CN221716746 U CN 221716746U
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- 230000000149 penetrating effect Effects 0.000 title claims abstract description 41
- 230000007246 mechanism Effects 0.000 claims abstract description 54
- 230000006835 compression Effects 0.000 claims description 17
- 238000007906 compression Methods 0.000 claims description 17
- 230000003014 reinforcing effect Effects 0.000 claims description 11
- 230000035515 penetration Effects 0.000 claims description 10
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000004677 Nylon Substances 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 229920001778 nylon Polymers 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a front bearing stop shaft penetrating device of a small turbojet engine, which relates to the technical field of turbojet engine assembly and comprises a turbojet engine placing seat, a shaft limiting guide mechanism, a shaft penetrating pressing mechanism, a casing clamping mechanism and a bearing stop mechanism, wherein the top of the turbojet engine placing seat is provided with a longitudinal arc placing groove; the shaft limiting guide mechanism comprises a sliding adjusting rod, a supporting rod, a shaft limiting sleeve and a guide conical groove, wherein a longitudinal sliding groove is formed in the bottom of the front side of the turbojet engine placing seat, the sliding adjusting rod is connected in the longitudinal sliding groove in a sliding manner, the front end of the sliding adjusting rod is fixedly connected with the bottom of the supporting rod, the top of the supporting rod is fixedly connected with the longitudinal shaft limiting sleeve, the guide conical groove is formed in the inner side of the front end of the shaft limiting sleeve, and the center of the shaft limiting sleeve coincides with the circle center of a circle where the circular arc placing groove is located; the front bearing stop shaft penetrating device of the small turbojet engine is convenient and stable to operate and beneficial to improving shaft penetrating efficiency.
Description
Technical Field
The utility model relates to the technical field of turbojet engine assembly, in particular to a front bearing stop shaft penetrating device of a small turbojet engine.
Background
The turbojet engine is characterized in that the turbojet engine is used as a power source of an airplane generally by generating thrust force depending on gas flow, the rotation center of the turbojet engine is a turbojet engine shaft when the turbojet engine works, and the turbojet engine shaft needs to be reinstalled after the maintenance of the small turbojet engine is completed, wherein the important step is that the small turbojet engine shaft penetrates into a bearing of the small turbojet engine, however, when the small turbojet engine shaft is installed, the bearing is easy to rotate, and the shaft penetrating operation of the small turbojet engine shaft is influenced.
Disclosure of utility model
The technical problem to be solved by the utility model is to overcome the existing defects, and provide the front bearing stop shaft penetrating device of the small turbojet engine, which is characterized in that a casing of the small turbojet engine is clamped and fixed firstly, then a bearing at the rear side of the casing is pressed and fixed through a bearing stop mechanism, a shaft limiting guide mechanism is used for guiding a shaft of the small turbojet engine, the shaft of the small turbojet engine penetrates through the casing to be aligned with the inner side of the bearing at the rear side of the casing, and a shaft penetrating pressing mechanism is used for pressing the shaft of the small turbojet engine backwards, so that the installation of the shaft of the small turbojet engine is realized, the operation is convenient and stable, the shaft penetrating efficiency is improved, and the problems in the background technology can be effectively solved.
In order to achieve the above purpose, the present utility model provides the following technical solutions: a front bearing stop penetration device for a small turbojet engine, comprising:
the top of the turbojet engine placing seat is provided with a longitudinal arc placing groove;
The shaft limiting guide mechanism comprises a sliding adjusting rod, a supporting rod, a shaft limiting sleeve and a guiding conical groove, wherein a longitudinal sliding groove is formed in the bottom of the front side of the turbojet engine placement seat, the sliding adjusting rod is connected in the longitudinal sliding groove in a sliding manner, the front end of the sliding adjusting rod is fixedly connected with the bottom of the supporting rod, the top of the supporting rod is fixedly connected with the longitudinal shaft limiting sleeve, the guiding conical groove is formed in the inner side of the front end of the shaft limiting sleeve, and the center of the shaft limiting sleeve coincides with the circle center of a circle where the circular arc placement groove is located;
the shaft penetrating pressing mechanism is arranged on the side surface of the front end of the turbojet engine placing seat;
the casing clamping mechanism is arranged at the front end and the rear end of the turbojet engine placing seat;
And the bearing stop mechanism is arranged at the rear end of the bottom of the turbojet engine placing seat.
The arc placing groove on the turbojet engine placing seat is used for placing a casing of the small turbojet engine, the casing clamping mechanism clamps the casing into the arc placing groove, the bearing stopping mechanism works to press and fix a bearing at the rear end of the casing, the bearing stopping mechanism does not rotate the bearing, the sliding adjusting rod slides back and forth, the shaft limiting sleeve is positioned in the middle of the front end of the casing through the supporting rod, the small turbojet engine shaft passes through the shaft limiting sleeve, the small turbojet engine shaft is easier to penetrate into the shaft limiting sleeve through the arrangement of the guiding conical groove, then the sliding adjusting rod, the supporting rod and the shaft limiting sleeve are pushed to move backwards, the rear end of the shaft limiting sleeve extends into the front end in the casing, meanwhile, the rear end of the small turbojet engine shaft is aligned to the inner side of the bearing at the rear end of the casing, the shaft penetrating pressing mechanism faces the front end of the small turbojet engine shaft, and the small turbojet engine shaft is pressed back axially until the rear end of the small turbojet engine shaft penetrates into the inner side of the bearing at the rear end of the casing, and shaft penetrating work is completed.
Further, the shaft limiting guide mechanism further comprises a reinforcing rib plate, and the bottom of the shaft limiting sleeve is fixedly connected with the front side of the top of the supporting rod through the reinforcing rib plate. The reinforcing rib plate is used for reinforcing the connection strength of the supporting rod and the shaft limiting sleeve and preventing the shaft limiting sleeve from being inclined under the stress.
Further, the cartridge receiver clamping mechanism comprises a baffle ring, grooves, rotary compression cylinders, a second pressing rod and a clamping component, the baffle ring is fixedly connected to the rear end of the turbojet engine placement seat, the grooves are respectively formed in two sides of the front end of the turbojet engine placement seat, the rotary compression cylinders are respectively and fixedly installed in each groove, and the front ends of the rotary compression cylinders are fixedly connected with one end of the second pressing rod through the clamping component. The blocking ring blocks the rear end of the case, and the rotary compression cylinder drives the second compression rod to rotate when working, and simultaneously the second compression rod compresses the front end of the case, so that the front end and the rear end of the case are clamped and fixed.
Further, the clamping assembly comprises a mounting block and a mounting screw, the front end of the rotary compression cylinder is fixedly connected with the mounting block, a clamping groove at the front side of the mounting block is clamped with one end of the second pressing rod, and the second pressing rod is fixed in the clamping groove at the front side of the mounting block through the mounting screw. The installation piece and the installation screw cooperation can carry out firm fixed to pressing rod two, if pressing rod two wearing and tearing, can turn on the installation screw and change pressing rod two.
Further, the cartridge receiver clamping mechanism further comprises a protection pad and a mounting column, the protection pad is arranged on the rear side of the second pressing rod, two mounting columns are fixedly connected to the front side of the protection pad, and the mounting columns are clamped with the mounting holes on the second pressing rod in a matched mode. The protection pad adopts nylon pad, can avoid pressing second and the quick-witted casket front end direct contact, avoids pressing second and scrapes colored quick-witted casket front end, can change the protection pad with the help of the mounting column with pressing second on the mounting hole cooperation.
Further, the shaft penetrating pressing mechanism comprises a pressing column, a pressing power assembly and a pressing rod I, wherein the transverse pressing rod I is arranged in front of the turbojet engine placing seat through the pressing power assembly, the middle part of the rear side of the pressing rod I is fixedly connected with the front end of the pressing column, and the rear end of the pressing column is correspondingly arranged with the shaft limiting sleeve. The pressing power assembly is used for driving the pressing rod I and the pressing column to move backwards, and the small turbojet engine is pressed backwards in the axial direction through the pressing column, so that shaft penetrating work is achieved.
Further, the pressing power assembly comprises a connecting block, a shaft penetrating cylinder, a fixing seat, pull rods and fixing bolts, two fixing seats are fixedly connected to two sides of the turbojet engine placing seat respectively, the rear sides of the two fixing seats are fixedly connected with the two connecting blocks through the two longitudinal shaft penetrating cylinders respectively, the tops of the two connecting blocks are fixedly connected with the rear ends of the two pull rods respectively, and the front ends of the two pull rods are fixedly connected with the two ends of the pressing rod I through the fixing bolts respectively. The fixing seat is used for installing a shaft penetrating cylinder, and the shaft penetrating cylinder stretches to drive the connecting block and the pull rod to move backwards, so that the first pressing rod and the first pressing rod are driven to move backwards through the fixing bolt.
Further, the bearing stop mechanism comprises a longitudinal moving assembly, a vertical rod, a circular ring and a stop friction ring, wherein the circular ring is fixedly connected to the rear end of the bottom of the turbojet engine placement seat through the vertical rod and is positioned on the right rear side of the shaft limiting sleeve, and the stop friction ring is fixedly connected to the front side of the circular ring. The longitudinal moving assembly is used for driving the vertical rod and the circular ring to move forwards, so that the stop friction ring presses the bearing at the rear end of the casing, the bearing is prevented from rotating, and the shaft penetrating work is prevented from being influenced.
Further, the longitudinal movement assembly comprises a support, a longitudinal sliding column, a sliding seat, a longitudinal stud and a hand wheel, wherein the support is fixedly connected to the rear end of the bottom of the turbojet engine placement seat, the longitudinal sliding column is fixedly connected in the support, the longitudinal stud is rotationally connected to the support, the hand wheel is fixedly connected to the rear end of the longitudinal stud, the longitudinal stud is in threaded connection with a threaded hole in the sliding seat, and a sliding hole in the sliding seat is in sliding connection with the longitudinal stud. The hand wheel rotates the longitudinal stud clockwise, the longitudinal stud and the sliding seat can slide forwards along the longitudinal sliding column under the action of the threads of the longitudinal stud and the sliding seat, the stop friction ring can be driven to move forwards, the hand wheel rotates the longitudinal stud anticlockwise, the stop friction ring can be driven to move backwards, and the bearing can be loosened when the stop friction ring moves backwards.
Further, the turbojet engine comprises support legs, four support legs are fixedly connected to four corners of the bottom of the turbojet engine placement seat respectively, the support legs support the turbojet engine placement seat high, and the longitudinally moving assembly is convenient to install.
Compared with the prior art, the utility model has the beneficial effects that: the front bearing stop shaft penetrating device of the small turbojet engine has the following advantages:
The small-sized turbojet engine is clamped and fixed by the casing, then the bearing at the rear side of the casing is pressed and fixed by the bearing stop mechanism, the small-sized turbojet engine shaft is guided by the shaft limiting guide mechanism, the small-sized turbojet engine shaft penetrates through the casing to be aligned with the inner side of the bearing at the rear side of the casing, the shaft penetrating pressing mechanism presses the small-sized turbojet engine shaft backwards, the installation of the small-sized turbojet engine shaft is realized, the operation is convenient and stable, and the shaft penetrating efficiency is improved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is a schematic view of the bottom structure of the present utility model;
FIG. 3 is a schematic view of the structure of the present utility model shown in FIG. 2 at a partially enlarged scale;
fig. 4 is a schematic view of the rear structure of the present utility model.
In the figure: the turbojet engine comprises a1 turbojet engine placing seat, a 2-axis limiting guide mechanism, a 21 sliding adjusting rod, a 22 supporting rod, a 23-axis limiting sleeve, a 24 guiding conical groove, a 25 reinforcing rib plate, a 3-axis penetrating pressing mechanism, a 31 pressing column, a 32 connecting block, a 33-axis penetrating cylinder, a 34 fixing seat, a 35 pull rod, a 36 fixing bolt, a 37 pressing rod I, a 4-casing clamping mechanism, a 41 retaining ring, a 42 groove, a 43 rotating and pressing cylinder, a 44 mounting block, a 45 pressing rod II, a 46 mounting screw, a 47 protecting pad, a 48 mounting column, a 5-bearing stopping mechanism, a51 support, a 52 longitudinal sliding column, a 53 sliding seat, a 54 longitudinal stud, a 55 hand wheel, a 56 supporting rod, a 57 circular ring, a 58 stopping friction ring and a 6 supporting leg.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1 to 4, the present utility model provides a technical solution: a front bearing stop shaft penetrating device of a small turbojet engine comprises a turbojet engine placing seat 1, a shaft limiting guide mechanism 2, a shaft penetrating pressing mechanism 3, a casing clamping mechanism 4 and a bearing stop mechanism 5;
the top of the turbojet engine placing seat 1 is provided with a longitudinal arc placing groove;
In order to prop up the turbojet engine placing seat 1, the support legs 6 are further arranged, four bottom four corners of the turbojet engine placing seat 1 are respectively and fixedly connected with four support legs 6, the support legs 6 prop up the turbojet engine placing seat 1, and the longitudinally moving assembly in the bearing stop mechanism 5 is convenient to install.
The shaft limiting guide mechanism 2 comprises a sliding adjusting rod 21, a supporting rod 22, a shaft limiting sleeve 23 and a guiding conical groove 24, wherein a longitudinal sliding groove is formed in the bottom of the front side of the turbojet engine placement seat 1, the sliding adjusting rod 21 is connected in the longitudinal sliding groove in a sliding manner, the front end of the sliding adjusting rod 21 is fixedly connected with the bottom of the supporting rod 22, the top of the supporting rod 22 is fixedly connected with the longitudinal shaft limiting sleeve 23, the guiding conical groove 24 is formed in the inner side of the front end of the shaft limiting sleeve 23, and the center of the shaft limiting sleeve 23 coincides with the circle center of a circle where the circular arc placement groove is located;
The shaft limiting guide mechanism 2 further comprises a reinforcing rib plate 25, and the bottom of the shaft limiting sleeve 23 is fixedly connected with the front side of the top of the supporting rod 22 through the reinforcing rib plate 25. The reinforcing rib plates 25 are used for reinforcing the connection strength of the supporting rods 22 and the shaft limiting sleeve 23 and preventing the shaft limiting sleeve 23 from being inclined under stress.
The through shaft pressing mechanism 3 is arranged on the side surface of the front end of the turbojet engine placing seat 1;
The casing clamping mechanism 4 is arranged at the front end and the rear end of the turbojet engine placing seat 1;
The cartridge receiver clamping mechanism 4 comprises a baffle ring 41, grooves 42, rotary compression cylinders 43, a second pressing rod 45 and a clamping component, the baffle ring 41 is fixedly connected to the rear end of the turbojet engine placement seat 1, the grooves 42 are respectively formed in two sides of the front end of the turbojet engine placement seat 1, the rotary compression cylinders 43 are respectively and fixedly installed in each groove 42, and the front ends of the rotary compression cylinders 43 are fixedly connected with one end of the second pressing rod 45 through the clamping component. The blocking ring 41 blocks the rear end of the casing, and the rotary compression cylinder 43 drives the pressing rod II 45 to rotate when working, and simultaneously the pressing rod II 45 compresses the front end of the casing, so that the front end and the rear end of the casing are clamped and fixed.
The clamping assembly comprises a mounting block 44 and a mounting screw 46, the front end of the rotary compression cylinder 43 is fixedly connected with the mounting block 44, a clamping groove at the front side of the mounting block 44 is clamped with one end of a second pressing rod 45, and the second pressing rod 45 is fixed in the clamping groove at the front side of the mounting block 44 through the mounting screw 46. The mounting block 44 and the mounting screw 46 are matched to firmly fix the second pressing rod 45, and if the second pressing rod 45 is worn, the mounting screw 46 can be loosened to replace the second pressing rod 45.
The cartridge receiver clamping mechanism 4 further comprises a protection pad 47 and a mounting column 48, the protection pad 47 is arranged on the rear side of the second pressing rod 45, the two mounting columns 48 are fixedly connected to the front side of the protection pad 47, and the mounting columns 48 are clamped with the mounting holes on the second pressing rod 45 in a matching mode. The protection pad 47 adopts the nylon pad, can avoid pressing the second 45 of pole and the front end direct contact of receiver, avoids pressing the second 45 of pole and scrapes the flower receiver front end, can change the protection pad 47 with the help of the mounting column 48 with pressing the mounting hole cooperation on the second 45 of pole.
The bearing stopper mechanism 5 is mounted at the bottom rear end of the turbojet engine mount 1.
When the turbojet engine is used, the arc placing groove on the turbojet engine placing seat 1 is used for placing a casing of the small turbojet engine, the casing clamping mechanism 4 clamps the casing into the arc placing groove, the bearing stopping mechanism 5 works to press and fix the bearing at the rear end of the casing and prevent the bearing from rotating, the sliding adjusting rod 21 slides back and forth, the shaft limiting sleeve 23 is positioned in the middle of the front end of the casing through the supporting rod 22, the small turbojet engine shaft passes through the shaft limiting sleeve 23, the guiding conical groove 24 is arranged to enable the small turbojet engine shaft to penetrate into the shaft limiting sleeve 23 more easily, then the sliding adjusting rod 21, the supporting rod 22 and the shaft limiting sleeve 23 are pushed to move backwards, the rear end of the shaft limiting sleeve 23 stretches into the front end of the casing, meanwhile, the rear end of the small turbojet engine shaft is aligned to the inner side of the bearing at the rear end of the casing, the shaft penetrating pressing mechanism 3 faces the front end of the small turbojet engine shaft, the small turbojet engine shaft is pressed back axially until the rear end of the small turbojet engine shaft penetrates into the inner side of the bearing at the rear end of the casing, and shaft penetrating work is completed.
In a second embodiment, referring to fig. 1 to 4, the present utility model provides a technical solution: the embodiment is a further explanation of the structure of the first embodiment;
The shaft penetrating pressing mechanism 3 comprises a pressing column 31, a pressing power assembly and a pressing rod I37, wherein the transverse pressing rod I37 is arranged in front of the turbojet engine placing seat 1 through the pressing power assembly, the middle part of the rear side of the pressing rod I37 is fixedly connected with the front end of the pressing column 31, and the rear end of the pressing column 31 is correspondingly arranged with the shaft limiting sleeve 23. The pressing power assembly is used for driving the pressing rod I37 and the pressing column 31 to move backwards, and the pressing column 31 is used for pressing the small turbojet engine backwards to realize shaft penetrating work.
The pressing power assembly comprises a connecting block 32, a shaft penetrating cylinder 33, a fixed seat 34, pull rods 35 and fixing bolts 36, wherein two fixed seats 34 are fixedly connected to two sides of the turbojet engine placement seat 1 respectively, the rear sides of the two fixed seats 34 are fixedly connected with the two connecting blocks 32 through the two longitudinal shaft penetrating cylinders 33 respectively, the tops of the two connecting blocks 32 are fixedly connected with the rear ends of the two pull rods 35 respectively, and the front ends of the two pull rods 35 are fixedly connected with two ends of a pressing rod 37 through the fixing bolts 36 respectively.
The fixing seat 34 is used for installing the shaft penetrating cylinder 33, and the shaft penetrating cylinder 33 stretches to drive the connecting block 32 and the pull rod 35 to move backwards, so that the pressing rod one 37 and the pressing rod 31 are driven to move backwards through the fixing bolt 36.
Wherein the rotary compression cylinder 43 and the through-shaft cylinder 33 are connected with an external air source through an air pipe and a valve body.
In a third embodiment, referring to fig. 1 to 4, the present utility model provides a technical solution: the embodiment is a further explanation of the structure of the second embodiment;
The bearing stop mechanism 5 comprises a longitudinal moving assembly, a vertical rod 56, a circular ring 57 and a stop friction ring 58, wherein the circular ring 57 is fixedly connected to the rear end of the bottom of the turbojet engine placement seat 1 through the vertical rod 56, the circular ring 57 is positioned on the right rear side of the shaft limiting sleeve 23, and the stop friction ring 58 is fixedly connected to the front side of the circular ring 57. The longitudinal moving assembly is used for driving the vertical rod 56 and the circular ring 57 to move forwards, so that the stop friction ring 58 presses the bearing at the rear end of the casing, the bearing is prevented from rotating, and the shaft penetrating work is prevented from being influenced.
The longitudinal moving assembly comprises a support 51, a longitudinal slide column 52, a sliding seat 53, a longitudinal stud 54 and a hand wheel 55, wherein the support 51 is fixedly connected to the rear end of the bottom of the turbojet engine placement seat 1, the longitudinal slide column 52 is fixedly connected to the support 51, the longitudinal stud 54 is rotationally connected to the support 51, the hand wheel 55 is fixedly connected to the rear end of the longitudinal stud 54, the longitudinal stud 54 is in threaded connection with a threaded hole on the sliding seat 53, and a sliding hole on the sliding seat 53 is in sliding connection with the longitudinal slide column 52.
When the anti-friction device is used, the hand wheel 55 rotates the longitudinal stud 54 clockwise, the longitudinal stud 54 and the sliding seat 53 can slide forwards along the longitudinal sliding column 52 under the action of the threads of the sliding seat 53, the stop friction ring 58 can be driven to move forwards, the hand wheel 55 rotates the longitudinal stud 54 anticlockwise, the stop friction ring 58 can be driven to move backwards, and when the stop friction ring 58 moves backwards, the bearing can be released.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. A front bearing stop threading device for a small turbojet engine, comprising:
a vertical arc placing groove is formed in the top of the turbojet engine placing seat (1);
The shaft limiting guide mechanism (2) comprises a sliding adjusting rod (21), a supporting rod (22), a shaft limiting sleeve (23) and a guide conical groove (24), wherein a longitudinal sliding groove is formed in the bottom of the front side of the turbojet engine placement seat (1), the sliding adjusting rod (21) is connected in the longitudinal sliding groove in a sliding manner, the front end of the sliding adjusting rod (21) is fixedly connected with the bottom of the supporting rod (22), the top of the supporting rod (22) is fixedly connected with a longitudinal shaft limiting sleeve (23), the guide conical groove (24) is formed in the inner side of the front end of the shaft limiting sleeve (23), and the center of the shaft limiting sleeve (23) coincides with the circle center of a circle where the circular arc placement groove is located;
a shaft penetrating pressing mechanism (3) which is arranged on the side surface of the front end of the turbojet engine placing seat (1);
the casing clamping mechanism (4) is arranged at the front end and the rear end of the turbojet engine placing seat (1);
and the bearing stop mechanism (5) is arranged at the rear end of the bottom of the turbojet engine placing seat (1).
2. The front bearing stop shaft penetration device of a small turbojet engine according to claim 1, wherein: the shaft limiting guide mechanism (2) further comprises a reinforcing rib plate (25), and the bottom of the shaft limiting sleeve (23) is fixedly connected with the front side of the top of the supporting rod (22) through the reinforcing rib plate (25).
3. The front bearing stop shaft penetration device of a small turbojet engine according to claim 1, wherein: the machine case clamping mechanism (4) comprises a baffle ring (41), grooves (42), rotary compression cylinders (43), a pressing rod II (45) and a clamping component, the rear end of the turbojet engine placement seat (1) is fixedly connected with the baffle ring (41), the grooves (42) are respectively formed in two sides of the front end of the turbojet engine placement seat (1), the rotary compression cylinders (43) are respectively and fixedly arranged in each groove (42), and the front ends of the rotary compression cylinders (43) are fixedly connected with one end of the pressing rod II (45) through the clamping component.
4. A front bearing stop penetration device for a small turbojet engine according to claim 3, characterized in that: the clamping assembly comprises a mounting block (44) and a mounting screw (46), the front end of the rotary compression cylinder (43) is fixedly connected with the mounting block (44), a clamping groove at the front side of the mounting block (44) is clamped with one end of a second pressing rod (45), and the second pressing rod (45) is fixed in the clamping groove at the front side of the mounting block (44) through the mounting screw (46).
5. A front bearing stop penetration device for a small turbojet engine according to claim 3, characterized in that: the cartridge receiver clamping mechanism (4) further comprises a protection pad (47) and a mounting column (48), the protection pad (47) is arranged on the rear side of the second pressing rod (45), the two mounting columns (48) are fixedly connected to the front side of the protection pad (47), and the mounting columns (48) are clamped with the mounting holes on the second pressing rod (45) in a matched mode.
6. The front bearing stop shaft penetration device of a small turbojet engine according to claim 1, wherein: the shaft penetrating pressing mechanism (3) comprises a pressing column (31), a pressing power assembly and a pressing rod I (37), wherein the transverse pressing rod I (37) is arranged in front of the turbojet engine placing seat (1) through the pressing power assembly, the middle part of the rear side of the pressing rod I (37) is fixedly connected with the front end of the pressing column (31), and the rear end of the pressing column (31) is correspondingly arranged with the shaft limiting sleeve (23).
7. The front bearing stop axle penetration device for a small turbojet engine of claim 6, wherein: the pressing power assembly comprises a connecting block (32), a shaft penetrating cylinder (33), a fixed seat (34), a pull rod (35) and a fixing bolt (36), wherein two fixed seats (34) are fixedly connected to two sides of the turbojet engine placement seat (1) respectively, two connecting blocks (32) are fixedly connected to the rear sides of the two fixed seats (34) through the two longitudinal shaft penetrating cylinders (33) respectively, the tops of the two connecting blocks (32) are fixedly connected with the rear ends of the two pull rods (35) respectively, and the front ends of the two pull rods (35) are fixedly connected with two ends of a pressing rod (37) through the fixing bolt (36) respectively.
8. The front bearing stop shaft penetration device of a small turbojet engine according to claim 1, wherein: the bearing stop mechanism (5) comprises a longitudinal moving assembly, a vertical rod (56), a circular ring (57) and a stop friction ring (58), wherein the circular ring (57) is fixedly connected to the rear end of the bottom of the turbojet engine placement seat (1) through the vertical rod (56), the circular ring (57) is positioned on the right rear side of the shaft limiting sleeve (23), and the stop friction ring (58) is fixedly connected to the front side of the circular ring (57).
9. The front bearing stop axle penetration device of a small turbojet engine of claim 8, wherein: the vertical movement assembly comprises a support (51), a vertical sliding column (52), a sliding seat (53), a vertical stud (54) and a hand wheel (55), wherein the support (51) is fixedly connected to the rear end of the bottom of the turbojet engine placement seat (1), the vertical sliding column (52) is fixedly connected to the inside of the support (51), the vertical stud (54) is rotationally connected to the inside of the support (51), the hand wheel (55) is fixedly connected to the rear end of the vertical stud (54), the vertical stud (54) is in threaded connection with a threaded hole on the sliding seat (53), and a sliding hole on the sliding seat (53) is in sliding connection with the vertical sliding column (52).
10. The front bearing stop shaft penetration device of a small turbojet engine according to claim 1, wherein: the turbojet engine placement seat further comprises supporting legs (6), and four bottom corners of the turbojet engine placement seat (1) are fixedly connected with four supporting legs (6) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323271521.4U CN221716746U (en) | 2023-12-01 | 2023-12-01 | Front bearing stop shaft penetrating device of small turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323271521.4U CN221716746U (en) | 2023-12-01 | 2023-12-01 | Front bearing stop shaft penetrating device of small turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221716746U true CN221716746U (en) | 2024-09-17 |
Family
ID=92687794
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323271521.4U Active CN221716746U (en) | 2023-12-01 | 2023-12-01 | Front bearing stop shaft penetrating device of small turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221716746U (en) |
-
2023
- 2023-12-01 CN CN202323271521.4U patent/CN221716746U/en active Active
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