An aircraft engine with a connection assembly

Abstract

The present invention discloses an aero-engine with a connection assembly, including an engine body, one side of the engine body is rotatably connected to a flight propeller through a rotating shaft, the other side of the engine body is movably connected to a gearbox, and the top and bottom of the engine body and the gearbox are fixedly installed with a total of four connection assemblies; the connection assembly includes a connection shell fixed to the engine body and the gearbox, and a socket is fixed inside the connection shell. The present invention relates to the field of aero-engine technology. The aero-engine with a connection assembly, through the coordinated use of the connection assembly and the linkage assembly, enables the socket to be inserted into the connection shell, thereby realizing a locking connection between the two connection shells, thereby realizing a quick installation connection between the gearbox and the engine body. This design not only simplifies the cumbersome steps of the traditional bolt connection method, but also greatly improves the efficiency and convenience of the installation connection.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, in particular to an aeroengine with a connection assembly. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry.

[0003] Referring to the Chinese patent, aircraft engine connection assembly and aircraft engine (publication number: CN214118904U, publication date: 2021-09-03), this patent solves the problem that during the installation process, in order to improve the installation accuracy, the adjustment pad needs to be continuously replaced so that the bolt hole on the quick release ring and the bolt hole position on the gear box casing are exactly matched when the quick release ring is screwed to the tightening position. This process generally makes the operation and assembly cycle longer, and a large number of adjustment pads of different sizes need to be backed up, which brings many inconveniences. However, the existing aircraft engine and the gearbox need to be tightened by a large number of bolts. Not only are the disassembly and assembly steps cumbersome, but accidents are prone to occur after the bolts become loose. In addition, when the engine drives the flight propeller to rotate, a small amount of external dust will adhere to the rotating shaft of the flight propeller, which is easily infiltrated by lubricating oil to increase adhesion. Since the space is relatively small, a large number of engine parts need to be removed for cleaning, and the cleaning efficiency is relatively low. In this regard, we propose an aircraft engine with a connection assembly to solve the above problems. Summary of the invention

[0004] In view of the deficiencies of the prior art, the present invention provides an aircraft engine with a connection assembly, which solves the problems raised in the background technology.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions: an aeroengine with a connection assembly, comprising an engine body, one side of the engine body is rotatably connected to a flight propeller through a rotating shaft, the other side of the engine body is movably connected to a gear box, and a total of four connection assemblies are fixedly installed on the top and bottom of the engine body and the gear box;

[0006] The connecting assembly includes a connecting shell fixed on the engine body and the gear box, the connecting shell is fixed with a socket inside, the socket is provided with a semicircular groove inside, one side of the socket is provided with an arc through groove, the arc through groove is communicated with the semicircular groove, a semicircular block is rotatably connected inside the semicircular groove, a connecting rod is fixed on one side of the semicircular block, one side of the connecting shell is penetrated by a slide groove, one end of the connecting rod penetrates the arc through groove and the slide groove and extends to the outside of the connecting shell, the outer surface of the connecting rod is slidably connected with the inner surface of the slide groove, one side of the connecting shell is penetrated by a square groove, a tube body is arranged inside the connecting shell, one end of the tube body is slidably connected with a hook 1, one end of the hook 1 is hooked on the connecting rod, the other end of the hook 1 penetrates one end of the tube body and extends to the inside of the tube body, a circular plate is fixed on the other end of the hook 1, a spring 1 is fixed between one side of the circular plate and the inner wall of the tube body, a hook 2 is fixed on the other end of the tube body, a hanging ear is fixed on the connecting shell, and the hook 2 is hooked on the hanging ear.

[0007] Preferably, one end of the socket extends to the inside of another connecting shell, and the inclined surface of the socket contacts and is pressed against one surface of the semicircular block.

[0008] Preferably, a linkage assembly is arranged between the upper and lower connecting assemblies, and the linkage assembly includes a fixed block fixed on one side of the upper and lower connecting rods, a cross bar is arranged on one side of the upper and lower connecting rods, a ring is fixed at one end of the two cross bars, and the two rings are sleeved on the connecting rods, a connecting plate is fixed between one end of the two cross bars, and a pull ring is fixed on one side of the connecting plate.

[0009] Preferably, the engine body is provided with an automatic cleaning component for cleaning the rotating shaft, and the automatic cleaning component includes a vertical plate arranged on one side of the engine body, two horizontal plates are fixed to one side of the vertical plate, square rods are fixed to one side of the two horizontal plates, the opposite ends of the two square rods are fixed to the top and bottom of the engine body, and a bidirectional screw is rotatably connected between the opposite sides of the two horizontal plates.

[0010] Preferably, a motor is fixed to the top of the upper horizontal plate, the output end of the motor is fixed to the top of the bidirectional screw rod through a coupling, two movable seats are provided on one side of the vertical plate, and one end of the bidirectional screw rod passes through the two movable seats and extends to the outside of the movable seat.

[0011] Preferably, the inner surfaces of the two movable seats are threadedly connected to the outer surface of the bidirectional screw rod, an insertion rod is provided on one side of the two movable seats, an L-shaped rod is fixed at one end of the two insertion rods, arc plates are fixed at the opposite ends of the two L-shaped rods, cleaning bristles are fixed on the opposite sides of the two arc plates, and the cleaning bristles are in contact with the outer surface of the rotating shaft.

[0012] Preferably, a disassembly and replacement component is provided between the two insertion rods and the movable seat, and the disassembly and replacement component includes a groove opened on one side of the movable seat, one end of the insertion rod extends to the inside of the groove, a transverse groove is opened inside the movable seat, a slot is opened on one side of the insertion rod, and a locking rod is slidably connected to one side of the movable seat, and one end of the locking rod passes through the movable seat and the transverse groove and extends to the inside of the slot.

[0013] Preferably, a slide plate is fixed to the outer surface of the locking rod, and the outer surface of the slide plate is slidably connected to the inner surface of the transverse groove. A second spring is sleeved on the outer surface of the locking rod, one end of the second spring is fixed to one side of the slide plate, and the other end of the second spring is fixed to the inner wall of the transverse groove. A second pull ring is fixed to the other end of the locking rod.

[0014] Beneficial Effects

[0015] The present invention provides an aircraft engine with a connection assembly. Compared with the prior art, it has the following advantages:

[0016] Beneficial effects:

[0017] (1) The aircraft engine with a connecting assembly, through the coordinated use of the connecting assembly and the linkage assembly, enables the socket to be inserted into the connecting shell, thereby realizing a locking connection between the two connecting shells, thereby realizing a quick installation connection between the gear box and the engine body. This design not only simplifies the cumbersome steps of the traditional bolt connection method, but also greatly improves the efficiency and convenience of the installation connection.

[0018] (2) The aircraft engine with a connection component realizes automatic attachment of the bristles to the rotating shaft through the setting of the automatic dust cleaning component, and utilizes the rotation of the rotating shaft and the bristles to clean the dust adhering to the rotating shaft. The cleaning can be performed quickly even in a narrow space without removing the engine components for cleaning, which greatly improves the cleaning efficiency.

[0019] (3) The aircraft engine with the connection assembly realizes the rapid disassembly, assembly and replacement of the cleaning brush by means of the disassembly and assembly replacement assembly. When the cleaning brush becomes dirty, it can be disassembled and cleaned or replaced in time, thus ensuring that the dust on the rotating shaft can be cleaned in time with clean bristles. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a three-dimensional diagram of the external structure of the present invention;

[0021] Figure 2 It is a stereoscopic diagram of the connection assembly and linkage assembly of the present invention;

[0022] Figure 3 For the present invention Figure 2 A partial enlarged view of the middle A;

[0023] Figure 4 It is a diagram of the separation state of two connection components of the present invention;

[0024] Figure 5 It is a cross-sectional view of two connection components of the present invention;

[0025] Figure 6 For the present invention Figure 5 A partial enlarged view of point B in the middle;

[0026] Figure 7 A three-dimensional diagram of the automatic dust cleaning component of the present invention;

[0027] Figure 8 It is a cross-sectional view of the movable seat of the present invention.

[0028] In the figure: 1, engine body; 2, rotating shaft; 3, flying propeller; 4, gear box; 5, connecting assembly; 6, linkage assembly; 7, automatic dust cleaning assembly; 8, disassembly and replacement assembly; 51, connecting shell; 52, socket; 53, semicircular groove; 54, arc-shaped through groove; 55, semicircular block; 56, connecting rod; 57, slide groove; 58, square groove; 59, tube body; 510, hook 1; 511, round plate; 512, spring 1; 513, hook 2; 514, ear; 61, fixing block; 62, horizontal bar; 63, collar; 64, connecting plate; 65, pull ring one; 71, vertical plate; 72, horizontal plate; 73, square rod; 74, two-way screw rod; 75, motor; 76, moving seat; 77, plug rod; 78, L-shaped rod; 79, arc plate; 710, cleaning brush; 81, groove; 82, horizontal groove; 83, slot; 84, locking rod; 85, slide plate; 86, spring two; 87, pull ring two. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] The present invention provides three technical solutions, including the following embodiments:

[0031] Example 1

[0032] See also Figure 1-Figure 6, an aero engine with a connection assembly, comprising an engine body 1, one side of the engine body 1 is rotatably connected to a flight propeller 3 through a rotating shaft 2, a drive shaft in the engine body 1 is fixed to the rotating shaft 2 through a coupling, the other side of the engine body 1 is movably connected to a gear box 4, a reduction gear set is arranged inside the gear box 4, and a total of four connection assemblies 5 are fixedly installed on the top and bottom of the engine body 1 and the gear box 4;

[0033] The connecting assembly 5 includes a connecting shell 51 fixed on the engine body 1 and the gear box 4, a socket 52 is fixed inside the connecting shell 51, two inclined surfaces are arranged on the socket 52, a semicircular groove 53 is provided inside the socket 52, an arcuate through groove 54 is provided on one side of the socket 52, the arcuate through groove 54 is communicated with the semicircular groove 53, a semicircular block 55 is rotatably connected inside the semicircular groove 53, a connecting rod 56 is fixed on one side of the semicircular block 55, a slide groove 57 is penetrated through one side of the connecting shell 51, one end of the connecting rod 56 penetrates the arcuate through groove 54 and the slide groove 57 and extends to the outside of the connecting shell 51, the outer surface of the connecting rod 56 is slidably connected to the inner surface of the slide groove 57, and the connecting shell 51 is provided with a semicircular block 55. A square groove 58 is provided through one side, and a tube body 59 is provided inside the connecting shell 51. A hook 510 is slidably connected to one end of the tube body 59. One end of the hook 510 is hooked on the connecting rod 56, and the hook 510 can pull the connecting rod 56 to rotate. The other end of the hook 510 passes through one end of the tube body 59 and extends to the inside of the tube body 59. A circular plate 511 is fixed to the other end of the hook 510. A spring 512 is fixed between one side of the circular plate 511 and the inner wall of the tube body 59. A hook 2 513 is fixed to the other end of the tube body 59. A hanging ear 514 is fixed on the connecting shell 51. The hook 2 513 is hooked on the hanging ear 514, and the hook 2 513 can rotate on the hanging ear 514.

[0034] One end of the plug socket 52 extends to the inside of the other connection shell 51 , and the inclined surface of the plug socket 52 contacts and presses against one surface of the semicircular block 55 .

[0035] A linkage assembly 6 is arranged between the upper and lower connecting assemblies 5, and the linkage assembly 6 includes a fixed block 61 fixed on one side of the upper and lower connecting rods 56, a cross bar 62 is arranged on one side of the upper and lower connecting rods 56, one end of the two cross bars 62 is fixed with a ring 63, the two rings 63 are both sleeved on the connecting rod 56, a connecting plate 64 is fixed between one end of the two cross bars 62, and a pull ring 65 is fixed on one side of the connecting plate 64.

[0036] By using the connecting component 5 and the linkage component 6 in coordination, the socket 52 is inserted into the connecting shell 51, thereby realizing a locking connection between the two connecting shells 51, thereby realizing a quick installation connection between the gear box 4 and the engine body 1. This design not only simplifies the cumbersome steps of the traditional bolt connection method, but also greatly improves the efficiency and convenience of the installation connection.

[0037] Example 2

[0038] Based on Example 1, see Figure 7 As shown, the engine body 1 is provided with an automatic cleaning component 7 for cleaning the rotating shaft 2. The automatic cleaning component 7 includes a vertical plate 71 arranged on one side of the engine body 1, and two horizontal plates 72 are fixed to one side of the vertical plate 71. Square rods 73 are fixed to one side of the two horizontal plates 72. The opposite ends of the two square rods 73 are fixed to the top and bottom of the engine body 1. A bidirectional screw rod 74 is rotatably connected between the opposite sides of the two horizontal plates 72. The bidirectional screw rod 74 is a screw rod with two sections of threads with different rotation directions, that is, one section is a right-handed thread and the other section is a left-handed thread. When rotating, it can drive two movable seats 76 to move in opposite directions or back to back.

[0039] A motor 75 is fixed on the top of the upper horizontal plate 72. The motor 75 is a three-phase asynchronous motor that can be rotated forward and reversed. It is controlled by an external switch and is electrically connected to an external power supply. The output end of the motor 75 is fixed to the top of the bidirectional screw rod 74 through a coupling. Two movable seats 76 are provided on one side of the vertical plate 71. One end of the bidirectional screw rod 74 passes through the two movable seats 76 and extends to the outside of the movable seat 76.

[0040] The inner surfaces of the two movable seats 76 are threadedly connected to the outer surface of the bidirectional screw rod 74. An insertion rod 77 is provided on one side of the two movable seats 76. An L-shaped rod 78 is fixed at one end of the two insertion rods 77. Arc plates 79 are fixed at the opposite ends of the two L-shaped rods 78. Cleaning bristles 710 are fixed on the opposite sides of the two arc plates 79. The cleaning bristles 710 are in contact with the outer surface of the rotating shaft 2. When the two movable seats 76 move towards each other, the cleaning bristles 710 can be driven to fit the rotating shaft 2, and the self-rotation of the rotating shaft 2 can be further used to cooperate with the cleaning bristles 710 to clean it.

[0041] By setting up the automatic dust cleaning component 7, it is possible to automatically stick the bristles to the rotating shaft 2, utilize the rotation of the rotating shaft 2 and cooperate with the bristles to clean the dust stuck on the rotating shaft 2, and it can also clean quickly in a narrow space without removing engine parts for cleaning, thereby greatly improving the cleaning efficiency.

[0042] Example 3

[0043] Based on Example 2, see Figure 8As shown, a disassembly and replacement component 8 is provided between the two insertion rods 77 and the movable seat 76. The disassembly and replacement component 8 includes a groove 81 opened on one side of the movable seat 76, one end of the insertion rod 77 extends to the inside of the groove 81, the size of the insertion rod 77 is adapted to the size of the groove 81, a transverse groove 82 is opened inside the movable seat 76, a slot 83 is opened on one side of the insertion rod 77, a locking rod 84 is slidably connected to one side of the movable seat 76, one end of the locking rod 84 passes through the movable seat 76 and the transverse groove 82 and extends to the inside of the slot 83, the size of the locking rod 84 is adapted to the size of the slot 83, and the transverse groove 82 is connected to the slot 83.

[0044] A slide plate 85 is fixed to the outer surface of the locking rod 84, and the outer surface of the slide plate 85 is slidably connected to the inner surface of the transverse groove 82. A spring 2 86 is sleeved on the outer surface of the locking rod 84, and one end of the spring 2 86 is fixed to one side of the slide plate 85, and the other end of the spring 2 86 is fixed to the inner wall of the transverse groove 82. A pull ring 2 87 is fixed to the other end of the locking rod 84.

[0045] By setting up the disassembly and replacement component 8, the cleaning bristles 710 can be quickly disassembled and replaced. After the cleaning bristles 710 are dirty, they can be disassembled and cleaned or replaced in time, ensuring that the dust on the rotating shaft 2 can be cleaned in time with clean bristles.

[0046] Meanwhile, the contents not described in detail in this specification belong to the prior art known to those skilled in the art.

[0047] During operation, the gearbox 4 is docked to the engine body 1, so that the socket 52 is plugged into another connection shell 51, so that the inclined surface of the socket 52 contacts and squeezes one side of the semicircular block 55, so that the semicircular block 55 rotates, and the semicircular block 55 drives the connecting rod 56 to rotate, and at the same time the connecting rod 56 drives the hook 1 510 to pull the spring 1 512 to stretch. When the two connection shells 51 are completely docked, the two springs 2 86 are reset and contracted, further driving the two semicircular blocks 55 to reset, and then the two connection shells 51 are locked and connected together, so that the gearbox 4 is installed on the engine body 1. By pulling the two pull rings 1 65, the upper and lower connecting rods 56 can be driven to rotate, and then the gear box 4 can be removed. When it is necessary to clean the dust on the rotating shaft 2, the motor 75 is started to make the motor 75 drive the bidirectional screw rod 74 to rotate, and at the same time drive the two moving seats 76 to move towards each other, and finally make the two arc plates 79 move towards each other, so that the cleaning bristles 710 contact the rotating shaft 2. When the rotating shaft 2 rotates, the cleaning bristles 710 are used to clean off the dust. When it is necessary to clean and replace the cleaning bristles 710, pull the pull ring 2 87 to make the locking rod 84 slide out of the slot 83, and further pull out the plug rod 77.

[0048] The above embodiments of the invention are described in detail, but the contents are only preferred embodiments of the invention and cannot be considered to limit the scope of the invention. All equivalent changes and improvements made within the scope of the invention should still fall within the scope of the invention.

Claims

1. An aircraft engine with a connection assembly, comprising an engine body (1), characterized in that: One side of the engine body (1) is rotatably connected to a flying propeller (3) via a rotating shaft (2), and the other side of the engine body (1) is movably connected to a gear box (4), and a total of four connecting components (5) are fixedly installed on the top and bottom of the engine body (1) and the gear box (4); The connecting assembly (5) comprises a connecting shell (51) fixed on the engine body (1) and the gear box (4); a socket (52) is fixed inside the connecting shell (51); a semicircular groove (53) is provided inside the socket (52); an arcuate through groove (54) is provided on one side of the connecting shell (52); the arcuate through groove (54) is connected to the semicircular groove (53); a semicircular block (55) is rotatably connected inside the semicircular groove (53); a connecting rod (56) is fixed on one side of the semicircular block (55); a sliding groove (57) is provided through one side of the connecting shell (51); one end of the connecting rod (56) passes through the arcuate through groove (54) and the sliding groove (57) and extends to the outside of the connecting shell (51); the outer surface of the connecting rod (56) is aligned with the inner surface of the sliding groove (57). A square groove (58) is formed through one side of the connection shell (51), a tube body (59) is arranged inside the connection shell (51), one end of the tube body (59) is slidably connected with a hook 1 (510), one end of the hook 1 (510) is hooked on the connecting rod (56), the other end of the hook 1 (510) passes through one end of the tube body (59) and extends to the inside of the tube body (59), a circular plate (511) is fixed to the other end of the hook 1 (510), a spring 1 (512) is fixed between one side of the circular plate (511) and the inner wall of the tube body (59), a hook 2 (513) is fixed to the other end of the tube body (59), a hanging ear (514) is fixed on the connection shell (51), and the hook 2 (513) is hooked on the hanging ear (514).

2. An aircraft engine with a connection assembly according to claim 1, characterized in that: One end of the plug socket (52) extends to the inside of another connection shell (51), and the inclined surface of the plug socket (52) contacts and presses against one surface of the semicircular block (55).

3. An aircraft engine with a connection assembly according to claim 1, characterized in that: A linkage assembly (6) is provided between the upper and lower connection assemblies (5), and the linkage assembly (6) comprises a fixing block (61) fixed to one side of the upper and lower connecting rods (56), a cross bar (62) is provided on one side of the upper and lower connecting rods (56), a sleeve (63) is fixed to one end of the two cross bars (62), and the two sleeves (63) are sleeved on the connecting rod (56), a connecting plate (64) is fixed between one end of the two cross bars (62), and a pull ring (65) is fixed to one side of the connecting plate (64).

4. An aircraft engine with a connection assembly according to claim 1, characterized in that: The engine body (1) is provided with an automatic dust cleaning component (7) for cleaning dust at the rotating shaft (2), the automatic dust cleaning component (7) comprising a vertical plate (71) arranged on one side of the engine body (1), two horizontal plates (72) being fixed on one side of the vertical plate (71), square rods (73) being fixed on one side of the two horizontal plates (72), opposite ends of the two square rods (73) being fixed to the top and bottom of the engine body (1), and a bidirectional screw rod (74) being rotatably connected between opposite sides of the two horizontal plates (72).

5. An aircraft engine with a connection assembly according to claim 4, characterized in that: A motor (75) is fixed on the top of the upper horizontal plate (72), and the output end of the motor (75) is fixed to the top of the bidirectional screw rod (74) through a coupling. Two movable seats (76) are arranged on one side of the vertical plate (71), and one end of the bidirectional screw rod (74) passes through the two movable seats (76) and extends to the outside of the movable seat (76).

6. An aircraft engine with a connection assembly according to claim 5, characterized in that: The inner surfaces of the two movable seats (76) are both threadedly connected to the outer surface of the bidirectional screw rod (74); one side of the two movable seats (76) is provided with an insertion rod (77); one end of the two insertion rods (77) is fixed with an L-shaped rod (78); the opposite ends of the two L-shaped rods (78) are fixed with an arc plate (79); the opposite sides of the two arc plates (79) are fixed with cleaning bristles (710); the cleaning bristles (710) are in contact with the outer surface of the rotating shaft (2).

7. An aircraft engine with a connection assembly according to claim 6, characterized in that: A disassembly and replacement assembly (8) is provided between the two insertion rods (77) and the movable seat (76), and the disassembly and replacement assembly (8) includes a groove (81) provided on one side of the movable seat (76), one end of the insertion rod (77) extends to the inside of the groove (81), a transverse groove (82) is provided inside the movable seat (76), a slot (83) is provided on one side of the insertion rod (77), and a locking rod (84) is slidably connected to one side of the movable seat (76), and one end of the locking rod (84) passes through the movable seat (76) and the transverse groove (82) and extends to the inside of the slot (83).

8. An aircraft engine with a connection assembly according to claim 7, characterized in that: A slide plate (85) is fixed on the outer surface of the locking rod (84), and the outer surface of the slide plate (85) is slidably connected to the inner surface of the transverse groove (82). A second spring (86) is sleeved on the outer surface of the locking rod (84), and one end of the second spring (86) is fixed to one side of the slide plate (85), and the other end of the second spring (86) is fixed to the inner wall of the transverse groove (82). A second pull ring (87) is fixed to the other end of the locking rod (84).

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