A rotor propeller device

Abstract

The present application discloses a kind of rotor propeller device, belong to a kind of airfoil device of aircraft wing or fluid power generation.This application includes multiple blades (1), machine base (2) and transmission component (3), the blade (1) is arranged on the machine base (2) or the transmission component (3), and the front blade adjacent to front and back as the rear blade of canard, promote the efficiency of using wing tip vortex.This application rotor propeller device uses combined blade to form canard layout, low speed rotation, effectively reduce vibration and noise;And wing tip vortex is utilized, imitate the efficiency of improving the way of goose array flight.

Description

Technical Field

[0001] This invention relates to an airfoil device for aircraft or fluid power generation, specifically a rotor propeller device. Background Technology

[0002] The earliest prototype of the rotor propeller was a traditional Chinese children's toy, the bamboo dragonfly. A rotor propeller is a device that converts engine power into propulsion or fluid kinetic energy into mechanical energy by rotating blades in a fluid. Rotary propellers can consist of two or more blades and can be classified into various types according to their applications, such as propellers for windmills, airplanes, and ships.

[0003] Because the blade speed is limited by the wingtip speed, rotor propellers cannot be made larger and larger. Currently, existing rotor propeller technology offers limited efficiency improvements, and the vibration and noise generated by high-speed rotation cannot be overcome. Summary of the Invention

[0004] In order to solve the above-mentioned technical problems or defects in the prior art, the present invention provides a rotor propeller with a low rotation speed, which effectively reduces vibration and noise. In particular, the blades with a canard configuration can make full use of wingtip vortices to improve efficiency.

[0005] The rotor propeller device of the present invention is achieved through the following technical solution: a rotor propeller device, comprising multiple blades, a base and a transmission component, wherein the blades are disposed on the base or the transmission component, and the adjacent front blades serve as canards for the rear blades, thereby promoting efficiency by utilizing wingtip vortices.

[0006] Preferably, the blades are arranged in groups of at least two blades coupled close to or far from each other; and at least two groups are respectively arranged on the base, or the blades in the same group are integrated through the wing root and arranged on the transmission component.

[0007] Preferably, the base is composed of at least two annular rings, and the blades are disposed on the annular rings of the base.

[0008] Preferably, the blades and the base or transmission components constitute a rotor propeller device with or without a central shaft.

[0009] Preferably, the blades, which are the front blades of the canard wing, are positioned on a horizontal plane that is higher than or level with the rear blades.

[0010] The beneficial effects of this invention compared to the prior art are:

[0011] The rotor propeller device of this invention adopts a canard layout with combined blades, which effectively reduces vibration and noise at low speed rotation; and utilizes wingtip vortices to improve efficiency by mimicking the flight pattern of geese. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the first embodiment of a rotor propeller device according to the present invention.

[0013] Figure 2 This is a schematic diagram of a second embodiment of a rotor propeller device according to the present invention. Detailed Implementation

[0014] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0015] Figure 1 This invention illustrates a first embodiment of a rotor propeller device, comprising a base 2 and multiple blades 1 mounted on the base 2. The base 2 has a five-ring structure, with each ring fixedly connected to the other rings via the blades 1. A fixed transmission component 3 is located at the center of the innermost ring, connecting to the fuselage, and is driven by the fuselage engine to rotate or collect fluid kinetic energy and convert it into mechanical energy. The blades 1 are arranged in groups of three, using close-range or long-range coupling, with their wingtips uniformly facing outwards on the five-ring base 1. The wing root, wingtip, and middle of each blade 1 are fixedly connected to the rings of the base 2, enabling the front blade to act as a canard for the rear blade, promoting efficiency through the use of wingtip vortices. The blades 1 are symmetrically arranged on the base 2 in four sets of coupled blades, achieving smooth rotation.

[0016] Figure 2 This invention illustrates a second embodiment of the rotor propeller device, comprising a base 2 and multiple blades 1 mounted on the base 2. The base 2 has a five-ring structure, with each ring fixedly connected to the blades 1 to form a single unit. A fixed transmission component 3 is provided on the outer wall of the outermost ring, connecting to the fuselage. The fuselage drives rotation or collects fluid kinetic energy and converts it into mechanical energy via electromagnetic or planetary gears. The blades 1 are arranged in groups of three, using close-range or long-range coupling, with their wingtips uniformly facing inwards on the five-ring base 1. The wing root, wingtip, and middle section of each blade 1 are fixedly connected to the rings of the base 2, enabling the front blade to act as a canard for the rear blade, promoting efficiency through the utilization of wingtip vortices. The blades 1 are symmetrically arranged on the base 2 in four sets of coupled blades, achieving smooth rotation.

[0017] The rotor propeller device of the present invention is not limited to Figure 1 and Figure 2In addition to the two implementation methods, the present invention can also employ coaxial counter-rotating propeller technology, or eliminate the base 2 and directly extend and connect the root of each blade in the same group to form a whole, and then fix it to the transmission component 3 or connect it to the fuselage through a variable pitch mechanism, thereby realizing the technical solution of the rotor propeller device of the present invention. Therefore, any other structure or various changes made to the present invention, as long as there is a technical solution that utilizes the blades or rotor of the canard to improve efficiency, falls within the protection scope of the present invention.

Claims

1. A rotor propeller device, comprising multiple blades (1), a base (2), and a transmission component (3), characterized in that, The blade (1) is mounted on the base (2) or on the transmission component (3); The blades (1) are formed by at least two blades coupled close to each other or far apart, and at least two sets are respectively set on the base (2), or the blades (1) in the same set are integrated through the wing root and set on the transmission component (3), so that the front blades of the same set are positioned on a horizontal plane higher than the rear blades to form a canard, thereby promoting the use of wingtip vortices to improve efficiency. Among them, the outermost ring of the base (2) is provided with a rotor propeller device that fixes the transmission component (3) to the body and forms a rotor propeller device without a central shaft with the blade (1), or the center of the innermost ring of the base (2) is provided with a rotor propeller device that fixes the transmission component (3) to the body and forms a rotor propeller device with a central shaft with the blade (1). The base (2) is composed of at least two annular rings. The wing root, wingtip and blade middle of the blade (1) are fixedly connected to each annular ring of the base (2), so that the front blade serves as the canard of the rear blade. The front blade of the blade (1) serving as the canard is set on a horizontal plane higher than the rear blade. The blades (1) of the same group of blades (1) are in the same ring as the wingtip and blade middle of the blade (1) serving as the canard and the wing root and blade middle of the rear blade (1).

2. The rotor propeller device according to claim 1, characterized in that, The blade (1) is set on the horizontal plane of the rear blade as the front blade of the canard wing.

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