JPS6348746B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a cooling device for a hovercraft engine.

(Prior art) As a vehicle that can navigate both on water and on land, there is something called a hovercraft, as shown in the revised 5th edition of the Mechanical Engineering Handbook (edited by the Japan Society of Mechanical Engineers, 1968). The aircraft travels while floating above the water or ground by supplying pressurized air between it and the water or ground. The body of such a hovercraft is generally equipped with a levitation engine for obtaining the pressurized air and a propulsion engine for rotating a propeller to obtain propulsive force.

However, in such a hovercraft, there are many cases where sufficient cooling of the engine cannot be obtained depending on the position where the engine is mounted on the tower, and some kind of countermeasure is desired.

(Object of the Invention) The present invention was made in consideration of the above-mentioned circumstances, and an object of the present invention is to provide a hovercraft engine cooling device that can sufficiently cool the engine mounted on the aircraft body. do.

(Structure of the Invention) In order to achieve the above-mentioned object, in the present invention, pressurized air is supplied between the bottom surface of the aircraft body and the water surface or the ground, so that the aircraft body is raised above the water surface or the ground, In a hovercraft that travels by propulsion force based on a propulsion propeller, a case is provided on the aircraft body, a radiator for an engine mounted on the aircraft body is disposed within the case, and the case includes the With the radiator in between,
First and second inlets and an outlet are formed, the first inlet is open to the atmosphere, and the second inlet is provided with a cooling duct that guides a portion of the pressurized air. The cooling device for an engine for a hovercraft is characterized in that: the outflow port is set to face a suction airflow area of the propulsion propeller. (Example) In FIGS. 1 and 2, 1 is a fuselage, and a levitation engine 2 is mounted on the lower front of the cabin 1a, and a propulsion engine 3 is mounted on the rear of the cabin 1a. has been done.

On the bottom surface of the fuselage 1, over its entire periphery,
An annular tube 4 made of a flexible material such as rubber is arranged. This annular tube 4 has a number of outlet ports 4a that open downwardly formed therein at predetermined intervals over its entire circumference, and also opens upwardly in a portion corresponding to the front part of the fuselage 1. A pair of left and right inflow ports 4b are formed. A duct 5 is connected to each of these two inlets 4b, and a fan 6 for generating pressurized air is disposed inside each duct 5. This fan 6 is rotationally driven by the flotation engine 2 via a belt 7, and the pressurized air generated by the rotation of the fan 6 enters the annular tube 4 from the inlet 4b. and is discharged from the outlet 4a. The pressurized air discharged from the outlet 4a confines the pressurized air between the bottom of the aircraft 1 and the running surface 8 (water surface or the ground), and the aircraft 1 moves towards the running surface 8. float more.

On the other hand, behind the propulsion engine 3, that is, on the rear end of the fuselage 1, there are provided a pair of left and right cylindrical ducts 9 extending in the front and rear directions, and each duct 9 has a propulsion propeller. 10 is disposed, and a rudder 11 is disposed behind the propulsion propeller 10. The duct 9 is provided to improve thrust by preventing turbulence from occurring in the air blown by the propulsion propeller 10. The propulsion propeller 10 is rotatably driven by the propulsion engine 3 via a belt 12, and thrust is generated by the rotation of the propulsion propeller 10, and the aircraft 1 floated as described above. The traveling direction is changed by changing the angle of the rudder 11 by operating from inside the cabin 1a.

The propulsion engine 3 is arranged in an engine room 14 defined by a case 13. The case 13 has an air inlet 13a as a first inlet and an air inlet 13b as a second inlet opened vertically in the front wall portion of the case 13. is duct 9
An air outlet 13c as an outlet is opened so as to be directed toward the front opening of the air outlet 13c.
faces the suction airflow area of the propulsion propeller 10. And engine room 1
4 has two upper and lower air inlets 13a and 13b.
A radiator 15 and an oil cooler 16 of the propulsion engine 3 are arranged facing the engine.

Of the two inflow ports 13a and 13b, the air inflow port 13a located above is open to the atmosphere, while the air inflow port 13b located below is The annular tube 4 is connected to the annular tube 4. That is, one end of each cooling duct 17 is connected to the air inlet 13b, and the other end is connected to the annular tube 4 at an intermediate portion of the body 1 in the longitudinal direction.

In addition, 18 in the figure is a radiator of the levitation engine 2, and the radiator 18 is arranged facing the inlet side of the duct 5 so that it can be sufficiently cooled by a large amount of air flowing through the rotation of the fan 6. It's summery. Further, 19 is a propulsion engine cooling fan.

In the above configuration, the levitation engine 2
The pressurized air generated by the power source is used for levitation of the aircraft 1 as described above, and a part of the pressurized air is also supplied to the radiator of the propulsion engine 3 via the cooling duct 17. 15 and oil cooler 1
6 to cool it. The pressurized air that has cooled the radiator 15 and oil cooler 16 sweeps through the engine room 14 and flows toward the propulsion propeller 10. In addition, outside air flows in from the air inlet 13a as cooling air under the influence of the pressurized air flow and the suction action of the propulsion propeller 10 and the fan 19, and this outside air is used together with the pressurized air. The radiator 15 and oil cooler 16 are cooled. Therefore, the cooling performance can be significantly improved, and based on the specified cooling performance,
Based on the cooling capacity of outside air, the amount of pressurized air used for cooling can be significantly reduced.

In the embodiment, since the pressurized air flows toward the propulsion propeller 10 as described above, the power required for suction of the cooling air by the propulsion propeller 10 is slightly reduced.

Although the embodiments have been described above, the present invention is not limited thereto, and includes, for example, the following cases.

The pressurized air may be used to cool not only the propulsion engine but also the levitation engine.

The present invention can be similarly applied to an engine in which a single engine is used for both levitation and propulsion without separately providing a levitation engine and a propulsion engine.

For engines that do not have an oil cooler, a portion of the pressurized air may be guided only to the radiator.

The cooling duct 17 can be connected to an appropriate position of the annular tube 4 depending on the tower mounting position of the engine.

(Effects of the Invention) As is clear from the above, the present invention has the following advantages:
The engine (radiator) can be actively cooled using a portion of the pressurized air and outside air, allowing the engine to fully demonstrate its performance without overheating.

In addition, cooling can be performed not only with pressurized air but also with outside air, and by adding active cooling with this outside air, cooling performance can be significantly improved, and the specified cooling Based on performance, the amount of pressurized air used for cooling can be significantly reduced.

[Brief explanation of drawings]

FIG. 1 is a plan view showing one embodiment of the present invention, and FIG.
The figure is a partially sectional side view showing an embodiment of the present invention. 1... fuselage, 2, 3... engine, 8... running surface, 15... radiator, 17... cooling duct.

Claims (1)

[Claims] 1. A hovercraft that supplies pressurized air between the bottom of the aircraft and the water surface or the ground to raise the aircraft above the water or the ground, and that travels by propulsion based on a propulsion propeller. A case is provided on the aircraft body, a radiator for an engine mounted on the aircraft body is disposed within the case, and a radiator is disposed in the case with the radiator sandwiched therebetween;
First and second inlets and an outlet are formed, the first inlet is open to the atmosphere, and the second inlet is provided with a cooling duct that guides a portion of the pressurized air. A cooling device for an engine for a hovercraft, characterized in that: the outlet port is connected to a cooling device for an engine for a hovercraft, and the outlet port is set to face a suction air flow area of the propulsion propeller.