KR20110017996A - Turbine of turning blade structure which is more efficient in energy conversion - Google Patents

Abstract

PURPOSE: A turbine using a rotary blade structure with improved energy conversion efficiency is provided to transfer excellent drag power to a rotary shaft by controlling the angle of each blade. CONSTITUTION: A turbine using a rotary blade structure with improved energy conversion efficiency comprises a turbine rotary shaft, rotary blades, a blade rotary shaft, stoppers, a magnet(5) for preventing noise, electromagnets(4), a slip ring(2), and a brush device. The stoppers for restraining the turning radius of the rotary blades are installed in the rear of the rotary blades and control the position of the blades.

Description

Turbine of turning blade structure which is more efficient in energy conversion

The present invention is a combination of the field of hydrodynamics and mechanical elements, the field of hydrodynamics is a field that transfers more energy to the rotational power of the turbine to convert the drag kinetic energy into mechanical rotational motion in the fluid in the flow It is a wing shape and method that can maximize drag force, and in the field of mechanical element, a device capable of minimizing drag force, a mechanism that transmits recovered drag to a turbine shaft without loss, and rotor blades and stoppers in a turbine ( This is related to shock absorbers and other rotary shaft configurations of the contact impulse between stoppers.

Drag is a force acting in the opposite direction of a fluid flow, for example, the force felt in a hand holding an umbrella when carrying an umbrella on rainy and windy days.

The magnitude of drag D is the relative velocity of the fluid to v, the density of the fluid to ρ, and the cross-sectional area of the object to be S,

D = 1 / 2CρSv ^ 2

to be. Where C is a constant determined by the shape of the object or the state of the surface, usually called the drag coefficient.

Using the renewable energy in the above drag equation, the relative speeds v and density ρ are the most important considerations according to the location selection and fluid type according to the natural environment.

[Document 1] Naver Search Result of "D drag", Doosan Encyclopedia, Search Date 2009.8.3

Background of the Invention The present invention seeks to transfer the generated drag to the turbine's rotary shaft without loss and to create the wing position when the drag is configured and positioned so as to maximize the drag matched to the turbine rotational axis in the cross-sectional area S. It is a technique to change and minimize, and invented a method to maximize the drag coefficient represented by the proportional constant C by using the shape, structure, and additional device.

       In FIG. 2, when the fluid flow is 5, the wing 10 in the forward direction (conceptual wing 2 below) is perpendicular to the fluid flow direction in a structure and a position capable of receiving the most drag. This overlapped with the plan of FIG. 2 and the region-specific shape is as follows.

                                Wings 3

                           C area | B area

                   Wings 4 -------- + -------- Wings 2

                           D area | A area

                                Wings 1

                   ↑↑↑↑↑↑↑↑↑↑↑↑↑↑ (Fluid direction)

              [Planar conceptual diagram of FIG. 2 and region plane according to fluid flow]

       When the turbine axis of rotation (+ part) rotates in the A, B, C, and D directions (counterclockwise), the only wing that helps to rotate in the forward direction is the drag of the wing in the A + B region, and the rest is provided only for reducing factors. The most important factor is to devise a device that can receive the maximum drag in the A + B area and a device that can receive the minimum drag in the C + D area.

       The number of blades is suitable for 3 ~ 5 so that a large amount of fluid enters the blade and impulses in a short time according to the turbine's rotation, but it depends on the turbine design speed, the speed of the fluid, the density and the pressure. Design and analysis is a factor.

       The number of wings varies depending on the designer, but generally, the number of blades tends to increase when the turbine is high speed. In the present invention, the number of blades is a low speed turbine. As the number of blades increases, the fluid incidence area decreases, and the amount of fluid supplied to the blades decreases, and the fluid flow space of the central turbine shaft portion becomes narrow, leading to a decrease in efficiency. The shape of the wing corresponds to the drag coefficient C in the above drag equation, as well as the shape (Fig. 3) as well as the state of the surface affects the magnitude of the drag is the subject of the invention of the present invention (Fig. 5).

       Rotational speed (rpm) is the main factor that transmits the kinetic energy at the velocity of fluid (m / s) to the rotational axis in relation to the rotational diameter, but in the case of high-speed rotation only a part of the wing in the A + B area of the upper conceptual diagram It is converted into rotational motion, which causes a sharp drop in conversion efficiency. To explain this correlation simply, the larger the diameter and the larger the rotational speed (rpm), the faster the velocity of the fluid is needed.

       In order to prevent such a decrease in efficiency, several devices such as a constant velocity rotating device and a blade pitch angle control of the turbine are additionally required.In the present invention, the blade shape and surface in the turbine, the blade position and angle in the maximum area of drag, and the minimum area are The invention has been invented with respect to the position and angle of the wing and the noise and shock mitigation device according to the impulse during the wing movement.

In FIG. 2, when the fluid flows in the fifth direction, the vanes participating in the radial direction in the turbine rotational direction to help generate power may transmit the drag kinetic energy in the direction of fluid flow to the rotational axis as much as the tenth blade. The outer wing is not helpful to the rotational force or to serve to reduce the rotational power in the reverse direction. Ignoring the coefficient of friction, pressure, temperature, and other losses, the equation gives the total amount of drag that each wing receives.

Total drag size = 10 wing size-(9 wing + 11 wing + 12 wing size)

If the total drag magnitude> 0 (Zero), it can be said to be the forward rotation, the reverse rotation is reverse, if the total drag magnitude and the total drag of each wing is the same (Zero) can be said to be a stationary state. It is obvious that the larger the result of this equation, the larger the force applied to the rotating shaft in the forward direction, and the better the energy conversion efficiency of the turbine.

Therefore, it is the most important element of the turbine to achieve maximum efficiency, so that the forward drag wing of the rotating shaft can receive the maximum drag, and the reverse direction of the rotation direction or the wing that does not help maintain the minimum drag.

To maximize drag, drag is maximized when the vanes are located perpendicular to the flow of fluid (10 in Figure 2) and minimum when vanes are positioned horizontally in fluid flow (9, 11, 12 in Figure 2). do. However, in the conventional turbine, the blades are fixed, which is a main factor in reducing the turbine rotational force due to the reverse drag when it is in position 12 of FIG.

This fixed wing structure is rotated and a stopper that can limit the rotation radius of each wing (Stopper) is installed on the back of each wing to limit the position of the wing movement. Although the space is limited, as the blade moves about each axis of rotation (No. 2 in Fig. 2), when each blade touches the stopper when the entire turbine rotates (No. 13 in Fig. 2), it is proportional to the weight and size of the blade and the magnitude of drag. Since the impact noise and impact can be transmitted to the stopper and the wing at the same time, which may cause the turbine's life, the magnet is placed at the back contact of the wing and the electromagnet at the stopper to solve the noise and impact at the same time. It was solved using manpower, repulsive force and compression spring.

Although there is an electronic control method mainly used in medium and large turbines as a method of changing the vane angle, there are disadvantages in that the configuration is complicated and foreign technologies have to pay royalties for use and maintenance is difficult.

Accordingly, the invention has been invented a device capable of automatically changing the wing angle so that the drag can be the maximum or minimum depending on the position of the fluid using the force acting on the wing without any additional device.

In addition, the wing shape (Fig. 4) and the surface in the configuration as shown in Figure 5 in order to receive the maximum drag.

Rotating blade angle control device, which does not require external external maneuvering, is designed to adjust the blade angle at the maximum and minimum points of drag on the flow of fluid, thereby providing excellent drag compared to rotary turbines using conventional drag. To pass on. Even on the wing surface, the surface of the existing wing front (No. 7 in Fig. 4, concave inner surface) is smooth or flat in its own state, but it is composed and mounted in various shapes (Fig. 5) to maximize drag on the surface. It is characterized by an excellent improvement, and the back of the wing is spherical smoothly to minimize the resistance of the fluid.

In addition, as a way to mitigate the impact of the stopper and the wing when moving the rotary blades is characterized by solving the noise and impact at the same time using the magnetic force (4, 5 in Figure 4) (Fig. 3).

The most inefficient part in converting and using kinetic energy of a fluid into electrical energy is a turbine that converts kinetic energy into rotational motion. The turbine, which greatly improves the problem of the low-efficiency turbine, uses electric energy using renewable energy. It can be used as a driving force for production, can replace depleted fossil fuels, and can use pollution-free clean energy cheaply and contribute to preventing global warming.

Referring to the preferred embodiment in detail with reference to the drawings of Figures 1 to 5, Figure 1 is a three-dimensional view showing the overall turbine configuration, Figure 2 is a plan view showing the overall structure of the turbine, the main configuration is a turbine Rotating shaft (with bearing device for rotation), rotary blades, blade rotation axis (Fig. 4, bearing device), wing stopper, top and bottom plate, rotor blade impulse and noise prevention magnet (No. 5 in Fig. 3) and electromagnet device ( 3, 4), the slip ring and the brush device for electromagnet power supply are required.

The first consideration is to determine the turbine output torque to determine the wing size, which is a very important basis for starting up generators and other devices with turbine rotational torque. Let's do it.

Based on the required turbine rotational torque (output), the size of the wing front cross-sectional area (width X length) is determined and the longitudinal length (height) of the turbine rotation axis and the longitudinal length of the upper and lower plate support structures (wing rotation axis, stopper column) are determined. The supporting structure refers to a total of eight, with four wing stopper posts on each wing and four axis of rotation of each wing, which are firmly fixed to the top and bottom plates. The shape of the top plate and the bottom plate is circular and the two sizes are the same, and the minimum radius size of the top plate and the bottom plate should be at least larger than the size of the blade rotation width plus the size of the turbine shaft radius (13 in FIG. 2).

The upper and lower plates are fixed to the turbine shaft bearing, and the turbine shaft center is fixed to the column or fixture. The bearings of the turbine shaft are designed to adequately cover the weight and torque of the entire turbine. According to the design, the whole center of gravity is considered to be located on the turbine's axis of rotation, and manufacturing is necessary. If the asymmetry of the center of gravity occurs, the bearing wear parts such as the bearing parts of the turbine's axis of rotation are intensified, which causes the shortening of life.

The position of the blade rotation axis is positioned the blade rotation axis and the stopper column position (No. 4 in Figure 2) symmetrically with respect to the turbine rotation axis as shown in FIG. The four positions of the rear stopper support (columns) on the side of the turbine shaft are located at the vertices of the square (No. 7,8 in Figure 2), which are two-thirds of the blade width from the center of the turbine shaft. (No. 13 in Fig. 2) Place the sum of the radius sizes apart (No. 4 in Fig. 2).

The four points of the wing axis are drawn on the sides of the imaginary square (fig. 8 in Fig. 2) drawn from above, and a square of the same size is drawn so that the wing axis is located at the outer corner of the extended square. 2, 2 times)

To solve the shock and noise problems caused by the impulse of the wing, align the same pole of the strong magnetic magnet at the position where the stopper touches the back of the wing and fix it firmly in the direction of impulse (No. 5 in Fig. 3). Place the electromagnet (No. 4 in Fig. 3) on the opposite stopper column, where the pole corresponding to the repulsive force (NN or SS) of the magnet is arranged. The number of magnets attached to the vanes and the strength of the opposing electromagnets is sufficient to provide more than a repulsive force to maintain non-contact and non-impact, depending on the vane size and the maximum drag magnitude of the fluid.

The electric power supplied to the electromagnet attached to the rear stopper of each blade in a turbine is supplied to the turbine rotating shaft by attaching the slip ring (No. 2 of FIG. 3), and using a brush (No. 7 of FIG. 3) from a turbine exterior.

In case of abnormal operating conditions, i.e. when the fluid velocity is too high to exceed the limit of the non-impact shock absorber, a high-strength compression spring is installed at the top, middle, and bottom of the stopper pillar impingement surface behind the wing to prevent breakage (Fig. 3). Attach 3). Even when the wing is subjected to maximum impact and pressure, it is attached with a height at maximum compression and a spring that can withstand pressure so that it does not touch the shock absorbers installed on the wing and the stopper column.

In order to attach the electromagnet device smoothly, 4 stopper columns are semi-circular as shown in Fig. 6, and the electromagnet is mounted on the surface. Install accordingly. The electromagnet is sealed to be waterproof and firmly fixed to the stopper column.

       Same as the effect item and the specific details of the invention

1 is a three-dimensional view of the turbine structure

2 is a turbine plan view and a structural diagram

3 is an electromagnet structure diagram of a magnet and a stopper attached to a blade in a turbine.

4 is a structure of the wing shape and rotation axis of the wing

5 is a model diagram of drag adder installed on the front surface of the fluid impingement surface

Claims (5)

Inside the turbine using the drag force of the fluid, the wing which receives the forward drag matched with the turbine rotation direction (counterclockwise) transmits the forward drag to the turbine axis of rotation and then rotates along the turbine axis of rotation. Rotary vane rescue device to minimize drag (Figure 2) The apparatus of claim 1, wherein the stoppers behind the blades limiting the radius of rotation of each blade in the turbine are impinged with each other when the blades move in accordance with the position, thereby generating noise and breaking the rotating blades. 3, 4, 5)        When the polarity (+,-) of the external electromagnet power supply is changed (No. 8 in Fig. 3), the magnetic pole of the electromagnet is reversed, and the repulsive force with the blade is attracted. Also, the electromagnet supply current amount control (No. 8 of FIG. 3) is a device that can adjust the rotational torque (output) intensity of the turbine by the magnetic force adjustment. The rotor blades subjected to the drag of the fluid flow in the turbine are arc-shaped (No. 7 in Fig. 4), and the wings arc length is three-eighths the length of the circumference (the arc length corresponding to the center angle of 135 degrees). Rotating vane device with 2/3 point of right center of gravity (No. 8 in Fig. 4) along the arc line with reference to the front face (No. 7 in Fig. 4) In order to maximize the forward drag of wing 10 of FIG. 2, the front surface of wing 7 of FIG. 4, that is, the fluid flow impulses to generate a drag as shown in FIGS. Additional structures to help recover the maximum amount of drag lost and lost

Images