JP2000043797A - Rotary blade type propelling force generator and helicopter - Google Patents

Abstract

PROBLEM TO BE SOLVED: To realize stable flying by facilitating the control of a flying posture, wherein the necessary of generating a propelling force in a direction for canceling reaction torque is eliminated, the opposite operation torque being generated by the rotation of a tail rotor because the reaction torque of a reverse direction to the rotational direction of a main rotor is transmitted to a fuselage when a driving force is transmitted from an engine through a gear mechanism to the main rotor in a helicopter. SOLUTION: By employing a propelling force generator provided with an output turbine 10 having a turbine shaft directly connected to the drive shaft 2 of a main rotor 1 and a gas generator 20 for generating a gas flow used to actuate the output turbine 10, the necessity of providing a tail rotor 5 to cancel reaction torque is eliminated, the frying posture control of a fuselage is facilitated, and thus stable frying is realized.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a thrust generator for generating a thrust by driving a rotary wing and a helicopter employing the thrust generator.

[0002]

2. Description of the Related Art In an aircraft that flies by driving a rotor to generate thrust, a reaction torque is generated in a direction opposite to the rotation direction in accordance with the driving of the rotor, so that a structure for canceling the reaction torque is provided. .

[0003] Taking a helicopter as an example, as shown in FIG. 4, a driving force is transmitted through a gear mechanism 4 provided between a drive shaft 2 of a main rotor 1 and an engine 3, and the main rotor Lifting force is obtained by rotation of 1. At this time, a reaction torque is generated in the body of the helicopter in a direction opposite to the rotation direction of the main rotor 1 (the direction of arrow A in the figure).

Therefore, in the case of a single-lift helicopter shown in the figure, a tail rotor 5 is provided at the rear end of the fuselage. The tail rotor 5 is driven by the engine 3 similarly to the main rotor 1, and the rotation of the tail rotor 5 generates a thrust in a direction to cancel the reaction torque, thereby stabilizing the body.

[0005] In the case of a dual lift helicopter having two main rotors, the two main rotors are rotated in two forward and reverse directions, respectively, and the reaction torques of the two are canceled out to stabilize the fuselage. It is planned.

[0006]

In the case of a single-lift helicopter, the structure of the fuselage is complicated due to the provision of the tail rotor.
There is a problem that it is very difficult to control the rotor. Furthermore, if the tail rotor fails for any reason during flight, the aircraft can quickly lose stability and cause a major accident.

The present invention has been made in view of the above circumstances, and a thrust generating device that obtains a thrust (lift) by the rotation of a rotary wing prevents the generation of a reaction torque due to the rotation of the rotary wing. An object of the present invention is to realize a stable flight by facilitating the control of the flight attitude of an airframe such as a helicopter that obtains a thrust by the thrust generating device.

[0008]

As means for solving the above-mentioned problems, a rotary wing type thrust generator having the following configuration is employed. This rotating blade type thrust generator generates thrust by driving a rotating blade, and includes an output turbine in which a turbine shaft is directly connected to a driving shaft of the rotating blade, and a gas flow for generating a gas flow for operating the output turbine. And a generator.

When an output turbine driven by a gas flow is employed as driving means for the rotor blades, the gas flow blown out from the gas flow generating device causes a uniform force to act on the surroundings to rotate the turbine shaft. The reaction torque is not received from the turbine side in one direction as in the case of using a gear mechanism, and the reaction torque is generated even if the rotor is rotated by rotating the drive shaft directly connected to the turbine shaft. Is suppressed.

[0010] It is desirable to employ a radiation turbine or a mixed flow turbine as the output turbine. According to each of these turbines, it is possible to further improve the efficiency of recovering the energy obtained from the gas flow generator.

Further, by employing the rotary wing type thrust generator as a drive mechanism for the main rotor of the helicopter, the tail rotor itself is not required. Further, it becomes easier to control the flight attitude of the aircraft.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of a rotary wing thrust generator and a helicopter according to the present invention will be described with reference to FIGS. FIG. 1 shows a single-lift helicopter. The helicopter includes an output turbine 10 that rotates a drive shaft 2 of the main rotor 1 as a thrust generating device that generates a thrust by rotation of the main rotor 1, and a gas that generates a gas flow that operates the output turbine 10. A generator (gas flow generator) 20 is provided.

The output turbine 10 is installed with the turbine shaft 11 directly connected to the drive shaft 2 and is operated by combustion gas blown from a gas generator 20 arranged adjacently.

A radiation turbine is employed as the output turbine 10 (hereinafter referred to as the radiation turbine 10). The radiation turbine 10 is also called a radial turbine or a radial turbine, and as shown in FIG. 2, combustion gas blown from a gas generator 20 is supplied to a turbine shaft 1.
In the process of flowing toward the center in the radial direction from the chamber 12 provided around the periphery 1, the gas flow strikes the rotor blade 13 provided on the turbine shaft 11 to rotate the turbine shaft 11.

In the case of the radiation turbine 10, the turbine shaft 11
The combustion gas flows from the surroundings toward the rotor blades 13 provided in the turbine, and a uniform force (gas pressure) acts from the surroundings to rotate the turbine shaft 11. The body does not receive reaction torque from the turbine side in the direction, and even if the main rotor 1 is rotated by rotating the drive shaft 2 directly connected to the turbine shaft 11, little reaction torque is generated on the body. .

Therefore, for the helicopter provided with the thrust generator configured as described above, it is not necessary to generate the thrust for canceling the reaction torque by the tail rotor 5 as in the prior art. In other words, there is no need to control the tail rotor 5 to cancel the reaction torque,
Since the tail rotor is used only to change the direction of the airframe, the flight attitude control of the airframe becomes much easier than in the past, and a stable flight can be realized.

The same effect can be obtained by using a mixed flow turbine 30 as shown in FIG. The diagonal flow turbine 30 is similar to the radiant flow turbine 10 in that the turbine shaft 31 is rotated without generating a reaction torque, and the shape of the moving blade 33 is changed so as to be an oblique gas inflow direction. Accordingly, the gas flow flowing from the chamber 32 is guided more smoothly than the radiation turbine 10, so that the energy recovery efficiency of the combustion gas can be further improved as compared with the radiation turbine 10. The power performance of the helicopter can be improved.

In the above embodiment, the airframe using the tail rotor 5 for directional control has been described, but the mechanism for performing directional control is not limited to the tail rotor.
For example, the following mechanism can be considered. (1) A part of the compressed air is taken out from the turboshaft engine, and the compressed air is guided to a certain distance from the rotor rotation axis, and is blown out in both rotation directions of the rotor. When changing the direction of the airframe, the amount of compressed air blown in both directions is changed between the two sides, and the amount of blown air is made different to generate thrust and thereby control the direction. (2) A variable nozzle is provided at the outlet of the output turbine, the blowing direction of the nozzle is changed, and the direction of the airframe is controlled by the reaction. (3) A swirl flow in the direction opposite to the rotation direction of the rotor is intentionally left at the outlet of the output turbine, and the rotation force in the direction opposite to the rotation direction of the rotor is extracted by the swirl flow. Direction control is performed by controlling the provided clutch mechanism (which generates a force in the same rotational direction as the rotor) and balancing the both.

Further, in the above-described embodiment, an example is shown in which the rotary wing type thrust generator according to the present invention is applied to a helicopter. However, the present invention is not limited to this, and may be applied to, for example, a propeller type aircraft. .

[0020]

As described above, according to the rotor-type thrust generator according to the present invention, the gas flow blown out from the gas flow generator exerts a uniform force from the surroundings to rotate the turbine shaft. Therefore, unlike the case where a gear mechanism is used, a reaction torque is not received from the turbine side in a predetermined direction, and the rotation blade is rotated by rotating a drive shaft directly connected to the turbine shaft. The generation of reaction torque can be suppressed. Further, when the rotary wing type thrust generator is employed in an aircraft, there is no need to provide a structure for canceling the reaction torque.

Further, by employing a radiant flow turbine or a mixed flow turbine as the output turbine, the efficiency of recovering the energy obtained from the gas flow generator can be further improved. The power performance of the employed aircraft can be improved.

By employing the rotary blade type thrust generator according to the present invention as a drive mechanism for a main rotor of a helicopter, it is not necessary to generate a thrust for canceling a reaction torque by a tail rotor as in the prior art. In other words, there is no need to control the tail rotor to counteract the reaction torque, and the tail rotor is used only to change the direction of the fuselage. It becomes easy and a stable flight can be realized.

[Brief description of the drawings]

FIG. 1 is a view showing one embodiment of a rotary wing type thrust generator according to the present invention, and is a schematic configuration diagram when the thrust generator is adopted in a single-lift helicopter.

FIG. 2 is a side sectional view showing a configuration of a radiation turbine.

FIG. 3 is a side sectional view showing a configuration of a mixed flow turbine.

FIG. 4 is a schematic configuration diagram illustrating an example of a conventional thrust generating device.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Main rotor (rotary blade) 2 Drive shaft 5 Tail rotor 10 Radiation turbine 11 Turbine shaft 12 Moving blade 20 Gas generator (gas flow generator) 30 Mixed flow turbine

Claims (4)

[Claims] 1. A thrust generator for generating thrust by driving a rotor, comprising: an output turbine having a turbine shaft directly connected to a drive shaft of the rotor; and a gas generating a gas flow for operating the output turbine. A rotor-type thrust generator comprising a flow generator. 2. The rotary blade type thrust generator according to claim 1, wherein a radiation turbine is adopted as the output turbine. 3. The rotating blade type thrust generator according to claim 1, wherein a mixed flow turbine is adopted as the output turbine. 4. A helicopter comprising the rotary wing type thrust generator according to claim 1, 2 or 3.