Turbojet engine

 

(57) Abstract:

The invention relates to a turbojet engine with afterburner chamber and rotary jet nozzle system control and regulation of the rotary nozzle, mounted on highly maneuverable multifunctional fighters. The engine contains afterburning chamber and rotary jet nozzle with its hydraulic system actuator. As the working fluid of the hydraulic system actuator rotary nozzle of the selected fuel. What this hydraulic system via electrohydrodynamic regulator-Converter attached to the engine provided with the fuel system of the engine. This controls electrohydrodynamic regulator-Converter electrically connected with the remote control system of the rotary nozzle and hydraulically with cavities for backward and forward movement of the cylinder actuator rotation of the nozzle. The fuel pump is equipped with a solenoid electrically connected with the remote control system by turning the nozzle. Controls electrohydrodynamic regulator and housing swivel nozzle kinematically connected between mahanirvana plane and the actuator of the steering nozzle. 1 C.p. f-crystals, 1 Il.

The invention relates to a turbojet engine with afterburner chamber and rotary jet nozzle, mounted on modern highly maneuverable aircraft and multi-role fighters.

Known turbojet engine with afterburner chamber and rotary multimode axisymmetric jet nozzle containing a very complex hydraulic system actuator nozzle, where the working fluid is used any hydraulic oil. It used to be paired on a tandem, telescopic hydraulic cylinders complex structures to control the supersonic part of the jet nozzle and system mechanical synchronization of the kinematics of the moving parts(1).

Also known turbojet engine, containing the afterburning chamber and rotary jet nozzle with its hydraulic actuator(2). This engine contains not less complicated than in the prototype (1), the combined hydraulic system actuator jet nozzle and a plane, where as the working fluid used hydraulic oil. It has two groups of actuators, three cylinder in each, alternating between the jet nozzle to provide highly maneuverable engine multifunction aircraft, by moving the belt supersonic wings in radial and tangential directions on the modes with changeable direction of the thrust vector. This design also has a complex system of hydraulic drive, automatic control and control of rotary nozzles and, according to the international aviation expositions and salons, in recent years, such technical solutions still do not have robust flight aircraft designs. This is largely due to the fact that the leak tightness of the joint management system nozzle and the plane can lead to violation of the controllability of the aircraft.

The objective of the invention is to improve the reliability of the hydraulic system of the aircraft control and power drive control of the rotary nozzle due to the separation of these hydraulic systems of the engine and of the aircraft by using as the working fluid of the hydraulic system actuator rotary nozzle - fuel used in the engine.

This task is achieved by the turbojet engine, containing the afterburning chamber and rotary jet nozzle with its hydraulic system power Pref is sooner fuel, what this hydraulic system via electrohydrodynamic regulator-Converter attached to the engine provided with the fuel system of the engine, with controls electrohydrodynamic regulator-Converter electrically connected with the remote control system by turning the nozzle, and hydraulically with cavities for backward and forward movement of the cylinder actuator rotation of the nozzle, and the fuel pump is equipped with a solenoid electrically connected with the remote control system by turning the nozzle.

In addition, controls electrohydrodynamic regulator and housing swivel nozzle kinematically interconnected mechanical feedback.

New here is that as the working fluid of the hydraulic system actuator rotary nozzle the fuel selected, for which the hydraulic system via electrohydrodynamic regulator-Converter attached to the engine, and communicated with the fuel system of the engine, with controls electrohydrodynamic regulator-Converter electrically connected with the remote control system by turning toplivnyy the pump is provided with a valve, electrically connected with the remote control system by turning the nozzle.

This controls electrohydrodynamic regulator and the housing of the rotary nozzle can be kinematically interconnected mechanical feedback.

Selecting as the working fluid of the hydraulic system actuator rotary nozzle fuel, we can divide the hydraulic system actuator rotary nozzle and the hydraulic control system of the aircraft, for which the hydraulic control system nozzle through electrohydrodynamic regulator-Converter attached to the engine provided with the fuel system of the engine.

Combining controls electrohydrodynamic regulator-Converter - electrically by remote control system by turning the nozzle, and hydraulically with cavities for backward and forward movement of the cylinder actuator rotation of the nozzle connected to the fuel system of the engine, we can increase the reliability of the hydraulic system of the aircraft control and hydraulic drive control system of the rotary nozzle.

Providing topl who s got the ability in time management swivel jet nozzle to stabilize the pressure of the working fluid supplied from the fuel pump to rotate the nozzle even when the engine is running and the regimes close to a small gas. This is done by means of the valve, which upon command from the remote control system of the rotary nozzle sets a certain, predetermined value of fluid pressure, thereby increasing reserves the stable operation of the drive.

Stabilization fuel pressure as the working fluid supplied to the control system rotary jet nozzle during operation of the system control the rotation of the jet nozzle according to the electrical command by setting and maintaining a certain preassigned values, providing as overcoming the gas-dynamic resistance and friction in the rotating device, while ensuring the consistency of the dynamic characteristics of the actuator, and hence, the stability factor.

Performing controls electrohydrodynamic regulator and housing swivel nozzle kinematically interconnected mechanical feedback, we get the ability to reliably and efficiently manage swivel nozzle in the range of operating conditions and, most importantly, failure of e is Stamou remote control by turning the nozzle.

The drawing shows a turbojet engine with afterburner chamber and rotary jet nozzle with the scheme of the actuator and the steering nozzle.

Turbojet engine 1 includes a compressor 2, the main combustion chamber 3, a turbine 4, the afterburning chamber 5 and the rotary nozzle 6 with a cooled wall 7, having the ability to rotate around the axis 8 at a given angle. On the housing 9 turbojet engine 1 is fixed electrohydrodynamic controller 10 controls 11 connected to the housing of the rotary nozzle 12 by mechanical feedback 13. In the case afterburners 5 hinged cylinders 14 with pistons and rods 15, pivoted 16 with the housing of the rotary nozzle 12 actuator 17 having a cavity forward stroke 18 and the cavity reverse 19 connected by pipes 20 and 21 with electrohydrodynamic controller 10 is electrically connected by wires 22 and 23 with the remote control system 24 of the rotary nozzle 6 and the fuel plunger pump 25 and a pipe 26 with the fuel plunger pump 25 regular fuel system 27 of the engine 1. The fuel pump 25 is supplied by a solenoid 28, when the body 1 on the ground during testing before takeoff or in flight of the aircraft, if necessary, the deviation direction of the thrust vector in the plane of the swing swivel nozzle 6 around the axis 8 at a given anglethe team at the turn from the remote control system 24 through wires 22 and 23, the electrical control signal supplied to electrohydrodynamic controller 10 mounted on the turbojet engine 1, and the fuel plunger pump 25 regular fuel system 27. In this fuel plunger pump 25 is rebuilt to maintain for them a certain preassigned values of pressure, for example 100 ATM, and stabilizes it during operation of the system control the rotation of the nozzle 6. Further, the fuel high pressure pipe 26 is fed to the input electrohydrodynamic controller 10 where it is converted to a command pressure fuel pipeline 20 or 21 enters the cavity of the forward stroke 18 or reverse 19, respectively, and rotates the rotary nozzle 6 around the axis 8 in the desired direction. When this control elements 11 electrohydrodynamic regulator 10 pivotally connected mechanical feedback 13 with the housing of the rotary nozzle 12 and monitor the dynamics of displacement rotary nozzle 6, ensuring trouble free operation of the turbojet engine in the entire range of operating conditions.

Sources of information:

1. ER N I, containing afterburning chamber and rotary jet nozzle with its hydraulic system actuator, characterized in that as the working fluid of the hydraulic system actuator rotary nozzle the fuel selected, for which the hydraulic system via electrohydrodynamic regulator-Converter attached to the engine provided with the fuel system of the engine, with controls electrohydrodynamic regulator-Converter electrically connected with the remote control system by turning the nozzle and hydraulically with cavities for backward and forward movement of the cylinder actuator rotation of the nozzle, and the fuel pump is equipped with a solenoid electrically connected with the remote control system by turning the nozzle.

2. Turbojet engine under item 1, characterized in that the control elements electrohydrodynamic regulator and housing swivel nozzle kinematically interconnected mechanical feedback.

 

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