RU2778959C1 - Nozzle with mass flow and forward flow - Google Patents

Abstract

FIELD: engine building.

SUBSTANCE: invention relates to engine building, in particular to the method for operation and the device of nozzles with the expiration of masses for various engines. The device is a nozzle, which is conditionally divided into two parts (determining its geometric shape): conical part 1, with a wall inclination angle of 45°, turning into a cylindrical part 2. Inside the nozzle, along its entire length, there are spiral grooves 3, at the nozzle inlet, having an angle of inclination from 95 to 130° with respect to the axis of the nozzle (above the axis), while the angle of inclination of the grooves 3 is constant along the entire length of the nozzle. The number of helical grooves 3 is a multiple of two; the number and volume of the grooves 3 may increase as the nozzle inlet diameter increases. Spiral grooves 3 from the conical part 1 pass into the cylindrical part 2 of the nozzle, while the grooves 3, in the cylindrical part 2, at the outlet of the nozzle, have an inclination of 0° relative to the axis of the nozzle. The number of grooves 3 in the cylindrical 2 part of the nozzle must be a multiple of four.

EFFECT: invention provides an increase in traction and a decrease in noise.

1 cl, 5 dwg

Description

The invention relates to engine building, in particular to the method of operation and the device of nozzles with the expiration of masses for various engines.

A Laval nozzle is known, which is a gas channel of a special profile (having a narrowing at the inlet of gases, and an expansion at the outlet) to change the speed of the gas flow passing through it. It is widely used on some types of steam turbines and is an important part of modern rocket engines and supersonic jet aircraft and water engines. Efficient nozzles of modern rocket engines are profiled on the basis of gas-dynamic calculations and the cylindrical part.

(https://ru.wikipedia.org/wiki/%D0%A1%D0%BE%D0%BF%D0%BB%D0%BE%D0%9B%D 0%B0%D0%B2%D0%B0 %D0%BB%D 1%8F#)

A rocket engine nozzle is known, containing an expanding supersonic part, the internal thermal protection of which is made by a spiral winding of a reinforcing tape. The internal thermal protection of the supersonic part of the nozzle contains a reinforcing fiber, such as carbon or silica, and a binder, such as phenol-formaldehyde resin. In the process of ablation of the binder, the internal thermal protection forms a helical and protruding into the supersonic gas flow roughness from the reinforcing fiber with a height of at least a quarter of the thickness of the laminar sublayer (RU 2211939, IPC F02K 9/97, publ. 10.09.2003, bull. No. 25).

The closest analogue is the engine nozzle with the expiration of masses, containing a narrow and a wide part. The nozzle on the side of the narrow part has inlets leading to channels for supplying a liquid or gas flow, which lead to spiral grooves inside the nozzle. In this case, the pitch of the spiral groove turns is constantly increased, as the diameter of the nozzle increases, to maintain the angle of the grooves. The angle of inclination of the turns relative to the horizon is the same along the entire length of the nozzle grooves (RU 2757789, IPC F02K 9/97, publ. 21.10.2021 Bull. No. 30).

All existing screw propellers create sound vibrations. Sound vibrations are created by the screw itself and the cone by the spiraling movement of air or water behind it. On a propeller, they form behind a low-pressure area, a turbulent flow of air. Behind the screw, the flow, a spiral cone along the flow, diverges in different directions, creating turbulent eddies along the perimeter. They then create a sound whose frequency depends on the speed of the screw. The thrust of such a propeller is created by the propeller itself (wing lift). Screw propellers are used in airplanes, helicopters, quadrocopters and other devices. This also includes jet and turbojet engines.

Noise arises from the divergence of the flow along the conical profile, rotating flows of gases or water, as well as from the propeller (Appendix No. 1). Noise can be reduced by arranging direct outgoing gas or liquid flows, because in this case, the outgoing flow does not have a rotational velocity component.

The objective of the invention is to increase the thrust of the engine and reduce its noise.

The present invention makes it possible to increase the thrust of propeller, turboprop, jet propulsion, due to the use of the force of rotation of the gas or liquid flow and to reduce the sound impact on the surrounding space, by changing the trajectory of the gas or liquid flow from a spirally diverging cone to direct movement.

The increase in thrust is provided by the conical and cylindrical parts of the nozzle, with helical (semicircular in profile) grooves inside the conical and cylindrical parts.

The essence of the invention is the possibility of increasing the thrust of screw, turboprop, jet propulsion, due to the use of the force of rotation of the gas or liquid flow and reducing the sound impact on the environment, thanks to the device of the inventive nozzle, which allows changing the trajectory of the gas or liquid flow from a spirally divergent cone to a straight one. movement.

The device is a nozzle which is conditionally divided into two parts (determining its geometric shape): 1 conical part, with a wall inclination angle of 45°, turning into a cylindrical 2. Inside the nozzle, along its entire length, there are spiral grooves 3, at the inlet nozzles having an angle of inclination from 95° to 130° with respect to the axis of the nozzle (above the axis), while the angle of inclination of the grooves 3 is constant along the entire length of the nozzle. The number of helical grooves 3 is a multiple of two; the number and volume of the grooves 3 may increase as the nozzle inlet diameter increases. Spiral grooves 3 from the conical part 1 pass into the cylindrical part 2 of the nozzle, while the grooves 3, in the cylindrical part 2, at the outlet of the nozzle, have an inclination of 0° relative to the axis of the nozzle. The number of grooves 3 in the cylindrical 2 part of the nozzle must be a multiple of four.

In FIG. 1 shows the image of a spiral in 3 coordinates.

In FIG. 2 shows the direction of movement of gas or liquid flows in the conical part of the nozzle.

In FIG. 3 shows the development of the inner side of the cylindrical part of the nozzle.

In FIG. 4 shows a nozzle for a jet engine (direction of gas flow, shown schematically by arrows).

In FIG. 5 shows a nozzle for a screw propeller (the direction of the flow of water or air, schematically shown by arrows).

The operation of the inventive nozzle can be shown on the example of use on a jet engine (Fig. 4):

During the operation of a jet engine, combustion products (gases) are formed in the combustion chamber "k", which are fed directly into the grooves 3 of the conical 1 part of the nozzle. The grooves 3 inside the nozzle are affected by the centrifugal force of the flows directed to the walls of the nozzle, with an angle of inclination from 95° to 130° with respect to the axis of the nozzle (above the axis). Vortex flows of gases move along spiral grooves 3, creating pressure inside the nozzle with their centrifugal force. From the interaction with the inner walls of the nozzle, the gas flow twists in the direction of winding the helical grooves 3 (from top to bottom). As a result, the body of the nozzle acquires a force in the direction of a smaller diameter (in the framework of Newton's second law), which can be expressed in an increase in the thrust of the jet engine to which the nozzle is attached. Thus, the conical 1 part of the nozzle will receive the centrifugal flow force F directed at 45° relative to the axis of the conical 1 part of the nozzle. Since the force F rests against the conical 1 part from the inside at an angle "ϕ", then in the formula it is "sin (ϕ)", and the wall itself forming a cone is also at an angle to the vertical, this is cos (ϕp).

At the outlet of the conical 1 part of the nozzle, the gas flows pass into the cylindrical part 2, in which the trajectory of the gas flow changes from a spiral diverging cone to a direct movement, while the vortex gas flows also continue to move along the spiral grooves 3, creating pressure inside nozzles with their centrifugal force. From the interaction with the inner walls of the nozzle, the gas flow continues to twist in the direction of winding the helical grooves 3 (from the combustion chamber "to" to the nozzle outlet). Moreover, the spiral grooves 3 change the angle of flow direction from the angle of inclination in the conical 1 part to 0°, relative to the axis of the nozzle. With this movement, the flow is a mass that moves along the top 1/4 of the circle, and the centrifugal force from this is directed at 45°, relative to the axis of the nozzle. As a result, the nozzle body acquires a force towards the combustion chamber "to" at an angle of 45 °, therefore, in the formula "sin (ϕ)" (in the framework of Newton's second law), which can be expressed in an increase in the thrust of the jet engine to which the nozzle is attached.

The inventive nozzle can operate not only from the gas flow generated as a result of the operation of a jet or turbojet engine, but also from the flow of liquid (water) or air forcibly supplied, for example, by propellers "in" a floating or aircraft (Fig. 5). In this case, the screw "c" should be located inside the conical 1 part of the nozzle, near its narrow part, which performs the function of a water intake (air intake).

During the operation of the propeller "c", streams of water or air will be created, coming out from the side of the cylindrical 2 part of the nozzle, while the nozzle, in addition, performs the function of a casing attached, for example, to the ship's hull. In this case, the nozzle may consist of two parts (i.e., cut in half, along the axis of the nozzle), be pulled together and combined into a single whole.

As in the description of the previous example with gas flows, in this case, the grooves inside the nozzle will be affected by the centrifugal force of water or air flows directed to the walls of the nozzle, with an angle of inclination from 95° to 130° with respect to the nozzle axis (above the axis ). Vortex flows of water or air move along spiral grooves, creating pressure inside the nozzle with their centrifugal force. From the interaction with the inner walls of the nozzle, the water or air flow twists in the direction of the winding of the spiral grooves, which are directed towards the flow created by the movement of the screw. As a result, the nozzle body acquires a force towards a smaller diameter (in the framework of Newton's second law), which can be expressed in an increase in the propeller thrust. And so the conical part of the nozzle will receive the centrifugal flow force F directed at 45 ° relative to the axis of the nozzle cone. Since the force F rests against the cone from the inside at an angle "ϕ", then in the formula it is "sin (ϕ)", and the wall forming the cone itself is also at an angle to the vertical, this is cos (ϕ).

At the outlet of the conical 1 part of the nozzle, the flows pass into the cylindrical 2 part, in which the flow trajectory changes from a spiral diverging cone to a direct movement, while the vortex flows of water or air also continue to move along the spiral grooves 3, creating pressure inside nozzles with their centrifugal force. From the interaction with the inner walls of the nozzle, the flow continues to twist in the direction of winding the helical grooves 3 to the nozzle outlet. Moreover, the helical grooves change the angle of the flow direction from the angle of inclination in the conical part to 0°, relative to the axis of the nozzle. With this movement, the flow is a mass that moves along the top 1/4 of the circle, and the centrifugal force from this is directed at 45°, relative to the axis of the nozzle. As a result, the body of the nozzle acquires a force towards the screw "b" at an angle of 45 °, therefore, in the formula "sin (ϕ)" (within the framework of Newton's second law), which can be expressed in an increase in the thrust of the propeller to which the nozzle is attached.

The resulting force of the nozzle increases the speed of the outgoing streams, and hence the amount of mass per unit time.

The walls of the conical 1 part of the nozzle are made with an inclination angle of 45°. Since the centrifugal force of the flow rests and acts on the nozzle at 45°, and the inclination of the nozzle, with respect to its axis, is also 45°. Therefore, sin(ϕ)*cos(ϕ) appears in the nozzle thrust calculation formula, an angle of 45° is optimal.

Formulas for calculations

The formula for calculating the thrust of the proposed nozzle:

Τ1 = (m*v ² * sin(ϕ)*cos(ϕ)/(Ra+Rb)/2/ g

T1 - thrust of the inventive nozzle

m - mass of gases permanently located in the nozzle

v - flow rate of gases or liquids (m/s)

g is the free fall acceleration for the Earth

R - changing radius of the center of the turns of the nozzle from Ra to Rb

ϕ - the angle of inclination of the turns of the spiral grooves

The centrifugal force of gas or liquid flows can be calculated by the formula:

F = m*(v ² /(Ra+Rb)/2)*sin(ϕ)*cos(ϕ)

m - mass of gases or liquids permanently located in the nozzle

v - flow rate of gases or liquids (m/s)

R - changing nozzle radius from Ra to Rb

ϕ - the angle of inclination of the turns of the spiral grooves

The mathematical model of the spiral (Fig. 1) can be described by an equation in parametric form, given in three coordinates Χ, Υ, Ζ:

X = R*cos(w*t);

Υ = R*sin(w*t);

Z = A*t;

R is the radius of the spiral;

w - frequency;

t - time;

A - spiral pitch;

The z axis is the helix axis. The first derivative with respect to Z is the speed ΔZ/dt = A, the second derivative with respect to Z is the acceleration ΔΔZ/dt = 0. In order for ΔΔZ/dt not to be equal to zero, it is necessary that the velocity of a point moving in a spiral be a function of A = F(t). If this function is positive, the interval [0; ∞], then the pitch of the helix increases, respectively, and the angle of inclination of the helix changes. If A \u003d 0, then we have a circle and the angle of inclination of the coil will be perpendicular to the Z axis, that is, 90 °. And if A \u003d ∞, then we have a straight line and the inclination of the spiral turns is 0 ° to the Z axis. Or the angles are vice versa, if considered in relation to the base of the nozzle.

Decision and obtaining a causal relationship between the proposed design and the technical result (Appendix No. 2).

According to the mathematical model of the spiral, in order for the spiral to have acceleration, it is necessary to change the angle of inclination of the spiral from 90 ° to 0 ° with respect to the axis of the spiral (upper part).

часть окружности меняет угол касательной к ней, в таком интервале. Соответственно была взята

часть траектории по окружности и свернута в цилиндр по левому и правому краю развертки, при этом траектория витков совпадает с разных сторон (лево и право).It has been suggested that only

part of the circle changes the angle of the tangent to it, in such an interval. Accordingly, it was taken

part of the trajectory is circular and rolled into a cylinder along the left and right edges of the development, while the trajectory of the turns coincides on different sides (left and right).

окружности (приложение №3).For calculations, it is enough to use the well-known calculation of the centrifugal force that occurs when a mass moves along

circles (Appendix No. 3).

окружности. При таком движении, поток представляет собой массу, которая движется по 1/4 верхней части круга, и центробежная сила от этого, направлена под 45°,относительно оси сопла.The grooves that direct the flow follow a strictly trajectory

circles. With this movement, the flow is a mass that moves along the top 1/4 of the circle, and the centrifugal force from this is directed at 45°, relative to the axis of the nozzle.

F \u003d m * v ² / R * sin (45 °), where

m - The mass of the flow, constantly located on the site;

v - flow rate;

R - The radius of the circle of the trajectory (path) of the section of the flow;

At the nozzle inlet, the angle of inclination of the grooves is the same as at the outlet of the conical part of the nozzle, and at the outlet it is 0° to the nozzle axis. If we take the nozzle sweep as a basis and calculate the nozzle according to the formula, then it is clear that the angle of inclination of the grooves that direct the flow should change, as in a circle. Only by changing the angle of inclination of the grooves guiding the flow is the technical result calculated by the formula possible.

The parametric equation of the spiral is known:

x = cos(x*t);

y = sin(y*t);

z = z*t

The first derivative from "z" to "t" gives us the speed, the second acceleration, z is the pitch of the spiral (from coil to coil), the speed is also calculated from coil to coil.

The angle of inclination of the helix turns is calculated as tg(α) = c/(b/4), where

α - the angle of inclination of the spiral turns

c - spiral radius

b - helix pitch

This shows that if the pitch or radius of the spiral does not change, then the angle of inclination of the spiral does not change.

The acceleration of the spiral, with a constant pitch, is zero. According to Newton's second law F(force) = m*a, where

m is the mass of the flow in the cylinder;

a - acceleration of the system;

If a = 0, then F = 0.

We change the helix angle to 0°, relative to the nozzle axis.

It can be seen that z is a variable and the acceleration of the system is not equal to zero, respectively, and the force is not equal to zero.

Let v - flow rate, v1 - final flow rate, v0 - initial flow rate, L - length of the flow path L = 2*π*h/4 = π*h/2, where h is the height of the cylindrical part, then the time t passed flow along the path t \u003d L / (v1-v0), and the acceleration will be equal to a \u003d (v1-v0) / t, since our speed along the spiral changes from v0 to v1.

According to Newton's second law F (force) \u003d m * a,

The final formula for the mathematical model:

F(force) \u003d 2 * m * (v1-v0) ² / π * h

In an ordinary spiral, the initial and final speeds are the same, and v1-v0 = 0, v1 = v*cos(ϕ1), v0 = v*cos(ϕ0), but is determined by the flow rate from the conical part and the groove angle ϕ1 = ϕ0, t .to. the angle of the grooves is the same as the angle of the grooves of the conical part and the same at the outlet of the cylindrical part. Accordingly, both acceleration and force will be equal to zero. In our helix ϕ0 > ϕ1, where ϕ is the angle of inclination of the grooves relative to the nozzle axis. ϕ0 - from 95° to 130°, ϕ1 - 0°, relative to the nozzle axis.

The use of the proposed device allows to increase the thrust and reduce the noise of a jet, turbojet engine, as well as a propeller water or air propulsion.

The task assigned to the authors has been completed.

Claims (1)

Nozzle with outflow of masses and straight outflow, consisting of a conical part, inside which there are spiral grooves, characterized in that the grooves go with an angle of inclination of 95-130 ° with respect to the axis of the nozzle, the angle of inclination of which is constant along the entire length of the nozzle, while conical part of the nozzle passes into a cylindrical part, inside which there are also spiral grooves, which at the nozzle exit have an inclination of 0° relative to the nozzle axis.

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