The method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle (options)

 

(57) Abstract:

The method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle can be used in the aviation industry, such as in gas turbine engines with an additional supply of heat in the afterburner having a jet nozzle with a variable in the direction of the thrust vector. The method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle includes a flow of air and fuel in the afterburner chamber. On the rotation of the nozzle at the walls of the rotary nozzle in the incoming gas stream, located on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, increase the cost of air and fuel. This method will reduce the temperature of the walls of the nozzle to a safe level from the point of view of their own health (no burnouts, providing strength indicators, and so on), and from the point of view of their health in the mechanism of the nozzle (the absence of zakonov and so on). 2 S. and 6 C. p. F.-ly, 3 ill.

The invention relates to a turbojet engine with an additional supply of heat in the afterburner and rotary jet the gate nozzle, including the supply of air and fuel in the afterburner chamber [1].

In this engine is relatively simple and well-known solutions can provide reliable cooling jet nozzle for all modes of engine operation.

The closest solution known is the method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle, including the supply of air and fuel in the afterburner chamber and the cooling of the walls of the afterburner and swivel nozzle by blowing cooling air their outer surfaces [2].

However, when the rotation of the specified jet nozzle cooling it rapidly deteriorating. This deterioration can be attributed to several reasons.

First, when the rotation of the nozzle is greatly increased heat flow of the gases coming from the afterburners on the walls of the nozzle located on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine. In this place the nozzle instead of the current gas flow along the walls there is a partial charge of the flow on the wall of the nozzle, so that the flow is partially inhibited and increases the heat transfer from the gas to the walls.

Secondly, because casting the si nozzle from the longitudinal axis of the engine, deteriorating working and the cooling nozzle. This is due to the fact that due to deceleration of the gas stream when it is turned in the nozzle disposable pressure drop of the cooling air which flows around the inner surface of the walls of the nozzles arranged on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine decreases. This immediately causes a reduced flow of cooling air and, as a consequence, the decrease in heat removal from the walls of the nozzle in this place.

Thus, there are at least two major reasons for deterioration of cooling this place nozzle and increase its temperature. The very increase in the temperature of the place in addition to burnout walls can lead to warping and, as a consequence, even jamming of the mechanism of rotation of the nozzle, which is unacceptable from the point of view of flight safety, highly maneuverable aircraft.

The objective of the invention is by turning the nozzle to reduce the temperature of its walls to a safe level from the point of view of its own health (no burnouts, providing strength characteristics, and so on), and from the point of view of its performance in the mechanism of the nozzle (the absence of zakonov and so on ) and so on who, s the longitudinal axis of the nozzle from the longitudinal axis of the engine.

This task is achieved in that in the method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle, including the supply of air and fuel in the afterburner chamber in command for rotating the nozzle in the oncoming gas flow at the walls rotary nozzle increase the cost of air and fuel. It is reached by different methods, namely:

a) the fact that in the area of the walls in the afterburner reduce the flow rate of the supplied fuel;

b) the fact that the cross-sectional afterburners redistribute the flow rate supplied to it of fuel, which, in addition to reducing the fuel consumption of the walls increase in other zones afterburners;

C) the fact that in the area of the walls of the afterburner serves the additional air.

New here is that the command to rotate the nozzle in the gas flow at the walls rotary nozzle increase the cost of air and fuel. To do this:

a) in the area of the walls in the afterburner reduce the flow rate of the supplied fuel, while still on the cross section afterburners redistribute the flow rate supplied to it of fuel, which, in addition to reducing the fuel consumption of the walls, respectively politely the air.

This task can be achieved and the fact that in the method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle, including the supply of air and fuel in the afterburner chamber in command for rotating the nozzle in the oncoming gas flow at the walls rotary nozzles arranged on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, increase the cost of air and fuel. It is reached by different methods, namely:

a) in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, reduce fuel;

b) are cross-sectional afterburners redistribute the flow rate supplied to it of fuel, which, in addition to reducing the fuel consumption from the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, respectively uvelichivyut it in other areas afterburners;

C) in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, serves the cooling air.

New here is that the command to rotate the nozzle in the oncoming gas flow at the walls psi engine increase the ratio of costs of air and fuel. To do this:

a) in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, reduce fuel;

b) while still on the cross treatment afterburners redistribute the flow rate supplied to it of fuel, which, in addition to reducing the fuel consumption from the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, respectively, increase in other zones afterburners:

C) in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, serves the cooling air.

Increasing command to rotate the nozzle, the cost of air and fuel at the walls afterburners, we reduces the temperature of the gas stream at the walls swivel nozzle that allows you to keep on the walls of the rotary nozzle temperature not higher than the one that was there before the command to rotate the nozzle. The simplest solution here is simply the reduction of fuel in the afterburner at her walls. But this is not always acceptable, as this leads to a corresponding reduction of engine thrust. It is therefore more efficient walls afterburners compensated by its redistribution towards the Central zone of the nozzle. The same task, almost no loss of traction, can be solved by filing in the area of the walls of the nozzle additional air taken from the corresponding pressure stage of the compressor. This additional air remains in the running of the engine, i.e. the loss for the engine as a whole from such filing insignificant.

If the command to rotate the nozzle increase in the ratio of costs of air and fuel to run only from the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, in addition to the main task - namely, reducing the temperature of the walls of the nozzle to a safe level, you can achieve and additional tasks - namely, reducing the circumferential non-uniformity of the temperature of the nozzle. To do this:

a) in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine and reduce the fuel supply, while the cross-sectional afterburners redistribute the flow rate supplied to it of fuel, which, in addition to reducing the fuel consumption from the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, respectively, increase in other zones afterburners;

b) f is with the cooling air.

This solution allows to reduce the temperature of the walls of the nozzle in the area of the nozzle, where the maximum exposure to heat incoming gas stream on the wall of the rotary nozzle and, thus, reduce the ring temperature irregularity arising from the rotation of the jet nozzle.

It should be noted that due to the fact that we act on the incoming gas stream in the most optimal location of the engine, the impact on the value of minimum, which allows the engine almost to keep all their options, such as save the amount of engine thrust.

The prior art has identified solutions that binds a command to rotate the nozzle with the process of increasing the cost ratio of air and fuel in the oncoming gas flow at the walls of the rotary nozzle.

The prior art is not identified, solutions, binding the command to rotate the nozzle with the process of increasing the cost ratio of air and fuel in the oncoming gas flow at the walls rotary nozzles arranged on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine.

Thus, our proposed solution meets criteriology and rotary jet nozzle, implements the proposed method of its work;

in Fig. 2 shows a cross-section on the additional fuel manifold in the afterburner;

in Fig. 3 shows a cross section through an air manifold in the afterburner.

Turbojet engine includes a compressor 1, a main combustion chamber 2, a turbine 3, afterburning chamber 4 with the fuel reservoir 5 and the rotary jet nozzle 6 with a cooled wall 7, having the ability to rotate up and down around a horizontal axis 8. In the afterburner 6 installed additional fuel manifold 9, with the upper 10 and lower 11 sections, connected by pipes 12 and 13 through the switching valve 14 from the supply line to the afterburner fuel 15. Switching valve 14 associated with the command valve 16, working on the rotation of the nozzle. Also in the afterburner 6 installed air manifold 17 having a top 18 and bottom 19 of the sections, connected by pipes 20 and 21 through the switching valve 22 and line 23 to the compressor 1. Switching valve 22 associated with the command valve 16, working on the rotation of the nozzle. In the manifold 9 holes 24 supply of afterburner fuel and manifold 17 - hole 25 for supplying additionally the second chamber from the air compressor 1 through the main combustion chamber 2 and the turbine 3 and afterburner fuel through the collector 5. On the rotation of the nozzle 6 in the incoming gas flow to the wall 7 of the rotary nozzle increase the cost of air and fuel. To do this, the command signal from the valve 16 by means of a switching valve 14 to shut off the supply of afterburner fuel additional fuel manifold 9 and / or by a signal from the command valve 16 by means of a switching valve 22 include the submission of additional air from the compressor 1 through the piping 23, 20 and 21 and the holes 25 of the air manifold 17 to the walls of the afterburner chamber 4. The additional fuel from the fuel manifold by means of a switching valve 14 be transferred to other collector 5 located closer to the Central zone of the afterburner chamber 4.

Increasing command to rotate the nozzle, the cost of air and fuel at the walls afterburners, we reduce the temperature of the gas stream at the walls swivel nozzle that allows you to keep on the walls of the rotary nozzle temperature not higher than what was there before the command to rotate the nozzle. After canceling a command to rotate the nozzle, the cost of air and fuel lead in the state, which was in the afterburner to this command.

The way to implement and code the combustion chamber 2 and the turbine 3 and afterburner fuel through the collector 5. Command to rotate the nozzle 6 "down in the gas flow at the walls 7 of the rotary nozzle located above the longitudinal axis of the engine, increase the cost of air and fuel. To do this, the command signal from the valve 16 by means of a switching valve 14 to shut off the supply of afterburner fuel section 10 additional fuel manifold 9 and / or by a signal from the command valve 16 by means of a switching valve 22 include the submission of additional air from the compressor 1 through the piping 23, 20 and 21 and the holes 25 section 18 of the air manifold 17 to the walls of the afterburner chamber 4 located at the top. Fuel from section 10 additional fuel reservoir by means of a switching valve 14 be transferred to other collectors 5 located closer to the Central zone of the afterburner chamber 4.

This solution allows to reduce the temperature of the walls of the nozzle in the area of the nozzle, where the maximum exposure to heat incoming gas stream on the wall of the rotary nozzle and, thus, reduce the ring temperature irregularity arising from the rotation of the jet nozzle. It should be noted that due to the fact that we act on the incoming gas pately almost to keep all their options, for example, to keep the thrust of the engine. After canceling a command to rotate the nozzle, the cost of air and fuel lead in the state, which was in the afterburner to this command.

As can be seen from the description, the method implemented using the well-known in the industry devices. Therefore, the present invention corresponds to the criterion of industrial applicability.

Sources of information:

1. U.S. patent N 4203286, NCI 60/266, publ. 1980 - similar.

2. U.S. patent N 4274593, NCI 239/265.35, publ. 1981 - the prototype.

1. The method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle, including the supply of air and fuel in the afterburner chamber, characterized in that on the rotation of the nozzle at the walls of the rotary nozzle in the incoming gas stream to increase the ratio of costs of air and fuel.

2. Way p. 1, characterized in that in the area of the walls in the afterburner reduce the flow rate of the supplied fuel.

3. The way PP.1 and 2, characterized in that the cross-sectional afterburners redistribute the flow rate supplied to it of fuel, which in addition to reducing the fuel consumption of stea in the area of the walls of the afterburner serves the additional air.

5. The method of operation of a turbojet engine with afterburner chamber and rotary jet nozzle, including the supply of air and fuel in the afterburner chamber, characterized in that on the rotation of the nozzle in the oncoming gas flow at the walls rotary nozzles arranged on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, increase the cost of air and fuel.

6. The method works on p. 5, characterized in that in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine and reduce the fuel supply.

7. The way PP.5 and 6, characterized in that the cross-sectional afterburners redistribute the flow rate supplied to it of fuel, which in addition to reducing the fuel consumption from the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis of the engine, increase it in other areas of the afterburner.

8. The method works on p. 5, characterized in that in the afterburner on the side opposite to the deviation of the longitudinal axis of the nozzle from the longitudinal axis, serves the cooling air.

 

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