CN114954998A

CN114954998A - Auxiliary tool for aerodynamic shaping of aircraft engine inlet duct

Info

Publication number: CN114954998A
Application number: CN202210546336.2A
Authority: CN
Inventors: 张伟光; 巩小波; 孙维放; 于晨子
Original assignee: Shandong Taikoo Aircraft Engineering Co Ltd
Current assignee: Shandong Taikoo Aircraft Engineering Co Ltd
Priority date: 2022-05-20
Filing date: 2022-05-20
Publication date: 2022-08-30

Abstract

The utility model provides an auxiliary fixtures for aerodynamic shaping of aircraft engine intake duct, adjusts the interval between linking arm and the lower linking arm through vertical adjusting device to ensure that the scraper blade lower extreme contacts with the inner wall of engine intake duct, can make the fixed arm sideslip through horizontal adjustment mechanism, thereby make the scraper blade remove to the operation position. Because the engine air inlet channel is an inclined plane, the deflection angle of the scraper blade can be adjusted through the angle adjusting device, and the lower end face of the scraper blade is ensured to be fully contacted with the inner wall of the engine air inlet channel. Go up the linking arm and be connected through rotating connecting device with branch, consequently the scraper blade can rotate around branch to carry out the plastic to the part that coats aerodynamic nature and glue in the circumferencial direction, improved efficiency, ensure the sealed precision of engine aerodynamic nature, ensured the safe operation of aircraft.

Description

Auxiliary tool for aerodynamic shaping of aircraft engine inlet duct

Technical Field

The invention relates to the technical field of aircraft maintenance, in particular to an auxiliary tool for aerodynamic shaping of an air inlet passage of an aircraft engine.

Background

The structure of the engine air inlet channel around the engine blade adopts a structure formed by a specially-made sealant in order to meet the special requirements of the aerodynamic performance of the engine, but the region is in a core region in the engine and is in a high-wind-speed and high-oscillation region, so that the aerodynamic sealant structure at the position is easy to shake and fall off or impact and fall off by foreign objects, the overall aerodynamic performance of the engine can be influenced after damage occurs, the engine needs to be stopped for repair, when the position is repaired, the damaged position can only be manually repaired, although the requirements of construction process standards are met, the precision is still different from the original position of leaving a factory, and in the construction process, due to the lack of an auxiliary tool, the construction technical requirements of workers are high, the efficiency of the operation process is low, repeated correction and trimming are needed, and a great amount of time is consumed.

Disclosure of Invention

The invention provides an auxiliary tool for improving the aerodynamic shaping working efficiency and precision of an engine cementing material structure around an aircraft inlet blade in order to overcome the defects of the prior art.

The technical scheme adopted by the invention for overcoming the technical problems is as follows:

the utility model provides an auxiliary fixtures that is used for aerodynamic shaping of aircraft engine intake duct, includes:

the outer end of the bracket fixing disc is coaxially provided with a supporting rod;

the upper end of the upper connecting arm is rotationally connected with the head end of the supporting rod through a rotating connecting device;

the support arms are arranged at intervals along the circumferential direction, the inner side ends of the support arms are mounted at the inner side ends of the support fixing disc through an adjusting mechanism, the support arms are adjusted in angle along the circumferential direction through the adjusting mechanism, mounting holes are formed in the outer side ends of the support arms, and bolts II penetrate through the mounting holes and then are fixed in screw holes of an engine front cone of an engine air inlet channel;

the lower end of the lower connecting arm is provided with a sliding hole along the horizontal direction, the lower end of the upper connecting arm is connected with the upper end of the lower connecting arm through a longitudinal adjusting device, and the longitudinal adjusting device is used for adjusting the distance between the upper connecting arm and the lower connecting arm;

the transverse adjusting mechanism is used for adjusting the horizontal position of the fixed arm; and

the scraper blade is connected with the fixed arm through an angle adjusting device, and the angle adjusting device is used for adjusting the angle of the scraper blade to enable the lower end face of the scraper blade to be in surface contact with the inner wall of the engine air inlet channel.

Furthermore, the rotating connection device comprises an optical axis end coaxially arranged at the head end of the support rod and a threaded end coaxially arranged at the head end of the optical axis end, the upper end of the upper connection arm is provided with a bearing, the optical axis end penetrates through an inner hole of the bearing, and the nut is screwed on the threaded end to lock and fix the support rod relative to the upper connection arm in the axial direction.

Furthermore, above-mentioned adjustment mechanism includes that the center that uses the support fixed disk sets up in 3 of support fixed disk medial extremity along the circumferencial direction interval and is convex track groove and main part fixed disk as the centre of a circle, the medial extremity of main part fixed disk is provided with 3 along the circumferencial direction interval and is convex track grooves, the medial extremity of support arm is provided with convex slider, both ends block respectively in the track groove of support fixed disk and main part fixed disk around the slider, and a plurality of bolts I fit soon in the main part fixed disk after passing the support fixed disk.

Furthermore, the longitudinal adjusting device comprises a connecting frame in a rectangular frame structure, a sliding sleeve I arranged at the upper end of the connecting frame, and a sliding sleeve II arranged at the lower end of the connecting frame, wherein a track groove I is formed in the side end of the upper connecting arm along the length direction of the upper connecting arm, a track groove II is formed in the side end of the lower connecting arm along the length direction of the lower connecting arm, the lower end of the upper connecting arm is inserted into the sliding sleeve I in a sliding manner, a set screw I is screwed into the sliding sleeve I, a bolt head of the set screw I is inserted into the track groove I, the upper end of the lower connecting arm is inserted into the sliding sleeve II in a sliding manner, a set screw II is screwed into the sliding sleeve II, a bolt head of the set screw II is inserted into the track groove II, a screw I is coaxially arranged at the upper end of the knob I, a screw II is coaxially arranged at the lower end of the knob I, the upper end of the screw I is in threaded transmission connection with the upper connecting arm, and the lower end of the screw II is in threaded transmission connection with the lower connecting arm, the screw I and the screw II have opposite thread directions.

Furthermore, the transverse adjusting mechanism comprises a knob II, a screw III is coaxially arranged on one side of the knob II, a screw IV is coaxially arranged on the other side of the knob II, the screw IV is in threaded transmission connection with the lower connecting arm, the screw III is in threaded transmission connection with the fixed arm, and the thread turning directions of the screw III and the screw IV are opposite.

Further, above-mentioned angle adjusting device is including setting up respectively in ear seat I and ear seat II of scraper blade upper end both sides, the screw rod V and the screw rod VI that fit in the fixed arm both ends soon along vertical direction respectively, knob III is installed to screw rod V's head end, knob IV is installed to screw rod VI's head end, screw rod V's lower extreme is rotated and is connected with free bearing I, free bearing II is installed in the lower extreme rotation of screw rod VI, be provided with the slot hole along the horizontal direction respectively on ear seat I and the ear seat II, the round pin axle I is fixed in the lower extreme of free bearing I after passing the slot hole of ear seat I, and round pin axle II is fixed in the lower extreme of free bearing II after passing the slot hole of ear seat II.

The invention has the beneficial effects that: the distance between the upper connecting arm and the lower connecting arm is adjusted through the longitudinal adjusting device, so that the lower end of the scraper blade is ensured to be in contact with the inner wall of an engine air inlet channel, the fixed arm can transversely move through the transverse adjusting mechanism, and the scraper blade is moved to an operation position. Because the engine air inlet channel is an inclined plane, the deflection angle of the scraper blade can be adjusted through the angle adjusting device, and the lower end face of the scraper blade is ensured to be fully contacted with the inner wall of the engine air inlet channel. The upper connecting arm is connected with the support rod through the rotating connecting device, so that the scraper can rotate around the support rod, the part coated with the pneumatic glue is shaped in the circumferential direction, the efficiency is improved, the precision of the pneumatic sealing of the engine is ensured, and the safe operation of the airplane is guaranteed.

Drawings

FIG. 1 is a schematic perspective view of the present invention;

FIG. 2 is a schematic structural view of a fixing disk portion of the main body of the present invention;

FIG. 3 is a schematic view of the present invention in use;

FIG. 4 is a schematic view of a squeegee portion of the invention;

in the drawing, 1, a main body fixing plate 2, a support fixing plate 3, a support 4, a mounting hole 5, a bolt I6, a support rod 7, a nut 8, a connecting frame 9, a sliding sleeve I10, a sliding sleeve II 11, an upper connecting arm 12, a track groove I13, a set screw I14, a lower connecting arm 15, a track groove II 16, a set screw II 17, a knob I18, a screw I19, a screw II 20, a knob II 21, a screw III 22, a screw IV 23, a fixing arm 24, a guide rod 25, a knob III 26, a knob IV 27, a screw V28, a screw VI 29, a hinge seat I30, a hinge seat II 31, a scraper 32, a pin I33, a pin II 34, a track groove 35, a sliding block 36, a threaded end 37, an engine air inlet 39, a front cone 40, a bolt II 41, a lug seat I42 and a lug seat II 43 are arranged.

Detailed Description

The invention will be further described with reference to fig. 1 to 4.

The utility model provides an auxiliary fixtures that is used for aerodynamic shaping of aircraft engine intake duct, includes: the bracket fixing disc 2 is coaxially provided with a supporting rod 6 at the outer end; the upper end of the upper connecting arm 11 is rotationally connected with the head end of the supporting rod 6 through a rotary connecting device; the support arms 3 are arranged at intervals along the circumferential direction, the inner side ends of the support arms 3 are mounted at the inner side ends of the support fixing discs 2 through adjusting mechanisms, the angles of the support arms 3 are adjusted along the circumferential direction through the adjusting mechanisms, mounting holes 4 are formed in the outer side ends of the support arms 3, and bolts II 40 penetrate through the mounting holes 4 and then are fixed in screw holes of engine front cones 39 of the engine air inlet 38; the lower end of the lower connecting arm 14 is provided with a sliding hole along the horizontal direction, the lower end of the upper connecting arm 11 is connected with the upper end of the lower connecting arm 14 through a longitudinal adjusting device, and the longitudinal adjusting device is used for adjusting the distance between the upper connecting arm 11 and the lower connecting arm 14; a guide rod 24 is installed on one side of the fixing arm 23, the guide rod 24 is installed in a sliding hole in the lower end of the lower connecting arm 14 in a sliding mode, and the transverse adjusting mechanism is used for adjusting the horizontal position of the fixing arm 23; and a scraper 31 connected to the fixing arm 23 through an angle adjusting device for adjusting the angle of the scraper 31 so that the lower end face of the scraper 31 is in surface contact with the inner wall of the engine intake duct 38. According to the different positions of the screw holes on the engine front cones 39 of different airplane models, the positions of the brackets 3 are adjusted through the adjusting structure, if the radius of the screw hole is changed, the brackets 3 with different specifications need to be replaced, finally, the mounting hole 4 is coincided with the screw hole, and the whole auxiliary tool is installed and fixed by screwing the bolt on the corresponding screw hole after penetrating through the mounting hole 4. The distance between the upper connecting arm 11 and the lower connecting arm 14 is adjusted by the longitudinal adjusting device so as to ensure that the lower end of the scraper 31 is in contact with the inner wall of the engine intake duct 38, and the fixed arm 23 can be traversed by the transverse adjusting mechanism so as to move the scraper 31 to the working position. Since the engine intake duct 38 is a slope, the deflection angle of the blade 31 can be adjusted by the angle adjusting device, ensuring that the lower end surface of the blade 31 is in sufficient contact with the inner wall of the engine intake duct 38. Go up linking arm 11 and branch 6 and be connected through rotating connecting device, consequently scraper blade 31 can rotate around branch 6 to the part of coating aerodynamic glue is reshaped in the circumferencial direction, has improved efficiency, ensures the sealed precision of engine aerodynamic, has ensured the safe operation of aircraft.

The rotary connecting device may be a structure including an optical axis end 36 coaxially disposed at the head end of the strut 6 and a threaded end 37 coaxially disposed at the head end of the optical axis end 36, the upper end of the upper connecting arm 11 is mounted with a bearing, the optical axis end 36 passes through an inner hole of the bearing, and the nut 7 is screwed on the threaded end 37 to lock and fix the strut 6 relative to the upper connecting arm 11 in the axial direction. The optical axis end 36 at the head end of the strut 6 is rotatably connected with the upper connecting arm 11 by a bearing, so that the rotating process of each bracket 3 is smooth.

The adjusting mechanism can be of a structure comprising 3 arc-shaped track grooves 34 and a main body fixing disk 1, wherein the 3 arc-shaped track grooves 34 are arranged at the inner side end of the support fixing disk 2 at intervals along the circumferential direction by taking the center of the support fixing disk 2 as a circle center, the 3 arc-shaped track grooves 34 are arranged at the inner side end of the main body fixing disk 1 at intervals along the circumferential direction, arc-shaped sliding blocks 35 are arranged at the inner side end of the support arm 3, the front end and the rear end of each sliding block 35 are respectively clamped in the track grooves 34 of the support fixing disk 2 and the track grooves 34 of the main body fixing disk 1, and a plurality of bolts I5 penetrate through the support fixing disk 2 and then are screwed in the main body fixing disk 1. According to different screw hole positions of engine front cones 39 of different types, the sliding blocks 35 can slide in the track grooves 34 of the main body fixing disc 1 and the support fixing disc 2 to realize the position adjustment of each support 3, so that the mounting holes 4 in the supports 3 are overlapped with the screw hole positions of the engine front cones 39, the bolts I5 are screwed after the adjustment is in place, the main body fixing disc 1 and the support fixing disc 2 are matched with each other to extrude and fix the sliding blocks 35, and the position fixing of the supports 3 is realized.

The longitudinal adjusting device can be a structure which comprises a connecting frame 8 in a rectangular frame structure, a sliding sleeve I9 arranged at the upper end of the connecting frame 8 and a sliding sleeve II 10 arranged at the lower end of the connecting frame 8, wherein a track groove I12 is formed in the side end of an upper connecting arm 11 along the length direction of the side end, a track groove II 15 is formed in the side end of a lower connecting arm 14 along the length direction of the side end, the lower end of the upper connecting arm 11 is inserted into the sliding sleeve I9 in a sliding manner, a set screw I13 is screwed into the sliding sleeve I9, the bolt head of the set screw I13 is inserted into the track groove I12, the upper end of the lower connecting arm 14 is inserted into the sliding sleeve II 10 in a sliding manner, a set screw II 16 is screwed into the sliding sleeve II 10, the bolt head of the set screw II 16 is inserted into the track groove II 15, a screw I18 is coaxially arranged at the upper end of a knob I17, and a screw II 19 is coaxially arranged at the lower end of the knob I, the upper end of the screw I18 is in threaded transmission connection with the upper connecting arm 11, the lower end of the screw II 19 is in threaded transmission connection with the lower connecting arm 14, and the thread turning directions of the screw I18 and the screw II 19 are opposite. When the longitudinal adjustment is needed, the knob I17 is rotated, so that the screw I18 and the screw II 19 synchronously rotate, the screw thread turning directions of the screw I18 and the screw II 19 are opposite, the upper connecting arm 11 is enabled to synchronously slide inwards or outwards in the sliding sleeve I9 and the lower connecting arm 14 is enabled to synchronously slide inwards or outwards in the sliding sleeve II 10, the set screw I13 plays a guiding role in the track groove I12 and the set screw II 16 plays a guiding role in the track groove II 15 during sliding, and after the adjustment is in place, the set screw I13 and the set screw II 16 are screwed, so that the screw heads are respectively contacted with the bottoms of the corresponding track groove I12 and the track groove II 15, and the locking and fixing of the positions of the upper connecting arm 11 and the lower connecting arm 14 are realized.

The transverse adjusting mechanism can be of a structure comprising a knob II 20, wherein a screw III 21 is coaxially arranged on one side of the knob II 20, a screw IV 22 is coaxially arranged on the other side of the knob II 20, the screw IV 22 is in threaded transmission connection with the lower connecting arm 14, the screw III 21 is in threaded transmission connection with the fixed arm 23, and the thread turning directions of the screw III 21 and the screw IV 22 are opposite. When the transverse adjustment is needed, the knob II 20 is rotated, so that the screw III 21 and the screw IV 22 rotate synchronously, and the fixed arm 23 horizontally slides relative to the lower connecting arm 14 and the guide rod 24 slides in the sliding hole to play a guiding role due to the fact that the thread turning directions of the screw III 21 and the screw IV 22 are opposite.

The angle adjusting device can be of a structure comprising an ear seat I41 and an ear seat II 42 which are respectively arranged on two sides of the upper end of the scraping plate 31, a screw rod V27 and a screw rod VI 28 which are respectively screwed on two ends of the fixed arm 23 along the vertical direction, a knob III 25 is arranged at the head end of the screw rod V27, a knob IV 26 is arranged at the head end of the screw rod VI 28, the lower end of the screw rod V27 is rotatably connected with a hinge seat I29, a hinge seat II 30 is rotatably arranged at the lower end of the screw rod VI 28, long holes 43 are respectively arranged on the ear seat I41 and the ear seat II 42 along the horizontal direction, a pin shaft I32 is fixed at the lower end of the hinge seat I29 after penetrating through the long hole 43 of the ear seat I41, and a pin shaft II 33 is fixed at the lower end of the hinge seat II 30 after penetrating through the long hole 43 of the ear seat II 42. When the knob III 25 or the knob IV 26 is rotated, the screw V27 or the screw VI 28 is driven to rotate respectively, the screw V27 is rotatably connected with the hinged support I29, the screw VI 28 is rotatably connected with the hinged support II 30, so that the hinged support I29 or the hinged support II 30 is driven to move in the vertical direction respectively, the ear support I41 and the ear support II 42 of the scraper 31 are provided with long holes 43, the long holes 43 are respectively hinged with the hinged support I29 through pin shafts I32 and the hinged support II 30 through pin shafts II 33, the long holes 43 are matched in phase to prevent interference, and the angle deflection of the scraper 31 is realized by adjusting different heights of the screw V27 or the screw VI 28.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an auxiliary fixtures that is used for aerodynamic shaping of aircraft engine intake duct which characterized in that includes:

the bracket fixing disc (2) is coaxially provided with a supporting rod (6) at the outer end;

the upper end of the upper connecting arm (11) is rotationally connected with the head end of the supporting rod (6) through a rotary connecting device;

the support arm fixing device comprises 3 support arms (3) which are arranged at intervals along the circumferential direction, the inner side end of each support arm (3) is installed at the inner side end of a support fixing disc (2) through an adjusting mechanism, the angle of each support arm (3) is adjusted along the circumferential direction through the adjusting mechanism, an installation hole (4) is formed in the outer side end of each support arm (3), and a bolt II (40) penetrates through the installation hole (4) and then is fixed in a screw hole of an engine front cone (39) of an engine air inlet channel (38);

the lower end of the lower connecting arm (14) is provided with a sliding hole along the horizontal direction, the lower end of the upper connecting arm (11) is connected with the upper end of the lower connecting arm (14) through a longitudinal adjusting device, and the longitudinal adjusting device is used for adjusting the distance between the upper connecting arm (11) and the lower connecting arm (14);

the fixing arm (23) is provided with a guide rod (24) at one side, the guide rod (24) is slidably arranged in a sliding hole at the lower end of the lower connecting arm (14), and the transverse adjusting mechanism is used for adjusting the horizontal position of the fixing arm (23); and

the scraping plate (31) is connected with the fixed arm (23) through an angle adjusting device, and the angle adjusting device is used for adjusting the angle of the scraping plate (31) so that the lower end face of the scraping plate (31) is in surface contact with the inner wall of the engine air inlet (38).

2. The auxiliary tool for aerodynamic shaping of an aircraft engine inlet according to claim 1, characterized in that: the rotating connecting device comprises a smooth shaft end (36) and a threaded end (37), the smooth shaft end (36) is coaxially arranged at the head end of the supporting rod (6), the threaded end (37) is coaxially arranged at the head end of the smooth shaft end (36), a bearing is installed at the upper end of the upper connecting arm (11), the smooth shaft end (36) penetrates through an inner hole of the bearing, and the supporting rod (6) is locked and fixed in the axial direction relative to the upper connecting arm (11) on the threaded end (37) through screwing of a nut (7).

3. The auxiliary tool for aerodynamic shaping of an aircraft engine inlet according to claim 1, characterized in that: adjustment mechanism includes that the center that uses support fixed disk (2) sets up in 3 of support fixed disk (2) medial extremity along the circumferencial direction interval as the centre of a circle and is convex track groove (34) and main part fixed disk (1), the medial extremity of main part fixed disk (1) is provided with 3 along the circumferencial direction interval and is convex track groove (34), the medial extremity of support arm (3) is provided with convex slider (35), the front and back both ends of slider (35) are blocked respectively and are arranged in track groove (34) of support fixed disk (2) and main part fixed disk (1), and a plurality of bolts I (5) are fit in main part fixed disk (1) soon after passing support fixed disk (2).

4. The auxiliary tool for aerodynamic shaping of an aircraft engine inlet according to claim 1, is characterized in that: the longitudinal adjusting device comprises a connecting frame (8) in a rectangular frame structure, a sliding sleeve I (9) arranged at the upper end of the connecting frame (8), and a sliding sleeve II (10) arranged at the lower end of the connecting frame (8), wherein a track groove I (12) is formed in the side end of an upper connecting arm (11) along the length direction of the upper connecting arm, a track groove II (15) is formed in the side end of a lower connecting arm (14) along the length direction of the lower connecting arm, the lower end of the upper connecting arm (11) is inserted into the sliding sleeve I (9) in a sliding manner, a set screw I (13) is screwed into the sliding sleeve I (9), the bolt head of the set screw I (13) is inserted into the track groove I (12), the upper end of the lower connecting arm (14) is inserted into the sliding sleeve II (10) in a sliding manner, a set screw II (16) is screwed into the sliding sleeve II (10), and the bolt head of the set screw II (16) is inserted into the track groove II (15), the upper end of the knob I (17) is coaxially provided with a screw rod I (18), the lower end of the knob I is coaxially provided with a screw rod II (19), the upper end of the screw rod I (18) is in threaded transmission connection with the upper connecting arm (11), the lower end of the screw rod II (19) is in threaded transmission connection with the lower connecting arm (14), and the thread turning directions of the screw rod I (18) and the screw rod II (19) are opposite.

5. The auxiliary tool for aerodynamic shaping of an aircraft engine inlet according to claim 1, characterized in that: horizontal adjustment mechanism includes knob II (20), one side coaxial arrangement of knob II (20) has screw rod III (21), and its opposite side coaxial arrangement has screw rod IV (22), screw rod IV (22) are connected with lower linking arm (14) screw thread transmission, screw rod III (21) are connected with fixed arm (23) screw thread transmission, screw rod III (21) are opposite with the screw thread of screw rod IV (22) soon.

6. The auxiliary tool for aerodynamic shaping of an aircraft engine inlet according to claim 1, is characterized in that: the angle adjusting device comprises an ear seat I (41) and an ear seat II (42) which are respectively arranged at the two sides of the upper end of the scraping plate (31), a screw rod V (27) and a screw rod VI (28) which are respectively screwed at the two ends of the fixed arm (23) along the vertical direction, a knob III (25) is arranged at the head end of the screw rod V (27), a knob IV (26) is arranged at the head end of the screw rod VI (28), the lower end of the screw rod V (27) is rotatably connected with a hinged support I (29), the lower end of the screw rod VI (28) is rotatably provided with a hinged support II (30), and the ear seat I (41) and the ear seat II (42) are respectively provided with a long hole (43) along the horizontal direction, the pin shaft I (32) penetrates through the long hole (43) of the ear seat I (41) and then is fixed at the lower end of the hinged seat I (29), and the pin shaft II (33) penetrates through the long hole (43) of the ear seat II (42) and then is fixed at the lower end of the hinged seat II (30).