An oil cooling device for a Y5B aircraft after replacing the piston engine with a turboprop engine

Abstract

The present invention relates to an oil cooling device for a Y5B aircraft after replacement of a turboprop engine. The device comprises a guard plate connected in a zigzag shape, an oil radiator fixedly arranged at the bottom end of the guard plate, an air guide plate fixedly arranged at the bottom end of the oil radiator and connected in a zigzag shape, a damper plate A arranged between the inner side surfaces of the guard plate, two damper plates B arranged between the inner side surfaces of the guard plate and located on both sides of the damper plate A, two reinforcing plates fixedly arranged on the outer side surfaces of the guard plate, a connecting piece A fixedly arranged on the plate surface of the damper plate A, a supporting frame A fixedly arranged on the plate surface of the damper plate A, a connecting piece B fixedly arranged on the plate surface of the damper plate B, a supporting frame B fixedly arranged on the plate surface of the damper plate B, a connecting rod located above the damper plates A and the damper plates B and rotatably connected to the supporting frame A and the supporting frame B respectively, a rocker arm fixedly connected to the connecting piece A, and a fixing frame A and a fixing frame B fixedly arranged on both sides of the guard plate.

Description

Technical Field

[0001] The invention relates to a lubricating oil heat dissipation device for a Y5B aircraft after a turboprop engine is replaced. Background Art

[0002] Before the Y5B aircraft was equipped with turboprop engines, the oil cooling system had no control over the airflow. Instead, an oil radiator was installed in the lower engine compartment, with its honeycomb holes aligned with the flight path. During flight, airflow from the rotating propellers directed toward the radiator, lowering the oil temperature. However, after the turboprop engines were installed, the characteristics of the engines necessitated the control of the airflow to the radiator. For example, the radiator damper had to be closed when starting the engine.

[0003] The oil cooling device is designed according to the characteristics of the turboprop engine. The honeycomb holes of the oil radiator are slanted downward (when viewed along the heading). The airflow brought by the rotation of the propeller is only a small part of the heat dissipation. Most of the heat is dissipated by the exhaust back pressure of the aircraft exhaust pipe, which draws the external air into the engine compartment through the oil cooling device and then discharges it out of the engine compartment through the exhaust back pressure device of the exhaust pipe. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a lubricating oil cooling device for a Y5B aircraft after it is equipped with a turboprop engine, which can effectively dissipate the heat of the engine lubricating oil and prevent the lubricating oil from overheating.

[0005] The present invention adopts the following technical solutions:

[0006] The present invention is located inside the engine hood and includes a guard plate connected in a circular shape, a lubricating oil radiator fixedly arranged at the bottom end of the guard plate, an air deflector fixedly arranged at the bottom end of the lubricating oil radiator and connected in a circular shape, a damper plate A arranged between the inner side surfaces of the guard plate, two damper plates B arranged between the inner side surfaces of the guard plate and located on both sides of the damper plate A, two reinforcing plates fixedly arranged on the outer side surfaces of the guard plate, a connecting piece A fixedly arranged on the surface of the damper plate A, a supporting frame A fixedly arranged on the surface of the damper plate A, a connecting piece B fixedly arranged on the surface of the damper plate B, a supporting frame B fixedly arranged on the surface of the damper plate B, and a damper plate located above the damper plates A and B. A connecting rod rotatably connected to the support frame A and the support frame B respectively, a rocker arm fixedly connected to the connecting member A at one end, a push-pull steel cable rotatably connected to the other end of the rocker arm, and a fixing frame A and a fixing frame B fixedly arranged on both sides of the guard plate; an engine frame and a mounting base are fixedly arranged on the inner side of the engine hood, a vent is arranged on the outer side of the engine hood, the air guide plate is fixedly arranged on the mounting base, the vent is communicated with the air guide plate connected in a circular shape, the connecting member A and the connecting member B both penetrate the guard plate, the connecting member B is rotatably connected to the reinforcement plate, the connecting member A penetrates the reinforcement plate, and the fixing frame A and the fixing frame B are both fixedly mounted on the engine frame.

[0007] A sealing strip is fixedly arranged between the air guide plate and the mounting base of the present invention.

[0008] The positive effects of the present invention are as follows:

[0009] 1. The vents, air guide plates, oil radiator, and guard plates of the present invention form a passageway to dissipate the oil in the oil radiator. The rocker arm can be controlled by pushing and pulling a steel cable, thereby rotating the connector A and the damper plate A. The linkage rod can link the damper plates A and B, rotating them together at a certain angle to control the air intake volume.

[0010] 2. The sealing strip of the present invention has a shock-absorbing effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a schematic diagram of the structure of the present invention;

[0012] Figure 2 Schematic diagram of the rocker arm structure of the present invention;

[0013] Figure 3 This is a schematic diagram of the engine hood structure of the present invention;

[0014] Figure 4 This is a schematic diagram of the vent structure of the present invention;

[0015] Figure 5 It is a top view of the structure of the present invention.

[0016] In the attached drawings: 1. Engine hood; 2. Guard plate; 3. Lubricating oil radiator; 4. Wind deflector; 5. Air damper plate A; 6. Air damper plate B; 7. Reinforcement plate; 8. Connector A; 9. Support frame A; 10. Connector B; 11. Support frame B; 12. Linkage rod; 13. Rocker arm; 14. Push-pull cable; 15. Fixing frame A; 16. Fixing frame B; 17. Engine mount; 18. Mounting base; 19. Vent; 20. Sealing strip. DETAILED DESCRIPTION

[0017] As attached Figure 1As shown in FIG. 5 , the present invention is located inside an engine hood 1 and includes a guard plate 2 connected in a circular shape, an oil radiator 3 fixedly arranged at the bottom end of the guard plate 2, an air deflector 4 fixedly arranged at the bottom end of the oil radiator 3 and connected in a circular shape, a damper plate A5 arranged between the inner side surfaces of the guard plate 2, two damper plates B6 arranged between the inner side surfaces of the guard plate 2 and located on both sides of the damper plate A5, two reinforcing plates 7 fixedly arranged on the outer side surfaces of the guard plate 2, a connecting piece A8 fixedly arranged on the surface of the damper plate A5, a supporting frame A9 fixedly arranged on the surface of the damper plate A5, a connecting piece B10 fixedly arranged on the surface of the damper plate B6, a supporting frame B11 fixedly arranged on the surface of the damper plate B6, and a support frame B12 located above the damper plates A5 and B6 and connected to the supporting frame A9 and the supporting frame B13 respectively. 1, a connecting rod 12 rotatably connected, a rocker arm 13 at one end fixedly connected to the connecting member A8, a push-pull steel cable 14 rotatably connected to the other end of the rocker arm 13, and a fixing frame A15 and a fixing frame B16 fixedly arranged on both sides of the guard plate 2; the shape surrounded by the guard plate 2 is a square, an engine frame 17 and a mounting base 18 are fixedly arranged on the inner side of the engine hood 1, a vent 19 is provided on the outer side of the engine hood 1, the air deflector 4 is fixedly arranged on the mounting base 18, and the vent 19 is communicated with the air deflector 4 connected in a circular shape, the connecting member A8 and the connecting member B10 both penetrate the guard plate 2, the connecting member B10 is rotatably connected to the reinforcing plate 7, the connecting member A8 penetrates the reinforcing plate 7, and the fixing frames A15 and B16 are both fixedly mounted on the engine frame 17. The vents 19, air deflector 4, oil radiator 3, and guard plate 2 form a passageway for dissipating the oil within the oil radiator 3. A push-pull cable 14 controls the rotation of the rocker arm 13, which in turn rotates the connector A8, driving the damper plate A5. The linkage rod 12 allows damper plates A5 and B6 to rotate together to a certain angle, thereby controlling the air intake. The oil radiator 3 is model 8000618.

[0018] A sealing strip 20 is fixedly provided between the air guide plate 4 and the mounting base 18 of the present invention. The sealing strip 20 has a shock-absorbing effect.

[0019] When in use, the rotation of the rocker arm 13 is controlled by pushing and pulling the steel cable 14, which in turn rotates the connecting member A8, driving the damper plate A5 to rotate. The connecting rod 12 can make the damper plate A5 and the damper plate B6 form a linkage and rotate together at a certain angle, thereby controlling the air intake.

[0020] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A lubricating oil cooling device for a Y5B aircraft after replacing a turboprop engine, located inside the engine cover (1), characterized in that: The invention comprises a guard plate (2) connected in a circular shape, a lubricating oil radiator (3) fixedly arranged at the bottom end of the guard plate (2), an air guide plate (4) fixedly arranged at the bottom end of the lubricating oil radiator (3) and connected in a circular shape, a damper plate A (5) arranged between the inner side surfaces of the guard plate (2), two damper plates B (6) arranged between the inner side surfaces of the guard plate (2) and located on both sides of the damper plate A (5), two reinforcing plates (7) fixedly arranged on the outer side surfaces of the guard plate (2), a connecting piece A (8) fixedly arranged on the plate surface of the damper plate A (5), and a support fixedly arranged on the plate surface of the damper plate A (5). Frame A (9), a connecting member B (10) fixedly arranged on the surface of the damper plate B (6), a supporting frame B (11) fixedly arranged on the surface of the damper plate B (6), a connecting rod (12) located above the damper plate A (5) and the damper plate B (6) and rotatably connected to the supporting frame A (9) and the supporting frame B (11), a rocker arm (13) fixedly connected at one end to the connecting member A (8), a push-pull steel cable (14) rotatably connected to the other end of the rocker arm (13), and a fixing frame A (15) and a fixing frame B (16) fixedly arranged on both sides of the guard plate (2); The shape formed by the guard plate (2) is a square; An engine frame (17) and a mounting base (18) are fixedly provided on the inner side of the engine hood (1); a vent (19) is provided on the outer side of the engine hood (1); the wind deflector (4) is fixedly provided on the mounting base (18); the vent (19) is communicated with the wind deflector (4) connected in a circular shape; a connecting member A (8) and a connecting member B (10) both pass through the guard plate (2); the connecting member B (10) is rotatably connected to the reinforcing plate (7); the connecting member A (8) passes through the reinforcing plate (7); and the fixing frame A (15) and the fixing frame B (16) are both fixedly installed on the engine frame (17).

2. The lubricating oil cooling device for a Y5B aircraft after replacing a turboprop engine according to claim 1, characterized in that: A sealing strip (20) is fixedly arranged between the air guide plate (4) and the mounting base (18).

Images