Vibration and noise reduction equipment for aircraft exhaust port

Abstract

The invention relates to the technical field of aircraft shock absorption and noise reduction, and discloses a shock absorption and noise reduction device for an aircraft exhaust port, and the shock absorption and noise reduction device for the aircraft exhaust port comprises an isolation cover which can be installed on an aircraft; the exhaust pipeline is arranged in the isolation hood and comprises a connecting section connected with an aircraft exhaust port and an outlet section capable of communicating with the connecting section; the deformation connecting part is provided with a first communicating end and a second communicating end which are respectively connected with the connecting section and the outlet section, and a reducing section arranged between the first communicating end and the second communicating end; and the opening binding part comprises an extrusion piece which is in contact with the reducing section. By arranging the deformation connecting part, the connecting section can be accelerated in the process of reaching the outlet section through the deformation connecting part, and the flow velocity difference between airflow outside the aircraft and airflow exhausted from the exhaust port is reduced, so that the problems of vibration and noise caused by a turbine generated by the fact that high-speed airflow is involved into the aircraft exhaust port due to the too large flow velocity difference are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft vibration reduction and noise reduction, in particular to a vibration reduction and noise reduction device for an aircraft exhaust port. Background Art

[0002] The aircraft exhaust vent is the outlet on the fuselage for exhausting air. The aircraft cabin pressure regulation system adjusts the exhaust volume of the pressurized cabin by controlling the opening of the exhaust vent, thereby maintaining the pressure in the cabin at a safe and comfortable level.

[0003] When an aircraft is in flight, due to its high flight speed, the air flow through the exhaust port will be very fast, but the air discharged from the exhaust port will flow slowly. The difference in flow rate between the exhaust port and the external air flow is too large, causing the high-speed air flow to enter the internal area covered by the fuselage through the exhaust port, and because of the large difference in flow rate, turbines are generated, causing vibration and noise problems in the surrounding structures. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is that the speed difference between the airflow discharged from the outlet and the external airflow is too large.

[0005] The above technical problem is solved by the following technical solution: The present invention provides a vibration and noise reduction device for an aircraft exhaust port, which includes an isolation cover that can be installed on the aircraft; an exhaust duct disposed in the isolation cover, comprising a connecting section connected to the aircraft exhaust port, and an outlet section capable of communicating with the connecting section; a deformable connecting portion having a first communicating end and a second communicating end connected to the connecting section and the outlet section respectively, and a reduced diameter section provided between the first communicating end and the second communicating end; The constriction portion includes an extrusion member in contact with the diameter-reducing section, and a pushing member abutting against the extrusion member; When the pushing member pushes the extruding member to move relative to the diameter-reducing section, the extruding member can reduce the diameter of the diameter-reducing section according to the compression diameter section.

[0006] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port of the present invention: the pushing member includes a rotating body and a force-applying body mounted on the rotating body; The extrusion piece is provided with a force-bearing body which resists the force-applying body.

[0007] In a preferred embodiment of the vibration reduction and noise reduction device for an aircraft exhaust port according to the present invention, it also includes a fixing portion installed on the isolation cover, which includes a mounting piece, the extrusion piece is installed on the fixing portion through the mounting piece, and the rotating body is rotatably installed on the fixing portion.

[0008] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port of the present invention: an opening is formed on the isolation cover; The vibration and noise reduction device for an aircraft exhaust port further includes a moving portion, which includes an action body movably mounted on the opening, and a pulling belt connecting the action body and the rotating body.

[0009] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port of the present invention: the rotating bodies are symmetrically arranged on both sides of the fixed portion, and a connecting column is provided between the two symmetrically arranged rotating bodies; A concentric groove is provided on the fixing portion, and the connecting column passes through the concentric groove.

[0010] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port according to the present invention: the mounting member includes a sliding column fixed on an extrusion member, a protrusion provided on the sliding column, and a first elastic member provided on the outside of the sliding column; when the extrusion member moves toward the reduced diameter section, the protrusion presses the first elastic member.

[0011] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port according to the present invention: the force-applying body has a contact surface in contact with the force-receiving body, one end of the contact surface extends away from the center of the rotating body, and the other end of the contact surface extends toward the center of the rotating body.

[0012] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port of the present invention, the number of the extruded parts is at least two, and the extruded parts are distributed circumferentially with the reduced diameter section as the axis.

[0013] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port of the present invention, it further comprises a connecting ring installed on the isolation cover, and the connecting section and the outlet section are both installed inside the isolation cover through the connecting ring.

[0014] In a preferred embodiment of the vibration and noise reduction device for an aircraft exhaust port of the present invention: a skirt is provided on the outlet section; A fixed column is installed on the connecting ring, and the outer portion of the fixed column is sleeved with the second elastic member; The fixed column passes through the skirt board, and the second elastic member abuts against the skirt board.

[0015] The beneficial effect of the present invention is that by providing a deformable connection portion, the connection section can be accelerated in the process of reaching the outlet section through the deformable connection portion, thereby reducing the flow velocity difference between the airflow outside the aircraft and the airflow discharged from the exhaust port, thereby reducing the problem of high-speed airflow being drawn into the aircraft exhaust port due to excessive flow velocity difference, generating turbine vibration and noise. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings of the embodiments of the present invention. Obviously, the drawings described below only relate to some embodiments of the present invention and are not intended to limit the present invention. Among them: Figure 1 Shows a schematic diagram of the overall structure of the present invention; Figure 2 A schematic structural diagram of the constriction portion and the deformable connection portion is shown; Figure 3 shows a cross-sectional view of a deformable connection; Figure 4 Shows a schematic structural diagram of the pushing member and the extruding member; Figure 5 Shows a schematic diagram of the structure of the fixed part and the rotating body; Figure 6 Shown Figure 5 Enlarged view of point A in the middle; Figure 7 shows a schematic structural diagram of the moving part; Figure 8 shows a specific structural diagram of the force-applying body; Figure 9 shows a schematic structural diagram of the connecting ring; Figure 10 Shown Figure 9 Enlarged view of point B in the middle.

[0017] 1. Isolation cover; 11. Opening; 2. Exhaust duct; 21. Connecting section; 22. Outlet section; 221. Skirt; 3. Deformable connecting part; 31. First connecting end; 32. Second connecting end; 33. Reduced diameter section; 4. Bound mouth; 41. Extrusion piece; 411. Force-bearing body; 42. Pushing piece; 421. Rotating body; 422. Force-applying body; 423. Connecting column; 424. Contact surface; 425. Far end; 426. Near end; 5. Fixed part; 51. Mounting part; 511. Sliding column; 512. Protruding body; 513. First elastic part; 52. Concentric groove; 6. Moving part; 61. Actuating body; 611. Strong pressure side; 612. Weak pressure side; 62. Pull belt; 7. Connecting ring; 71. Fixed column; 72. Second elastic part. DETAILED DESCRIPTION

[0018] In order to enable those skilled in the art to better understand the present invention, the present invention is further described in detail below with reference to specific embodiments and the accompanying drawings.

[0019] The terms used in the present invention are those commonly used in the art in view of the functions of the present invention, but these terms may vary according to the intentions of those skilled in the art, precedents, or new technologies in the art. In addition, specific terms may be selected by the applicant, and in such cases, their detailed meanings will be described in the detailed description of the present invention. Therefore, the terms used in the specification should not be understood as simple names, but rather as the meanings of the terms and the overall description of the present invention.

[0020] Reference Figure 1 This embodiment provides a vibration and noise reduction device for an aircraft exhaust port, including an isolation cover 1, which can be installed on an aircraft; the isolation cover 1 is installed on the outer wall of the aircraft fuselage, specifically at the aircraft exhaust port.

[0021] This vibration and noise reduction device includes an exhaust duct 2, which is arranged in an isolation cover 1, including a connecting section 21 connected to the aircraft exhaust port, and an outlet section 22 that can be communicated with the connecting section 21; the gas can directly enter the interior of the connecting section 21 from the aircraft's exhaust port and finally be discharged through the outlet section 22.

[0022] refer to Figure 1 and Figure 2 This vibration and noise reduction device includes a deformable connection part 3, which has a first connecting end 31 and a second connecting end 32 connected to the connecting section 21 and the outlet section 22 respectively, and a reduced diameter section 33 arranged between the first connecting end 31 and the second connecting end 32; the deformable connection part 3 can connect the connecting section 21 and the outlet section 22, so that the gas can eventually be discharged through the outlet section 22.

[0023] This vibration and noise reduction device includes a constriction portion 4, including an extrusion member 41 in contact with the diameter-reducing section 33, and a pushing member 42 abutting against the extrusion member 41; when the pushing member 42 pushes the extrusion member 41 to move relative to the diameter-reducing section 33, the extrusion member 41 can reduce the diameter of the diameter-reducing section 33 according to the compression section 33.

[0024] refer to Figure 3 The reduced diameter section 33 is located between the first connecting end 31 and the second connecting end 32. The diameter of the reduced diameter section 33 is reduced by the bundle mouth portion 4 so that the diameter of the reduced diameter section 33 is smaller than the diameters of the first connecting end 31 and the second connecting end 32, so that the deformable connection portion 3 constitutes a wide-narrow-wide channel, forming a Laval nozzle structure, so that the gas discharged from the aircraft exhaust port can be accelerated in the process of passing through the deformable connection portion 3 from the connecting section 21 to the outlet section 22, reducing the flow rate difference between the airflow outside the aircraft and the airflow discharged from the exhaust port, thereby reducing the problem of high-speed airflow being drawn into the aircraft exhaust port due to excessive flow rate difference, generating turbine vibration and noise.

[0025] When an aircraft flies at different speeds, the airflow speeds generated are different. The pushing member 42 can reduce the diameter of the reduced diameter section 33, and the compression ratio (inlet area / throat area) of the contraction section of the Laval nozzle structure formed by the reduced diameter section 33 can be changed. In this embodiment, it is the area ratio of the first connecting end 31 and the reduced diameter section 33. At the same time, the semi-cone angle of the expansion section is adjusted. In this embodiment, it is the semi-cone angle of the second connecting end 32, thereby controlling the acceleration effect of the gas discharged from the exhaust port.

[0026] In this embodiment, both the first communication end 31 and the second communication end 32 are preferably in a bell-mouth shape.

[0027] It should be noted that in order to prevent the airflow from reaching the speed of sound in advance before the diameter reduction section 33, resulting in congestion, the compression ratio of the contraction section is controlled between 3:1 and 5:1. At the same time, in order to avoid the problem of oblique shock waves caused by the excessive semi-cone angle of the second connecting end 32, the semi-cone angle of the second connecting end 32 is preferably controlled between 10° and 15°.

[0028] In order to enhance the effect of reducing the diameter of the diameter-reducing section 33 when the diameter-reducing section 33 is pressed, the diameter-reducing section 33 is preferably made of an elastic material, such as silicone rubber, polyurethane, etc. In addition, the number of the extrusion pieces 41 is at least two, and the extrusion pieces 41 are distributed around the diameter-reducing section 33 as the axis. In this embodiment, Figure 4 The number of extrusion members 41 is 4, and the extension lines of the moving directions of the extrusion members 41 all pass through the center position of the diameter-reducing section 33, thereby improving the effect of the extrusion members 41 reducing the diameter according to the compression diameter section 33.

[0029] As an optional embodiment, Figure 4 The pushing member 42 includes a rotating body 421 and a force-applying body 422 installed on the rotating body 421; the extrusion member 41 is provided with a force-bearing body 411 that counteracts the force-applying body 422. In this embodiment, the rotating body 421 is a circular ring structure, and the force-applying body 422 is fixed on the inner ring wall of the rotating body 421. When the rotating body 421 rotates, it can drive the force-applying body 422 to rotate synchronously. Through the rotation of the force-applying body 422, the force-bearing body 411 can be pressed to move the extrusion member 41. When the four extrusion members 41 move toward the diameter-reducing section 33, the diameter of the diameter-reducing section 33 can be reduced, the compression ratio of the contraction section of the Laval nozzle formed by the deformation connection part 3 can be improved, and the flow rate of the airflow discharged from the exhaust port can be changed. When the aircraft flies at different speeds, this device can adapt to different external airflow velocities.

[0030] As an optional embodiment, Figure 5 and Figure 6The vibration reduction and noise reduction device also includes a fixed part 5 installed on the isolation cover 1, which includes a mounting part 51. The extrusion part 41 is installed on the fixed part 5 through the mounting part 51, and the rotating body 421 can be rotatably installed on the fixed part 5. In this embodiment, one end of the fixed part 5 is fixed on the isolation cover 1, and the fixed part 5 is also an annular structure. The extrusion part 41 can slide on the fixed part 5. The rotating body 421 is an annular structure, which is concentric with the fixed part 5. The fixed part 5 cannot rotate, and the extrusion part 41 installed on the fixed part 5 cannot rotate. When the rotating body 421 rotates, it can push the extrusion part 41, and the extrusion part 41 will not rotate.

[0031] In another embodiment, Figure 7 , an opening 11 is provided on the isolation cover 1; the vibration and noise reduction device for the exhaust port of an aircraft also includes a moving part 6, which includes an action body 61 installed in the opening 11 and capable of movement, and a pulling belt 62 connecting the action body 61 and the rotating body 421, one end of the pulling belt 62 is connected to the action body 61, and the other end is connected to the side of the rotating body 421 away from the action body 61. The purpose of setting the moving part 6 is to automatically enhance the acceleration effect of the gas discharged from the exhaust port when the aircraft accelerates and the relative flow rate of the external airflow increases. One side of the moving part 6 extends to the outside of the isolation cover 1 through the opening 11 and contacts the external airflow. When the external high-speed airflow flows through the action body 61 in the moving part 6, due to the Bernoulli principle, the action body 61 generates a weak pressure side 612 on the outside of the isolation cover 1 and a high pressure side 611 on the inside of the isolation cover 1, so that the action body 61 is subjected to a thrust toward the outside of the isolation cover 1, so the action body 61 moves toward the outside of the isolation cover 1, and can pull the rotating body 421 to rotate through the pulling belt 62. Through the rotation of the rotating body 421, the force-applying body 422 is driven to rotate to squeeze the extrusion piece 41, so that the extrusion piece 41 presses the compression diameter section 33, reduces the diameter of the reduction section 33, and improves the contraction section compression ratio of the Laval nozzle structure formed by the reduction section 33, so that the air flow speed acceleration effect flowing through the reduction section 33 is improved. When the aircraft speed increases, the thrust of the strong pressure side 611 received by the action body 61 is also increased, thereby increasing the force of the pulling belt 62 to pull the rotating body 421, the rotation angle of the rotating body 421 increases, and the displacement caused by the force-applying body 422 pushing the extrusion piece 41 increases. The smaller the diameter of the reduction section 33, the diameter of the reduction section 33 can be adaptively adjusted according to the flight speed of the aircraft.

[0032] As an optional embodiment, Figure 5 and Figure 6The rotating bodies 421 are symmetrically arranged on both sides of the fixed part 5, and a connecting column 423 is arranged between the two symmetrically arranged rotating bodies 421; a concentric groove 52 is opened on the fixed part 5, and the connecting column 423 passes through the concentric groove 52. The concentric groove 52 is arc-shaped, and the concentric groove 52 and the fixed part 5 are concentrically related, and are also concentrically related to the rotating body 421. In this embodiment, the number of concentric grooves 52 is four, and the number of connecting columns 423 is also four. The column diameter of the connecting column 423 is adapted to the groove width of the concentric groove 52. When the four connecting columns 423 pass through the four concentric grooves 52 at the same time, the rotating bodies 421 at both ends of the connecting column 423 are rotatably installed on the fixed part 5. Therefore, when the pulling belt 62 pulls the rotating body 421, the rotating body 421 can rotate.

[0033] As an optional embodiment, Figure 6 The mounting member 51 includes a slide post 511 fixed to the extrusion member 41, a protrusion 512 provided on the slide post 511, and a first elastic member 513 provided on the outside of the slide post 511. When the extrusion member 41 moves toward the diameter-reducing section 33, the protrusion 512 presses the first elastic member 513. A hole for the slide post 511 to pass through is provided on the fixing portion 5, and the width of the protrusion 512 is greater than the diameter of the hole. When the extrusion member 41 moves toward the diameter-reducing section 33, it can drive the slide post 511 to move toward the diameter-reducing section 33. At this time, the protrusion 512 presses the first elastic member 513, causing the first elastic member 513 to deform. After the pulling force of the pulling belt 62 received by the rotating body 421 disappears, the elastic force of the first elastic member 513 pushes the protrusion 512, causing the sliding column 511 and the extrusion member 41 to move and reset in the direction away from the reduced diameter section 33. In addition, the existence of the first elastic member 513 also constrains the movement of the extrusion member 41. When the pulling belt 62 pulls the rotating body 421, causing the force-applying body 422 to press the extrusion member 41 to move, the first elastic member 513 is compressed. Only when the pressure applied by the pulling belt 62 to the rotating body 421 increases, will it further drive the rotating body 421 to rotate, causing the extrusion member 41 to move. Among them, the first elastic member 513 is a spring.

[0034] As an optional embodiment, Figure 8The force-applying body 422 has a contact surface 424 that contacts the force-bearing body 411. One end of the contact surface 424 is a distal end 425 extending in a direction away from the center of the rotating body 421. The other end of the contact surface 424 is a proximal end 426 extending in a direction close to the center of the rotating body 421. In the initial rotation state, the force-bearing body 411 of the extrusion member 41 and the distal end 425 of the contact surface 424 are in corresponding positions. When the rotating body 421 rotates clockwise, the contact surface 424 can apply force to the force-bearing body 411. The thrust toward the center of the diameter-reducing section 33 causes the extrusion member 41 to move toward the center of the diameter-reducing section 33. Therefore, when the pulling belt 62 pulls the rotating body 421 to rotate clockwise, it can push the extrusion member 41 to move. When the pulling force of the pulling belt 62 disappears, the extrusion member 41 moves away from the diameter-reducing section 33 under the action of the first elastic member 513. At this time, the force-bearing body 411 can transmit the force to the rotating body 421 through the contact surface 424, so that the rotating body 421 rotates counterclockwise to reset.

[0035] In another embodiment, Figure 9 The vibration reduction and noise reduction device also includes a connecting ring 7 installed on the isolation cover 1. The connecting section 21 and the outlet section 22 are both installed inside the isolation cover 1 through the connecting ring 7. The connecting ring 7 is fixed inside the isolation cover 1. The connecting section 21 and the outlet section 22 can both be installed on the connecting ring 7, thereby achieving the effect of installing the connecting section 21 and the outlet section 22 inside the isolation cover 1.

[0036] In another embodiment, Figure 10 The second elastic member 72 is deformed so that the pressure of the reducing section 33 is partially transmitted to the outlet section 22 when the pressure of the extruding member 41 is applied.

[0037] Finally, it should be pointed out that the methods and devices described in detail above are merely embodiments, and those skilled in the art can modify these embodiments in different ways without departing from the scope of the present invention.

Claims

1. A vibration and noise reduction device for an aircraft exhaust port, characterized in that: include, An isolation cover (1) capable of being installed on an aircraft; An exhaust duct (2) is arranged in the isolation cover (1), comprising a connecting section (21) connected to the aircraft exhaust port, and an outlet section (22) capable of communicating with the connecting section (21); A deformable connecting portion (3), comprising a first connecting end (31) and a second connecting end (32) respectively connected to the connecting section (21) and the outlet section (22), and a reduced diameter section (33) provided between the first connecting end (31) and the second connecting end (32); The constriction portion (4) comprises an extrusion member (41) in contact with the diameter-reducing section (33), and a pushing member (42) abutting against the extrusion member (41); When the pushing member (42) pushes the extruding member (41) to move relative to the diameter-reducing section (33), the extruding member (41) can reduce the diameter of the diameter-reducing section (33) according to the compression diameter section (33).

2. The vibration and noise reduction device for an aircraft exhaust port according to claim 1, characterized in that: The pushing member (42) comprises a rotating body (421) and a force-applying body (422) mounted on the rotating body (421); The extrusion piece (41) is provided with a force-bearing body (411) that abuts against the force-applying body (422).

3. The vibration and noise reduction device for an aircraft exhaust port according to claim 2, characterized in that: It also includes a fixing part (5) mounted on the isolation cover (1), which includes a mounting member (51), the extrusion member (41) being mounted on the fixing part (5) via the mounting member (51), and the rotating body (421) being rotatably mounted on the fixing part (5).

4. The vibration and noise reduction device for an aircraft exhaust port according to any one of claims 2 or 3, characterized in that: The isolation cover (1) is provided with an opening (11); The vibration and noise reduction device for an aircraft exhaust port further comprises a moving part (6), wherein the moving part (6) comprises a movable body (61) mounted on the opening (11) and capable of moving, and a pulling belt (62) connecting the movable body (61) and a rotating body (421).

5. The vibration and noise reduction device for an aircraft exhaust port according to claim 4, characterized in that: The rotating bodies (421) are symmetrically arranged on both sides of the fixed portion (5), and a connecting column (423) is arranged between the two symmetrically arranged rotating bodies (421); The fixing portion (5) is provided with a concentric groove (52), and the connecting column (423) passes through the concentric groove (52).

6. The vibration and noise reduction device for an aircraft exhaust port according to claim 3, characterized in that: The mounting member (51) comprises a sliding column (511) fixed on the extrusion member (41), a protrusion (512) provided on the sliding column (511), and a first elastic member (513) provided outside the sliding column (511); when the extrusion member (41) moves in the direction of the reduced diameter section (33), the protrusion (512) presses the first elastic member (513).

7. The vibration and noise reduction device for an aircraft exhaust port according to any one of claims 2, 5 or 6, characterized in that: The force-applying body (422) has a contact surface (424) in contact with the force-receiving body (411), one end of the contact surface (424) extends in a direction away from the center of the rotating body (421), and the other end of the contact surface (424) extends in a direction close to the center of the rotating body (421).

8. The vibration and noise reduction device for an aircraft exhaust port according to claim 7, characterized in that: The number of the extrusion pieces (41) is at least two, and the extrusion pieces (41) are distributed around the circumference with the reduced diameter section (33) as the axis.

9. The vibration and noise reduction device for an aircraft exhaust port according to claim 8, characterized in that: It also includes a connecting ring (7) mounted on the isolation cover (1), and the connecting section (21) and the outlet section (22) are both mounted inside the isolation cover (1) via the connecting ring (7).

10. The vibration and noise reduction device for an aircraft exhaust port according to claim 9, characterized in that: The outlet section (22) is provided with a skirt plate (221); A fixed column (71) is mounted on the connecting ring (7), and the exterior of the fixed column (71) is sleeved with a second elastic member (72); The fixed column (71) passes through the skirt plate (221), and the second elastic member (72) abuts against the skirt plate (221).

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