JPH0820396A - Helicopter - Google Patents

Abstract

PURPOSE:To dispense with the power for operating a cooling medium and make a helicopter lightweight at a low cost by using the surface of an airframe at the portion hit by much downwash as a cooling surface, and providing a cooling device having a passage for feeding a cooled medium cooled by the cooling surface inside the cooling surface. CONSTITUTION:This cooling device 10 fitted on a helicopter is formed into a double wall structure provided with an inner wall 5 inside a cooling surface 4 concurrently serving as the outer shell of a fuselage 2, and the double walls are partitioned by bulkheads to form a passage 7. A lubricant L serving as a cooled medium is guided from an inlet 8 and flows in the passage 7, and it flows outside the cooling surface 4. The lubricant L is cooled by downwash D or the air synthesized with the downwash D and a uniform stream and serving as a cooling medium. The cooled lubricant L is fed to a jet nozzle 14 in a gearbox 11 from an outlet 9 to lubricate gears and bearings.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention uses a downwash of a main rotor or a flow around an airframe during flight as a cooling medium of a cooling device for cooling gearbox lubricating oil or the like to cool the airframe surface. As a surface, it relates to a helicopter adapted to be used.

[0002]

2. Description of the Related Art The following cooling device has been conventionally used for cooling a lubricating oil or the like used in a gear box for transmitting a driving force from a helicopter engine to a main rotor or a tail rotor. . In the structure shown in FIG. 7, the power shaft 05 is taken out from the gear box 04, and the power shaft 0
5, the fan 06 provided at the inlet of the duct 07 provided at the upper part of the fuselage 03 is rotated, and air as a cooling medium is taken into the duct 07 from the atmosphere, passed therethrough, and provided at the exit side of the duct 07. The lubricating oil as a medium to be cooled, which flows through the inside of the radiator 08, is cooled.

However, in such a cooling device 02, in order to generate an air flow for cooling in the duct 07, the power is branched from the gear box 04 and taken out, and the power for rotating the air fan 06 is taken out. Therefore, there is a problem that the helicopter 01 as a whole causes power loss.
Further, since the fan 06 is provided and the power for driving the fan is taken out, the power shaft 05 and the like need to be provided separately from the gear box, which causes a problem that the cost and weight are increased.

In order to solve such a problem, a cooling device using the downwash of the main rotor as a cooling medium has been proposed. For example, JP-A-4-2769
In No. 8 "Helicopter radiator arrangement structure", a cylindrical guide, which opens toward the rotation surface of the main rotor, is provided at the upper end of the body, and the radiator is installed inside the cylindrical guide. A downwash as a cooling medium from the main rotor is introduced into the cylindrical guide to cool the medium to be cooled passing through the inside of the radiator.

However, in the case where the tubular guide for introducing the downwash is provided on the outside of such a body, the tubular guide protruding to the outside of the fuselage adversely affects the movement performance of the helicopter, and particularly, high speed and high speed are achieved. There is a problem that it is difficult to adopt a helicopter that is required to have a turning ability. Also,
In addition to the equipment for achieving the function as a helicopter, providing a cylindrical guide is effective in reducing weight.
Not so effective. Furthermore, since the tubular guide protruding outside the aircraft constantly receives downwash to generate a force that constantly pushes the aircraft downward, it is necessary to generate a lift force in the main rotor to compensate for this. However, improvement in terms of power loss cannot be expected so much.

[0006]

DISCLOSURE OF THE INVENTION The present invention solves the above-mentioned problems by eliminating the need for power for operating the cooling medium, and therefore, the power loss does not occur and the cost is reduced. An object of the present invention is to provide a helicopter having a cooling device which can reduce the weight and does not affect the exercise performance.

[0007]

Therefore, the helicopter of the present invention has the following means. The cooling surface is the surface of the aircraft that is hit by a lot of downwash, or the surface of the aircraft that is hit by a large amount of the combined downwash and external airflow during flight is the cooling surface. The helicopter is equipped with a cooling device having a passage for passing. The surface of the fuselage does not refer only to the body of the helicopter, but is a skid that is normally equipped on the lower part of the helicopter's fuselage, or a stabilizer wing attached to the rear of the fuselage, etc. The surface of is also included.

[0008]

The helicopter body is made of a light metal such as an aluminum alloy, except for special parts such as the main rotor and engine. This aluminum alloy has a high thermal conductivity and is an optimum member for heat exchange. The helicopter of the present invention utilizes the airframe itself as a part of a heat exchanger and a cooling surface, and an airflow flowing outside the airframe and a passage provided inside the airframe surface used as a cooling surface of the heat exchanger. Since heat is exchanged with a cooling medium such as lubricating oil flowing through the cooling medium to cool the cooling medium, (1) a cooling medium for generating a flow of air is generated. No power is required, the power loss required for this power supply is eliminated, and the cost and weight increase associated with installation of the power unit can be reduced. (2) Further, it is not necessary to install a device for utilizing the downwash outside the machine body, which allows the helicopter to have excellent maneuverability. Furthermore, the power loss that has occurred with the use of downwash is eliminated, and the increase in weight can be reduced.

[0009]

Embodiments of the helicopter of the present invention will be described below with reference to the drawings. FIG. 1 is an overall perspective view showing a first embodiment of the helicopter of the present invention, FIG. 2 is a schematic view showing details of the cooling device shown in FIG. 1, and FIG. 3 is a second embodiment of the helicopter of the present invention. FIG. 4 is an overall perspective view showing an example, FIG. 4 is a cross-sectional view of the cooling device of FIG. 3, and FIG. 5 is a cooling system diagram when the cooling device shown in FIG. 2 or 4 is applied to lubricating oil cooling.

A helicopter 1 having a main rotor 3 rotating above the body 2 and stopped at a predetermined position in the air by a lift force generated by the rotor 3 blows down the main rotor 3 as shown in FIG. (Down wash) D occurs around the aircraft. Further, in the helicopter 1 flying at a high speed, in addition to the above downwash D, an air flow accompanying the flight is generated around the airframe.

The present invention utilizes such downwash D and the air flow as a cooling medium. In the first embodiment shown in FIG. 1, an outer plate forming a single wall of the body 2 is used. A helicopter including a cooling device 10, a part of which also serves as the cooling surface 4. The cooling device 10 is shown in FIG.
As shown in FIG. 3, a double wall structure is provided in which the inner wall 5 is provided inside the cooling surface 4 which also serves as the outer plate of the body 2, and the inside of this double wall is partitioned by the partition wall 6 to form one cover. It has a welded assembly structure in which the passage 7 for the cooling medium L is formed.

Further, the inner wall 6 located at both ends of the passage 7 is provided with an inlet 8 and an outlet 9 connected by a flare joint. An example in which the cooling device 10 cools the lubricating oil used in the gear box 11 will be described with reference to FIGS. 2 and 5. As shown in FIG. 5, the lubricating oil L accumulated at the bottom of the gear box 11 is sucked by the pump 12, regulated by the pressure regulating valve 13 and sent to the cooling device 10.

As shown in FIG. 2, the lubricating oil L introduced from the inlet 8 between the cooling surface 4 and the inner wall 5 is, as shown by the arrow,
It flows through the passage 7 inside the cooling device 10. On the other hand, the cooling surface 4
Downwash D, or a flow of air that is a uniform flow combined with downwash D and serves as a cooling medium flows along the cooling surface 4 on the outer side of, and thereby the lubricating oil L is cooled.

The lubricating oil L cooled in the cooling device 10 is sent from the outlet 9 to the jet nozzle 14 in the gear box 11 and used for lubricating gears and bearings in the gear box 11. In the case of the present embodiment, it is not necessary to provide the cooling surface 4 that also serves as the outer plate on the entire body, and for a normal helicopter having a small cooling capacity, the portion shown in FIG. 1 is sufficient, but the required cooling capacity is required. The size may be determined according to the design of each helicopter. Further, by adopting this embodiment, it is possible to reduce the weight and cost by about 1% as compared with the conventional one shown in FIG. 7, and the power loss can be prevented to the same extent.

Next, FIG. 3 is a view showing a second embodiment of the helicopter of the present invention, which is equipped with a cooling device which also serves as a cooling surface for the skid 20 for wearing and wearing, which is usually mounted on the helicopter 1. When cooling the medium to be cooled by the cooling device, basically, it suffices that the heat transfer area for heat exchange with the cooling medium is large. Therefore, in the case of the present embodiment, as shown in FIG. The inside of the pipe of the pipe 23 is divided into two by the partition wall 21, and the fin 22 is provided inside the pipe to increase the heat transfer area.

Here, the lubricating oil as the medium to be cooled is made to flow forward on the right side of the partition wall 21, the flow is reversed at the end of the skid 20, and the backward lubricating oil is made to flow on the left side of the partition wall 21. . By doing so, the underwear skid 20 including the small-diameter pipe 23 can be used as a cooling device having a large heat transfer area. Further, the inlet / outlet of the lubricating oil L to the skid 20 may be provided at the joint between the skid 20 and the body 2.

In the case of the present embodiment, the skid 20 which is the cooling device 10 is located at a position distant from the body 2 and has a large flow velocity around it, and the entire circumference of the skid 20 can serve as a cooling surface. Cooling can be performed more efficiently than the cooling device 10 for the helicopter 1 according to the embodiment. Further, there is no need to provide a space for installing a cooling device inside the body 2, and a helicopter with high volume efficiency can be obtained.

It should be noted that it is also possible to provide a cooling device provided at the rear of the fuselage 2 and having outer plates of the horizontal 25 and the direction stabilizing blades 26 as cooling surfaces, although the positions are far from each other.

[0019]

As described above, according to the helicopter of the present invention, the following effects can be obtained with the configuration shown in the claims. (1) The cooling medium, which does not require the power for generating the flow of air, eliminates the power loss that was required for this power supply, and the cost of installing the power unit,
And the increase in weight can be reduced. (2) It is not necessary to install a device for using the downwash outside the machine body, which allows the helicopter to have excellent maneuverability.

Further, the power loss accompanying the use of downwash can be eliminated and the increase in weight can be reduced.

[Brief description of drawings]

FIG. 1 is an overall perspective view showing a first embodiment of a helicopter of the present invention.

FIG. 2 is a schematic diagram showing details of the cooling device shown in FIG.

FIG. 3 is an overall perspective view showing a second embodiment of the helicopter of the present invention.

4 is a cross-sectional view taken along the line AA of FIG.

FIG. 5 is a system diagram showing cooling of lubricating oil of a helicopter.

FIG. 6 is a diagram showing downwash of a helicopter.

FIG. 7 is an overall perspective view of a helicopter including an example of a conventional cooling device.

[Explanation of symbols]

 1 Helicopter 2 Body 3 Main rotor 4 Cooling surface (outer plate) 5 Inner wall 6,21 Partition wall 7 Passage of medium to be cooled 8 Inlet 9 Outlet 10 Cooling device 11 Gearbox 12 Pump 13 Pressure regulator 14 Jet nozzle 20 Skid 22 Fin 23 Pipe 25 Horizontal stabilizers 26 Directional stabilizers

Claims (1)

[Claims] 1. A downwash is generated, and
In a helicopter in which a main rotor that generates propulsive force is provided at the upper end of the fuselage, the cooling surface formed on the downwash or the portion of the aircraft surface where the air flow around the fuselage is large, and the inside of the cooling surface A helicopter characterized by comprising a cooling device which is composed of a passage which is divided into a passage through which a medium to be cooled passes.