Auxiliary opening structure of aero-engine thrust reverser

Abstract

The utility model discloses an auxiliary opening structure of an aero-engine reverse thrust cover, which comprises an aero-engine body and an air inlet cover, the air inlet cover is arranged outside the aero-engine body, and a reverse thrust cover body is arranged outside the aero-engine body on one side of the air inlet cover. An exhaust hood is arranged at the position, on one side of the reverse thrust hood body, of the outer portion of the aero-engine body, two sets of movable baffle plates are symmetrically arranged on the side, away from the reverse thrust hood body, of the exhaust hood, an annular frame is installed in the reverse thrust hood body, and three sets of first motors are installed on the outer wall of the annular frame at equal intervals. According to the auxiliary opening structure for the reverse thrust cover of the aero-engine, convenient and fast rotary adjusting type opening is achieved, airflow is conveniently guided to form reverse thrust to decelerate an aircraft, reverse thrust is conveniently generated for the second time by folding the reverse moving baffle plates, and the adjusting and controlling convenience and the reverse thrust efficiency of the auxiliary opening structure for the reverse thrust cover of the aero-engine are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of auxiliary opening structures, in particular to an auxiliary opening structure of a reverse thrust cover of an aero-engine. Background Art

[0002] A thrust reverser is a device that changes the direction of engine thrust. It turns a part of the gas flow that expands behind the turbine or the air flow at the fan outlet at a certain angle and sprays it obliquely forward, generating thrust in the opposite direction of the aircraft's flight direction. This is used to shorten the aircraft's landing runway. The thrust reverser cowl is a movable guide device in the aircraft engine's thrust reverser system. Traditional thrust reversers can generally be divided into three types according to their structural form: grab type, deflector type and cascade type.

[0003] For example, an auxiliary opening device for a reverse thrust cowl of an aircraft engine disclosed in the authorization announcement number CN214397264U is configured to open the reverse thrust cowl during ground maintenance of the aircraft engine, and includes a force transmission mechanism for driving the reverse thrust cowl to move along the axis of the aircraft engine to open or close, a fixture having an interface detachably connected to a fixed part of the aircraft engine, a power component installed on the fixture and configured to provide power to the force transmission mechanism, a controller installed on the fixture, and a control component provided outside the fixture and electrically connected to the controller;

[0004] Although it realizes torque control through the characteristics of the controller and power components to replace the manual rotation to achieve automatic control, it can shorten the time required for opening the reverse thrust hood and realize the intelligent opening of the reverse thrust hood, which can simplify the operation difficulty, reduce the demand for operators and improve the operation safety, but it does not solve the problem of the convenient rotation and adjustment opening of the existing auxiliary opening structure when in use, which is not convenient for guiding the airflow to form reverse thrust to slow down the aircraft, and is not convenient for moving the deflector in the reverse direction to close for a second time to generate reverse thrust, which affects the convenience of adjustment and control of the auxiliary opening structure of the reverse thrust hood of the aircraft engine and the efficiency of reverse thrust. Utility Model Content

[0005] The purpose of the utility model is to provide an auxiliary opening structure of an aircraft engine reverse thrust cover, so as to solve the problem that the auxiliary opening structure proposed in the above-mentioned background technology is not convenient for convenient rotation and adjustment to open, is not convenient for guiding the airflow to form reverse thrust to slow down the aircraft, is not convenient for moving the deflector in the reverse direction to close and generate reverse thrust for a second time, which affects the convenience of adjustment and control of the auxiliary opening structure of the aircraft engine reverse thrust cover and the efficiency of reverse thrust.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an auxiliary opening structure of an aircraft engine reverse thrust cover, comprising an aircraft engine body and an air intake cover, an air intake cover is arranged outside the aircraft engine body, a reverse thrust cover body is arranged outside the aircraft engine body on one side of the air intake cover, an exhaust cover is arranged outside the aircraft engine body on one side of the reverse thrust cover body, two groups of movable baffles are symmetrically arranged on the side of the exhaust cover away from the reverse thrust cover body, an annular frame is installed inside the reverse thrust cover body, three groups of first motors with equal spacing are installed on the outer wall of the annular frame, threaded rods are movably installed on the outer wall of the annular frame on one side of the first motor, and the output ends of the first motors are connected to the threaded rods, movable arms are arranged on the outer wall of the annular frame on one side of the threaded rod, a support shaft is installed at one end of the movable arm close to the annular frame, and the movable arms are movably connected to the annular frame through the support shaft, and baffle doors are installed on the outer walls of the movable arms, and threaded sleeves are sleeved on the surfaces of the threaded rods, and the threaded rods are threadedly connected to the threaded sleeves.

[0007] Preferably, a support arm is provided on the outer wall of the threaded sleeve, a first connecting shaft is installed on one end of the support arm close to the threaded sleeve, and the support arm is movably connected to the threaded sleeve through the first connecting shaft.

[0008] Preferably, a second connecting shaft is installed on one end of the support arm away from the threaded sleeve, and the support arm is movably connected to the movable arm through the second connecting shaft.

[0009] Preferably, a first cylinder is symmetrically and movably installed on the outer wall of the exhaust hood, a telescopic rod is installed at the output end of the first cylinder, a movable shaft is installed at the end of the telescopic rod away from the first cylinder, and the telescopic rod is movably connected to the two sets of movable baffles through the movable shaft.

[0010] Preferably, a second cylinder is symmetrically installed on the outer wall of the exhaust hood on one side of the first cylinder, an adjusting rod is installed at the output end of the second cylinder, a linkage shaft is installed at the end of the adjusting rod away from the second cylinder, and the adjusting rod is movably connected to the movable baffle through the linkage shaft.

[0011] Preferably, a remote controller is provided on the outer wall of the reverse thrust cover body, and an output end of the remote controller is electrically connected to input ends of the first motor, the first cylinder and the second cylinder.

[0012] Compared with the prior art, the utility model has the following beneficial effects: the auxiliary opening structure not only realizes convenient rotation-adjustable opening, but also facilitates guiding the airflow to form reverse thrust to decelerate the aircraft, and facilitates the reverse movement of the baffle plate to close and generate reverse thrust for a second time, thereby improving the convenience of adjusting and controlling the auxiliary opening structure of the reverse thrust cover of the aircraft engine and the efficiency of reverse thrust;

[0013] (1) First, the threaded rod is driven to rotate by the first motor, and the threaded sleeve moves on the surface of the threaded rod. The threaded sleeve drives the support arm to move through the first connecting shaft, and the support arm drives the movable arm to rotate through the second connecting shaft. The movable arm rotates with the support shaft as the axis, and the movable arm drives the baffle door to rotate. The multiple groups of baffle doors are changed from a closed state to an open state. The multiple groups of baffle doors flip outward, which plays a role of directional guide for the airflow, so that the airflow is discharged forward along the baffle door, generating reverse thrust, so as to facilitate the deceleration of the aircraft, thereby realizing the convenient rotation adjustment opening of the auxiliary opening structure, facilitating the guidance of the airflow to form reverse thrust to decelerate the aircraft, and improving the convenience of adjustment and control of the auxiliary opening structure;

[0014] (2) The telescopic rod is driven by the first cylinder to move, the telescopic rod drives the movable shaft to move, the movable shaft drives the two sets of movable baffles to move, and the second cylinder drives the adjusting rod to move. The moving direction of the adjusting rod is opposite to that of the telescopic rod. The movable baffles are driven by the adjusting rod through the linkage shaft to move. Under the reverse movement of the telescopic rod and the adjusting rod, the two sets of movable baffles are flipped backward and closed together, so that the engine exhaust jet is deflected obliquely forward, thereby generating a secondary reverse thrust to slow down the aircraft and facilitate the landing of the aircraft. The convenient reverse movable opening of the auxiliary opening structure is realized, the baffles are closed to generate a secondary reverse thrust, and the reverse thrust efficiency of the auxiliary opening structure of the aircraft engine reverse thrust cover is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the three-dimensional structure of the utility model;

[0016] Figure 2 It is a schematic diagram of the three-dimensional structure of the second cylinder of the utility model;

[0017] Figure 3 This is a front view structural schematic diagram of the utility model;

[0018] Figure 4 This is a schematic diagram of the front cross-sectional structure of the thrust reverser cover body of the utility model;

[0019] Figure 5 It is a three-dimensional enlarged structural schematic diagram of the annular frame of the utility model.

[0020] In the figure: 1. aircraft engine body; 2. air intake hood; 3. reverse thrust hood body; 4. exhaust hood; 5. deflector door; 6. annular frame; 7. first motor; 8. threaded rod; 9. threaded sleeve; 10. support arm; 11. movable arm; 12. first connecting shaft; 13. support shaft; 14. second connecting shaft; 15. movable deflector; 16. first cylinder; 17. telescopic rod; 18. movable shaft; 19. second cylinder; 20. adjusting rod; 21. linkage shaft; 22. remote controller. DETAILED DESCRIPTION

[0021] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined purpose of the utility model, the specific implementation method, structure, characteristics and effects of the present invention are described in detail below in combination with the accompanying drawings and preferred embodiments.

[0022] See also Figure 1-5 The utility model provides an embodiment: an auxiliary opening structure of an aircraft engine reverse thrust cover, comprising an aircraft engine body 1 and an air intake cover 2, an air intake cover 2 is arranged outside the aircraft engine body 1, a reverse thrust cover body 3 is arranged outside the aircraft engine body 1 on one side of the air intake cover 2, an exhaust cover 4 is arranged outside the aircraft engine body 1 on one side of the reverse thrust cover body 3, two groups of movable baffles 15 are symmetrically arranged on one side of the exhaust cover 4 away from the reverse thrust cover body 3, an annular frame 6 is installed inside the reverse thrust cover body 3, and three groups of first motors 7 with equal spacing are installed on the outer wall of the annular frame 6, and the first motor 7 plays a role in power output;

[0023] A threaded rod 8 is movably mounted on the outer wall of the annular frame 6 on one side of the first motor 7, and the output end of the first motor 7 is connected to the threaded rod 8. A movable arm 11 is arranged on the outer wall of the annular frame 6 on one side of the threaded rod 8. A support shaft 13 is mounted on one end of the movable arm 11 close to the annular frame 6, and the movable arm 11 is movably connected to the annular frame 6 through the support shaft 13. A deflector door 5 is mounted on the outer wall of the movable arm 11. A threaded sleeve 9 is mounted on the surface of the threaded rod 8. The threaded rod 8 and the threaded sleeve 9 play the role of threaded support, and the threaded rod 8 is threadedly connected to the threaded sleeve 9;

[0024] A support arm 10 is provided on the outer wall of the threaded sleeve 9, and a first connecting shaft 12 is installed at one end of the support arm 10 close to the threaded sleeve 9, and the support arm 10 is movably connected to the threaded sleeve 9 through the first connecting shaft 12, and a second connecting shaft 14 is installed at one end of the support arm 10 away from the threaded sleeve 9, and the support arm 10 is movably connected to the movable arm 11 through the second connecting shaft 14;

[0025] When in use, an external power supply is connected. First, when the aircraft takes off, the deflector door 5 is normally closed on the surface of the reverse thrust cover body 3, and the movable deflector 15 is folded outside the exhaust cover 4. When the aircraft lands, the airflow enters the interior of the reverse thrust cover body 3 from the air intake cover 2. The first motor 7 is turned on by operating the remote controller 22, and the threaded rod 8 is driven by the first motor 7 to rotate. Under the threaded support of the threaded rod 8 and the threaded sleeve 9, the threaded sleeve 9 moves on the surface of the threaded rod 8, and the threaded sleeve 9 drives the support arm 10 to move through the first connecting shaft 12, and the support arm 10 is driven by the first connecting shaft 12 to move. The two connecting shafts 14 drive the movable arm 11 to rotate, and the movable arm 11 rotates with the support shaft 13 as the axis, and the movable arm 11 drives the baffle door 5 to rotate, and the multiple groups of baffle doors 5 are changed from a closed state to an open state, and the multiple groups of baffle doors 5 are turned outward, which plays a role of directional flow guidance for the airflow, so that the airflow is discharged forward along the baffle door 5, and a reverse thrust is generated to facilitate the deceleration of the aircraft, thereby realizing the convenient rotation adjustment opening of the auxiliary opening structure, facilitating the guidance of the airflow to form a reverse thrust to decelerate the aircraft, and improving the convenience of the adjustment and control of the auxiliary opening structure;

[0026] A first cylinder 16 is symmetrically and movably mounted on the outer wall of the exhaust hood 4, and a telescopic rod 17 is mounted on the output end of the first cylinder 16, and a movable shaft 18 is mounted on the end of the telescopic rod 17 away from the first cylinder 16, and the telescopic rod 17 is movably connected to the two sets of movable baffles 15 through the movable shaft 18. A second cylinder 19 is symmetrically mounted on the outer wall of the exhaust hood 4 on one side of the first cylinder 16, and an adjusting rod 20 is mounted on the output end of the second cylinder 19, and a linkage shaft 21 is mounted on the end of the adjusting rod 20 away from the second cylinder 19, and the adjusting rod 20 is movably connected to the movable baffle 15 through the linkage shaft 21. A remote controller 22 is arranged on the outer wall of the reverse thrust hood body 3, and the output end of the remote controller 22 is electrically connected to the input end of the first motor 7, the first cylinder 16, and the second cylinder 19;

[0027] When in use, when the airflow inside the reverse thrust hood body 3 is discharged through the exhaust hood 4, the first cylinder 16 and the second cylinder 19 are opened by operating the remote controller 22, the first cylinder 16 plays a role of power output, and the second cylinder 19 plays a role of power output, the first cylinder 16 drives the telescopic rod 17 to move, and the telescopic rod 17 drives the movable shaft 18 to move, under the cooperation of the movable shaft 18 and the two sets of movable baffles 15, the movable shaft 18 drives the two sets of movable baffles 15 to move, and the second cylinder 19 drives the adjusting rod 20 to move, and the adjusting rod 20 The moving direction is opposite to that of the telescopic rod 17. The movable baffle 15 is driven by the adjusting rod 20 through the linkage shaft 21 to move. Under the reverse movement of the telescopic rod 17 and the adjusting rod 20, the two groups of movable baffles 15 flip backwards and close together, so that the engine exhaust jet is deflected obliquely forward, thereby generating a secondary reverse thrust to slow down the aircraft and facilitate the landing of the aircraft. The convenient reverse movable opening of the auxiliary opening structure is realized, which facilitates the secondary generation of reverse thrust by closing the baffles, thereby improving the reverse thrust efficiency of the auxiliary opening structure of the aircraft engine reverse thrust cover.

[0028] Working principle: when in use, an external power supply is connected. First, when the aircraft takes off, the deflector door 5 is normally closed on the surface of the reverse thrust hood body 3, and the movable deflector 15 is folded outside the exhaust hood 4. When the aircraft lands, the airflow enters the interior of the reverse thrust hood body 3 from the air intake hood 2, and the threaded rod 8 is driven to rotate by the first motor 7. The threaded sleeve 9 moves on the surface of the threaded rod 8, and the threaded sleeve 9 drives the support arm 10 to move through the first connecting shaft 12, and the support arm 10 drives the movable arm 11 to rotate through the second connecting shaft 14. The movable arm 11 rotates with the support shaft 13 as the axis, and the deflector door 5 is driven by the movable arm 11 to rotate, and multiple groups of deflector doors 5 are changed from a closed state to an open state, and multiple groups of deflector doors 5 are flipped outward, which plays a role of directional guidance for the airflow, so that the airflow is discharged forward along the deflector door 5, generating reverse thrust, to facilitate use. The aircraft decelerates, and when the airflow inside the reverse thrust hood body 3 is discharged through the exhaust hood 4, the telescopic rod 17 is driven by the first cylinder 16 to move, and the telescopic rod 17 drives the movable shaft 18 to move. Under the active cooperation of the movable shaft 18 and the two groups of movable baffles 15, the two groups of movable baffles 15 are driven by the movable shaft 18 to move, and the second cylinder 19 drives the adjusting rod 20 to move. The moving direction of the adjusting rod 20 is opposite to that of the telescopic rod 17. The movable baffle 15 is driven by the adjusting rod 20 through the linkage shaft 21 to move. Under the reverse movement of the telescopic rod 17 and the adjusting rod 20, the two groups of movable baffles 15 are flipped backwards and closed together, so that the engine exhaust jet is deflected obliquely forward, thereby generating a secondary reverse thrust to decelerate the aircraft, facilitate the landing of the aircraft, and complete the use of the auxiliary opening structure.

[0029] The above description is only a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Although the present invention has been disclosed as a preferred embodiment as above, it is not intended to limit the present invention. Any technical personnel in this field can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any brief modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. An auxiliary opening structure of an aircraft engine reverse thrust cover, comprising an aircraft engine body (1) and an air intake cover (2), characterized in that: An air intake hood (2) is arranged outside the aircraft engine body (1); a reverse thrust hood body (3) is arranged outside the aircraft engine body (1) on one side of the air intake hood (2); an exhaust hood (4) is arranged outside the aircraft engine body (1) on one side of the reverse thrust hood body (3); two groups of movable baffles (15) are symmetrically arranged on a side of the exhaust hood (4) away from the reverse thrust hood body (3); an annular frame (6) is installed inside the reverse thrust hood body (3); three groups of first motors (7) are installed at equal intervals on the outer wall of the annular frame (6); and the annular frame (6) on one side of the first motor (7) is provided with a plurality of first motors (7) arranged at equal intervals. 6) A threaded rod (8) is movably mounted on the outer wall, and the output end of the first motor (7) is connected to the threaded rod (8), a movable arm (11) is arranged on the outer wall of the annular frame (6) on one side of the threaded rod (8), a support shaft (13) is mounted on the end of the movable arm (11) close to the annular frame (6), and the movable arm (11) is movably connected to the annular frame (6) through the support shaft (13), a deflector door (5) is mounted on the outer wall of the movable arm (11), a threaded sleeve (9) is sleeved on the surface of the threaded rod (8), and the threaded rod (8) is threadedly connected to the threaded sleeve (9).

2. The auxiliary opening structure of the reverse thrust cover of an aircraft engine according to claim 1, characterized in that: A support arm (10) is provided on the outer wall of the threaded sleeve (9), a first connecting shaft (12) is installed at one end of the support arm (10) close to the threaded sleeve (9), and the support arm (10) is movably connected to the threaded sleeve (9) via the first connecting shaft (12).

3. The auxiliary opening structure of the reverse thrust cover of an aircraft engine according to claim 2, characterized in that: A second connecting shaft (14) is installed at one end of the support arm (10) away from the threaded sleeve (9), and the support arm (10) is movably connected to the movable arm (11) via the second connecting shaft (14).

4. The auxiliary opening structure of the reverse thrust cover of an aircraft engine according to claim 1, characterized in that: A first cylinder (16) is symmetrically and movably mounted on the outer wall of the exhaust hood (4); a telescopic rod (17) is mounted on the output end of each of the first cylinders (16); a movable shaft (18) is mounted on one end of each of the telescopic rods (17) away from the first cylinder (16); and the telescopic rods (17) are movably connected to the two sets of movable baffles (15) via the movable shaft (18).

5. The auxiliary opening structure of the reverse thrust cover of an aircraft engine according to claim 4, characterized in that: A second cylinder (19) is symmetrically mounted on the outer wall of the exhaust hood (4) on one side of the first cylinder (16); an adjusting rod (20) is mounted on the output end of each of the second cylinders (19); a linkage shaft (21) is mounted on the end of each of the adjusting rods (20) away from the second cylinder (19); and the adjusting rods (20) are movably connected to the movable baffle (15) via the linkage shaft (21).

6. The auxiliary opening structure of the reverse thrust cover of an aircraft engine according to claim 1, characterized in that: A remote controller (22) is provided on the outer wall of the reverse thrust cover body (3), and an output end of the remote controller (22) is electrically connected to input ends of the first motor (7), the first cylinder (16), and the second cylinder (19).

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