RU2679695C1 - Aircraft propeller - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: aircraft propeller contains a horizontal shaft on which a multi-blade disk wheel is fixed with outer and inner shells and blades with an increasing angle of attack of the air flow. Blades are made of the plane of the disk by cutting into sectors with an adopted arc length in meters according to the calculated number of blades, followed by bending part of the sectors along the limb lines.EFFECT: invention aims to increase thrust at low revs.1 cl, 3 dwg

Description

The invention relates to wind energy, in particular to wind turbines with a horizontal axis of rotation of the wind wheel, and can be used in aircraft construction as the propeller of airplanes for various purposes and take-off mass (designs by Antonov, Yakovlev, Ilyushin, etc.).

Known aircraft propeller containing a horizontal shaft mounted on it with a wheel with two, three or four blades. The disadvantage of such small-blade screws is that there is insufficient blade area in the peripheral zone.

An object of the present invention is to increase the number of blades, their area and geometric filling of the swept area with the blades of an aircraft propeller, increasing its efficiency.

The present technical essence is achieved by the fact that the aircraft propeller containing a horizontal shaft, a multiblade disk wheel mounted on it with outer and inner shells, between which there are blades with an increasing angle of attack of the air flow, the blades are made from the plane of the disk by cutting into sectors with an accepted length arcs in meters according to the estimated number of blades with subsequent bending of part of the sectors along the bending lines towards the air flow when the rotor rotates from the aircraft engine, while m diameter of the propeller disk is determined by the circumference by the product of the number of blades by the length of the arc of the sector in meters.

The above structural features of the multi-blade disc propeller of the aircraft compared to the existing ones allow, all other things being equal, to significantly increase the geometric filling of the swept area of the propeller, the air load on the propeller and the efficiency of the aircraft engine.

In FIG. 1 shows a front view of the screw (air flow guide conventionally not shown);

In FIG. 2 shows a section along aa;

In FIG. Figure 3 shows the sweep part of the outer shell with propeller blades (the outer shell is conventionally accepted as transparent).

The aircraft propeller (Fig. 1, 2) consists of a multi-blade disk wheel 1 with an outer 7 and an inner 8 shells, mounted on a horizontal shaft 2 (Fig. 2) with a hub 3, a flange 4 and a bolt connection 6. The blades 5 with increasing the angle of attack of the air flow (Fig. 3) is made from a plane of a disk 2 ... 4 mm thick by cutting it along the lines of radii into sectors with the accepted arc length in meters according to the estimated number of blades 5 and around the circumference of the inner shell 8 to the bend line 9 (Fig. 1, 3) (clockwise or counterclockwise) depending from the direction of rotation of the propeller.

By bending a part of the sector plane forward along a line 9 parallel to the sector radius (Fig. 1) towards the air flow, a blade 5 is formed with a flat stiffness rack 11 and a sub-blade window 10 on the disk plane (Fig. 3). The ends of the blades 5 are connected by the outer 7 and inner 8 shells. In the central zone, a removable conical guide 12 of the air flow is attached to the inner shell 8 (Fig. 2).

The main calculation parameter of the disk multi-blade propeller of an airplane is its diameter, for the calculation of which it is necessary to take the initial data: the number of blades (n = 8 ... 24) and the arc length of the sector (l = 0.3 ... 0.5) in meters. The screw diameter in meters is determined by the formula: D = n⋅l: π

So, with the number of blades n = 12 and the arc length of the sector l = 0.4 m, the disk circumference L = n⋅l equal to 4.8 m is determined, dividing it by π = 3.14, we get D = 1.528 m, which provides a sufficiently high calculation accuracy.

The device operates as follows. When the horizontal shaft 2 is rotated with a multi-blade disk propeller from the engine of the aircraft, the incoming air flow at high speed acts on the blades 5, creating horizontal thrust for the aircraft through the sub-blade windows 10 (Fig. 3).

The main feature of the aircraft multi-blade disc propeller is the high geometric filling of the swept area with blades 5 of a large working area, which significantly increases the air load on the propeller and thrust. This helps to reduce engine speed at operating and extreme loads, which reduces its wear, increases reliability, service life and efficiency.

Claims (1)

Aircraft propeller containing a horizontal shaft, a multiblade disk wheel mounted on it with outer and inner shells, between which there are blades with an increasing angle of attack of the air flow, characterized in that the blades are made from the plane of the disk by cutting into sectors with an accepted arc length in meters according to the estimated number of blades with the subsequent bending of part of the sectors along the bending lines towards the air flow during rotation of the propeller from the aircraft engine, while the diameter of the airfoil disk as determined by the product of the circumference of the blade sectors on the arc length in meters.

Images