JP2000219199A - High-speed cruising rotor machine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a high-speed cruising rotor machine capable of cruising at high speed without oscillating rotor shafts of rotational blades. SOLUTION: This rotor machine is provided with horizontal rotor blades 14 attached on the upper part of a machine in the width direction at a distance and having a pair of rotor shafts 12 to be rotated in the opposite directions and in the advancing direction, and an air flow speed reduction device 16 for reducing the speed of the air flow flowing on the adjacent side tip 15 between the rotor blades 14. The air flow speed reducing device 16 is a fairing 17 for covering the adjacent side tip 15 (the maximum speed range) between the rotor blades 14 or a variable diffuser for guiding the air flow to the tip by reducing the speed. The tip peripheral speeds of the rotor blades 14 are controlled by the air flow speed reducing device 16 so as not to exceed sound speed.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a high-speed cruising rotor machine having rotating blades.

The maximum cruising speed of an aircraft having a rotary wing, that is, a so-called helicopter, is about 400 km / h, which is less than half compared to the maximum cruising speed of a turboprop aircraft using the same jet engine of about 880 km / h. Stays. For this reason, the helicopter can take off and land vertically, hover, and the like, but has a disadvantage that it cannot perform high-speed cruising.

Further, a tilt rotor (Tilt Rotor) has been put to practical use as a rotor capable of solving the drawback and enabling high-speed cruising. This rotor machine is similar to a helicopter in that it takes off and land by rotating the rotor horizontally and then makes a high-speed cruise by rotating the rotor shaft horizontally and rotating the rotor vertically.

[0004]

However, in the tilt rotor machine, high-speed flight is enabled by allowing the direction of the rotor shaft to swing from vertical to horizontal, so that the mechanism becomes more complicated than that of a helicopter. In order to obtain the same payload, the size of the aircraft becomes large, and there is a problem that the manufacturing cost is increased.

The present invention has been made to solve such a problem. That is, an object of the present invention is to provide a high-speed cruising rotor machine that can cruise at high speed without swinging a rotor shaft of a rotor.

[0006]

In a helicopter, which is a form of VTOL, when the relative forward speed of the rotor, that is, the sum of the machine speed and the peripheral speed of the tip of the rotor blade exceeds the sonic speed, the boundary layer is severely separated. The blade performance is greatly reduced, causing vibration and the like. Therefore, since the tip peripheral speed of the rotor blade is set lower than the sound speed, the machine speed cannot be increased to the level of the fixed wing machine. However, since the portion exceeding the sound speed is only a small part of the whole, if the relative forward speed at this portion is reduced, the machine speed can be increased more than before. The present invention is based on such a new finding.

That is, according to the present invention, there is provided a horizontal rotor blade having a pair of rotor shafts (12) which are mounted on the upper part of the fuselage at intervals in the width direction, and which rotate in opposite directions and in the vicinity thereof in the forward direction. (14) and an airflow deceleration device (16) for decelerating the airflow flowing through the proximal end (15) of the rotor blade, so that the peripheral speed of the tip of the rotor blade does not exceed the sound speed by the airflow deceleration device. , A high speed cruising rotor machine is provided.

According to the configuration of the present invention, the airflow reduction device (16) controls the peripheral speed of the tip of the rotor blade so as not to exceed the sonic speed to reduce the airflow flowing through the tip portion (15) on the near side of the rotor blade. Therefore, it is possible to suppress the relative forward speed of the rotor blade during high-speed flight while keeping the pair of rotor shafts (12) substantially fixed,
A flight speed exceeding the speed limit of a conventional helicopter can be realized.

According to a preferred embodiment of the present invention, the airflow reduction device (16) reduces the airflow to the fairing (17) that covers the proximal end portion (15) of the rotor blade, or to the distal end portion. (18) or a variable diffuser.

[0010] With this configuration, the fairing (17) covers the front end (15) of the rotor blade on the near side, and
By reducing the airflow flowing between the fuselage and the fairing, or by changing the flow path area by the intake (18) or the variable diffuser, decelerating the airflow to the distal end and guiding it to the proximal end (15). The flowing air current can be reduced.

[0011]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of the present invention will be described below with reference to the drawings. In addition, the same reference numerals are given to the common parts in the respective drawings, and the duplicate description will be omitted. FIG. 1 is a schematic perspective view showing a first embodiment of a high-speed cruising rotor machine of the present invention. In this figure, a high-speed cruising rotor machine 10 of the present invention flows through a pair of horizontal rotor blades 14 attached to the upper part of the fuselage 1 at intervals in the width direction, and a proximal end portion 15 of the rotor blades 14. And an airflow reduction device 16 for reducing the airflow.

A pair of horizontal rotor blades 14 rotate in opposite directions about their respective rotor shafts 12 so as to negate each other's moments. Further, the rotor blades 14 are arranged so that the near sides which are close to each other, that is, the portions (proximity-side tip portions 15) passing right above the body 1 in the figure rotate in the forward direction (left side in the figure) during flight. Has become. Therefore, the proximity side tip 15
Is the relative maximum speed region of the rotor blade during flight. The rotor shaft 12 is mounted almost vertically to the fuselage 1, and preferably can be slightly swung during takeoff and landing, hovering, and high-speed cruising so as to enhance flight performance.

In FIG. 1, an airflow reduction device 16 is a fairing 17 that covers a proximal end portion 15 (a maximum speed region) of a rotor blade 14. This fairing 17
Is configured to reduce the airflow flowing between the body 1 and the fairing 17 by at least deflecting the airflow passing through the near-side distal end portion 15 and reduce the relative speed with the airflow in the maximum speed region.

FIG. 2 is a schematic perspective view showing a second embodiment of the present invention. In this figure, the air flow reduction device 16
Is an intake 18 for decelerating and guiding the airflow to the front end portion 15 (the maximum speed region) of the rotor blade 14. The intake 18 is installed independently of the airframe 1, and diffuses the high-speed airflow flowing from the inlet toward the downstream to reduce the speed, and guides the controlled flow field to the blade tip portion (proximal tip portion 15). It has become.

Further, a variable diffuser for changing the flow path area may be provided in place of the intake 18 to realize an optimum flow field in accordance with the flight speed. With these intakes 18 or variable diffusers, the airflow speed passing through the maximum speed region is reduced, and the peripheral speed of the tip of the rotor blade is controlled so as not to exceed the sound speed.

FIG. 3 is a diagram showing a change in speed at the time of intake. This figure shows the intake of a turbofan engine. By using the same intake 18, a high-speed airflow having a Mach number of about 0.9 is diffused downstream at the entrance to decelerate to a near side. It can be seen that the tip 15 can be decelerated to a Mach number of about 0.45 and guided to the blade tip (proximal tip 15).

According to the above-described structure of the present invention, the peripheral speed of the tip end of the rotor blade 14 is controlled by the airflow reduction device 16, that is, the fairing 17, the intake 18 or the variable diffuser, so that the peripheral speed of the rotor blade 14 does not exceed the sound speed. Since the airflow flowing through the tip portion 15 is decelerated, it is possible to suppress the relative forward speed of the rotor blades during high-speed flight while keeping the pair of rotor shafts 12 substantially fixed, which exceeds the speed limit of a conventional helicopter. Flight speed can be realized.

It should be noted that the present invention is not limited to the above-described embodiment, and it is needless to say that various changes can be made without departing from the gist of the present invention.

[0019]

As described above, according to the present invention, a pair of rotor shafts are arranged so that the forward speed of the rotor blades is maximized at the upper part of the fuselage, and the rotor is controlled by the air flow reduction device 16 installed at the upper part of the fuselage. By controlling the peripheral speed of the blade tip not to exceed the speed of sound, it is possible to fly at a higher speed than a conventional helicopter.

That is, the high-speed cruising rotor machine of the present invention comprises:
It has excellent effects such as being able to cruise at high speed without swinging the rotor shaft of the rotor blade.

[Brief description of the drawings]

FIG. 1 is a schematic perspective view showing a first embodiment of a high-speed cruising rotor machine of the present invention.

FIG. 2 is a schematic perspective view showing a second embodiment of the present invention.

FIG. 3 is a diagram showing a speed change in an intake.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Airframe 10 High-speed cruising rotor machine 12 Rotor shaft 14 Rotor blade 15 Proximity side tip part 16 Air flow reduction device 17 Fairing 18 Intake

Claims (2)

[Claims] 1. A horizontal rotor blade (14) having a pair of rotor shafts (12) mounted on the upper part of the fuselage at a widthwise distance from each other and rotating in opposite directions and on the proximal side thereof in a forward direction. An airflow reduction device (1) for reducing the airflow flowing through the front end portion (15) of the rotor blade on the near side.
6), wherein the airflow reduction device controls the peripheral speed of the tip of the rotor blade not to exceed the sound speed. 2. The air flow reduction device (16) includes a fairing (17) covering the proximal end portion (15) of the rotor blade, or an intake (18) or a variable intake that guides the air flow to the distal end portion by reducing the air flow. The high speed cruising rotor machine according to claim 1, wherein the high speed cruising rotor machine is a diffuser.