RU2757798C1 - Engine nozzle with mass expiration - Google Patents

Abstract

FIELD: engine production.

SUBSTANCE: invention relates to engine production, in particular to the method for operation and the design of nozzles with the expiration of masses for various engines. The nozzle of the engine with the expiration of the masses contains a narrow and wide part. The nozzle on the narrow side has inlet openings leading to the channels for supplying the flow of liquid or gas, which lead to spiral grooves inside the nozzle. At the same time, the winding pitch of the turns of the spiral grooves is constantly increasing, as the nozzle diameter increases. The angle of inclination of the turns relative to the horizon is the same, along the entire length of the nozzle grooves.

EFFECT: use of the invention makes it possible to increase the thrust of a jet, turbojet or water jet engine, as well as a screw propeller by using the centrifugal force of gas or liquid flows along spiral grooves inside the nozzle.

1 cl, 5 dwg

Description

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

The invention is based on a special method of operation and the device of a Laval nozzle, which is a gas channel of a special profile (having a narrowing at the entrance of gases, and at the exit of expansion) for changing 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 engines. Efficient nozzles of modern rocket engines are profiled based on gas-dynamic calculations.

(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% D1% 8F #)

Known is a rocket engine nozzle containing an expanding supersonic part, the internal heat protection of which is made by spiral winding of a reinforcing tape. The internal heat shield of the supersonic part of the nozzle contains a reinforcing fiber, for example, carbon or silica, and a binder, for example, of phenol-formaldehyde resin. In the process of binder ablation, the internal heat shield forms a spiral roughness protruding into a supersonic gas flow from a reinforcing fiber with a height of not less than a quarter of the thickness of the laminar sublayer (RU 2211939, IPC F02K 9/97, publ. 09/10/2003, bull. No. 25).

The problem to be solved by the known invention is to impart rotation to the rocket relative to the longitudinal axis of the nozzle, which ensures constant rotation during the entire operation time of the engine and does not cause increased losses of specific impulse. The task is partially completed. The rocket will rotate, since there is a spiral in the inner part, but the loss of specific impulse, pressure loss of the gas flow, and therefore the gas flow rate will also be. To this will be added a change in the direction of the gas flow, in the direction of decreasing the angle relative to the plane on which the wide part of the nozzle stands. Explanations: in the first case, there is a change in flow in the range of 0 ° to 90 ° with respect to the horizon (appendix). The centrifugal force of the flow is directed upwards at an angle of 45 ° to the horizon. In the second case, the flow changes in the range from 90 ° to 0 ° to the horizon. The centrifugal force of the flow is directed downward at an angle of 45 ° to the horizon. Since the nozzle expands towards the outlet of gases that rotate in a spiral, the angle of inclination of the spiral turns is constantly decreasing. Consequently, the centrifugal force of the gas flow will be directed towards the expansion. And since the flow from the expansion side will abut against the next turn, the centrifugal force of the flow will be transmitted to the nozzle and pull it towards the expansion. In the patent 2211939 it is said about the presence of spiral turns, which reduces the pressure for organizing the flow. The gas flow rate will decrease. The flow will follow the path of least resistance, past the spiral, as usual, with the direct exit of gases from the combustion chamber. In addition, the nozzle, inside, contains wound spiral ribbons of reinforcing material, which are destroyed under the action of high-temperature and high-speed gas flow that occurs during engine operation.

In a classic jet engine, the exhaust jet is very energetic and can be used more efficiently. In a spiral nozzle, part of the flow energy is transferred to the nozzle. If the flow rate increases in a classical nozzle, then it can be increased and left constant or decreased, at infinity to zero. Also, if you make a nozzle in the form of a "ballet skirt", then the exhaust gases will come out horizontally.

The task facing the author is to increase the thrust of a jet, turbojet or water jet engine, as well as a propeller.

The problem is solved by using the centrifugal force of gas or liquid flows along spiral grooves, with an increase in the pitch of the spiral turns inside the nozzle.

The essence of the invention is the possibility of increasing the thrust of a jet, turbojet or water-jet engine, as well as a screw propeller due to the use of the centrifugal force of gas or liquid flows along the spiral grooves inside the nozzle, the pitch of the turns of which is constantly increasing, compensating and making the angle of inclination of the spiral turns constant.

The nozzle consists of:

1 - inlet to the liquid or gas flow channel

2 - outlet from the liquid or gas flow supply channel

3 - channel for supplying liquid or gas flow

4 - spiral grooves (grooves)

5 - the narrow part of the nozzle cone

6 - wide part of the nozzle cone

The device is a nozzle, with a narrow part 5 of which there are inlet openings 1 leading to the channels 3 for supplying a flow of liquid or gas; channels 3 lead into helical grooves 4 inside the nozzle. To ensure the smallest angle of entry of liquid or gases into the spiral grooves 4, a minimum presence of two channels 3 is required. Since the nozzle diameter increases, it is necessary to increase the pitch between the turns of the spiral grooves 4 in order to compensate and make the angle of inclination of the spiral turns constant, which is explained by the formula: Hsp = d (h) * tan (ϕ) * 2 (see below for an explanation of the formula). The number and volume of spiral grooves 4 are multiples of the number of channels 3 and can increase as the pitch of the spiral increases.

The pitch of the turns of the spiral grooves 4 of the nozzle can be different, depending on the type and purpose of the engine, but the angle of inclination of the turns of the grooves 4 relative to the horizon is the same, along the entire length of the grooves 4 of the nozzle. The depth of the grooves 4 depends on the number of kilograms of jet per second.

Formula for calculating the pitch of the turns of the spiral grooves inside the nozzle:

HSP = d (h) * tan (ϕ) * 2

Hsp - the pitch of the turns of the spiral of the grooves, the straight line passing through the points (0; d1) and the point (h; d0)

h is the height of the nozzle (vertical);

d (1) is the final diameter of the nozzle;

d (0) is the initial nozzle diameter;

d (h) - function of the diameter over the height of the nozzle;

ϕ is the angle of inclination of the turns of the spiral of the grooves.

FIG. 1 shows the nozzle in section (side view).

FIG. 2 shows the nozzle (top view).

FIG. 3 schematically shows an example of the use of the inventive nozzle with a screw propeller.

FIG. 4 schematically shows an example of the arrangement of the helical groove inside the nozzle.

FIG. 5 schematically shows the direction of movement of the vortex flows inside the nozzle and the angle of inclination of the spiral grooves.

FIG. 2 shows a nozzle that has two channels that turn into spiral grooves. Subsequently, the number of grooves increases evenly. FIG. 1 shows the size of the grooves, which can increase in volume. So that the gas or liquid, which (which) does not fit into the grooves in volume and go past the grooves, can fit in them.

The work of the claimed invention can be shown on the example of a jet engine Laval nozzle.

During the operation of the jet engine, combustion products (gases) are formed in the combustion chamber (gases), coming out from the side of the wide part 6 of the nozzle. The grooves 4 inside the nozzle are acted upon by the centrifugal force of flows directed to the nozzle walls, with a zero angle to the bottom of the nozzle cone. The vortex flows of gases, passing through the channel 3, continue to move along the spiral grooves 4, creating pressure inside the nozzle with their centrifugal force (Fig. 5). From interaction with the inner walls of the nozzle, the gas flow is twisted in the direction of winding spiral grooves 4 (from top to bottom). As a result, the nozzle body acquires a force towards a smaller diameter (within 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. And so the nozzle cone will receive the centrifugal force of the flow F directed at 90 ° 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 itself forming the cone is also at an angle to the vertical, this is cos (ϕ).

The movement of gas flows in a spiral, entails a moment of forces arising around the symmetrical axis of the nozzle, which causes the rotation of the nozzle, depending on which direction the spiral grooves are twisted 4. For the balanced movement of the rocket, the second nozzle must have spiral grooves 4, twisted in the opposite side, from this we can conclude that to compensate for the rotation of the nozzles, you need an even number of them.

The engine thrust will increase from 2 to 10 times.

The inventive nozzle can operate not only from a gas flow generated as a result of the operation of a jet or turbojet engine, but also from a flow of liquid (water) forced, for example, by the propellers of the floating vehicle. In this case, the screw must be located inside the nozzle near its narrow part 5, which serves as a water intake. During the operation of the propeller, water flows will be created, coming out from the side of the wide part 6 of the nozzle cone, with a large diameter, and the nozzle itself, in addition, performs the function of a cone-shaped casing attached to the ship's hull (Fig. 3). In this case, the nozzle can consist of two parts (i.e. cut in half, along the axis of the nozzle) and contract and align into a single whole.

As in the description of the previous example with gas flows, in this case, the grooves 4 inside the nozzle will be acted upon by the centrifugal force of water flows directed to the nozzle walls, with a zero angle to the bottom of the nozzle cone. The vortex flows of water passing through the channel 3 continue to move along the spiral grooves 4, creating pressure inside the nozzle with their centrifugal force (Fig. 5). From interaction with the inner walls of the nozzle, the water flow is twisted in the direction of winding spiral grooves 4, which are directed towards the water flow created by the movement of the screw. As a result, the nozzle body acquires a force towards a smaller diameter (within the framework of Newton's second law), which can be expressed in an increase in the propeller thrust.

If we add turns to the nozzle spiral, then the ratio will increase by that much, but we must take into account the pressure loss for each turn.

Calculation formulas

Formula for calculating the thrust of the inventive nozzle:

T1 = (m * v ² * sin (ϕ) * cos (ϕ) / (R _a + R _b ) / 2 / g

T1 - thrust of the inventive nozzle

m - mass of gases or liquids constantly in the nozzle

v is the flow rate of gases or liquids (m / sec.)

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

R - changing radius of the nozzle from R _a to R _b

g - acceleration of gravity for the Earth

Formula for calculating the thrust of a jet engine with a Laval nozzle:

T2 = ((dm / t) * v / g - thrust of a conventional jet engine without a Laval nozzle

T2 - thrust of a jet engine with a Laval nozzle

K = T1 / T2 - ratio coefficient

dm / t - change in the mass of gas flows per unit of time

v is the gas flow rate taking into account the Laval nozzle (m / sec.)

g - acceleration of gravity for the Earth

The centrifugal force of flows of liquids or gases can be calculated by the formula:

F = m * (v ² / (R _a + R _b ) / 2) * sin (ϕ) * cos (ϕ).

m - mass of gases or liquids constantly in the nozzle

v is the flow rate of gases or liquids (m / sec.)

R - changing radius of the nozzle from R _a to R _b

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

By changing the shape of the cone from a bell with a narrowing at the bottom to a "ballet skirt", it is possible to obtain the exit of gases from the cone from 90 ° to 0 ° with respect to the bottom of the cone.

Now, the above described invention can be applied in jet engines, instead of Laval nozzles, as well as with screw, water propellers and water cannons.

If the thrust is n times greater, then:

1. Less fuel is needed.

2. There is more payload.

3. The engine is cheaper.

4. The speed of the aircraft or craft is greater.

Thus, the task assigned to the author has been completed.

Claims (1)

An engine nozzle with an outflow of masses, containing a narrow and wide part, characterized in that the nozzle on the side of the narrow part has inlets leading to the channels for supplying a liquid or gas flow that lead to spiral grooves inside the nozzle, while the pitch of the turns of the spiral grooves is constantly increasing , as the diameter of the nozzle increases, and the angle of inclination of the turns relative to the horizon is made the same along the entire length of the nozzle grooves.

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