RU2585160C1 - Edward soloviev ramjet engine - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention can be used in aircraft engine production. Ramjet engine comprises housing, main air intake, primary chamber of variable cross section, secondary chamber, main fuel injector. Ramjet engine also comprises series of mini air-jet engines, adjacent to inner walls of primary chamber of variable cross-section. Inside air intake reversible turbine with blades is located fixed on aerodynamic posts. Secondary chamber is made in form of tapered diffuser.

EFFECT: higher engine efficiency, possible aircraft speed, reliability.

5 cl, 4 dwg

Description

The invention relates to the field of aviation and can be used in the engine manufacturing of aircraft.

Known "" AIR-REACTIVE ENGINE "RU 2243400 [2], comprising a housing, an engine shaft with a compressor installed on it, a diffuser, ramjet engines located at a distance from the axis of rotation of the engine shaft and mounted on it, a fuel supply system, while the air intakes of ramjet engines are directed forward, and their nozzles go back into the common nozzle of the engine, consisting of a bell and a central body - “needles”, into the gap between which flow from ramjet engines Ateliers are combustion products, the engine contains a starter-generator located in front of the compressor in the engine cowl.

The disadvantage is the low reliability and fire safety due to the presence of a fuel supply system through the hollow shaft.

Closest to the claimed technical solution is "SUPERSONIC RECTANGULAR AIR-REACTIVE ENGINE WITH PULSE-BURNING COMBUSTION MODE (SPVRD WITH PRG) AND METHOD OF ITS OPERATION" RU 2446305 [2], comprising a variable air intake section and a chamber with a chamber and a nozzle, several injectors (supply belts) of fuel placed along the length of the combustion chamber, a device for initiating a pulsating combustion mode (and sensors for detecting the passage of pressure waves in the section of the combustion chamber of constant section), the first injector (feed belt) of fuel is located at the beginning of the constant section, and the next - in variable sections of the combustion chamber.

A disadvantage of the known design is the low efficiency of the engine. Another disadvantage is the low speed of the gases inside the engine, which limits the speed of the aircraft equipped with such an engine. The disadvantage is the increased complexity of the engine, leading to a decrease in engine reliability.

The technical result of the invention is to increase the efficiency of the engine, increase the possible speed of the aircraft, increase reliability.

The technical result is achieved in that a ramjet engine comprising a housing, a main air intake, a primary chamber of variable cross-section, a secondary chamber, and a main fuel injector is characterized in that it contains a series of mini air-jet engines adjacent to the inner walls of the primary chamber of variable cross-section , in the inner space of the air intake is a reversible turbine with blades mounted on aerodynamic struts, the secondary chamber is made in the form of diverging Gosia diffuser.

The diverging diffuser can be made in the form of a figure of rotation of the hyperbola. The implementation of the diffuser of this form will improve engine efficiency.

Aerodynamic struts can be made in the form of blades located at an angle to the axis of the main engine, for example 45 degrees. Installing aerodynamic struts at an angle allows you to direct the flow of incoming air in a spiral, the angle of inclination of which corresponds to the inclination of the mini-engines, which will further improve the efficiency of the engine as a whole. An angle of 45 degrees is the most optimal. The air intake can have sharp leading edges, which will reduce the drag of the engine and further increase its efficiency.

In FIG. 1 shows a cross section of the proposed engine manufactured using P. 1-5, in FIG. 2 is a view from the side of the air intake, FIG. 3 is a section through an air intake, FIG. 4 - view of a mini-engine (MVRD), where:

1 - housing;

2 - the main air intake;

3 - primary camera of variable cross-section;

4 - secondary camera;

5 - the main fuel injector;

6 - reversible turbine with blades;

7 - aerodynamic struts;

8 - mini-engine;

9 - the primary chamber of the mini-engine;

10 - secondary chamber of a mini-engine;

11 - injector of a mini-engine;

12 - direction of gas flow of the mini-engine.

The device operates as follows: In the end part of the housing 1 is the main air intake 2, passing into a wide part of the primary chamber of variable cross section 3 (aerodynamic diffuser). A chamber of variable cross section monotonously tapers from the air intake to the secondary chamber. The primary chamber has the shape of a converging hyperbolic diffuser formed by a hyperbola of revolution. The secondary chamber 4 has the form of a diverging hyperbolic diffuser formed by a hyperbola of revolution. The secondary chamber functions as a combustion chamber and an output nozzle. Both cameras in their narrow part smoothly pass into each other. At the narrowest point of the two articulated diffusers of the dual chamber of both engines is the main fuel injector 5 (nozzle, nozzle). This narrow section of the two diffusers also serves as a mixing chamber. A reversible turbine with blades 6 is mounted inside the air intake 2, mounted on aerodynamic struts 7. The ramjet engine has a set of mini ramjet engines 8, which are located in the primary chamber 3 in the direction of the air flow spirals on the inner wall of the primary chamber of the main engine , for example, in three rows. Each mini ramjet engine has a primary 9 and secondary 10 chambers of variable cross-section. The primary chamber has the shape of a converging hyperbolic diffuser formed by a hyperbola of revolution. The secondary chamber has the form of a diverging hyperbolic diffuser formed by a hyperbola of revolution. The secondary chamber functions as a combustion chamber and an output nozzle. Both chambers in their narrow part smoothly pass into each other, the injector of the mini-engine 11 is located in the narrowest place. The direction of the gas flow through the mini-engine is shown in pos. 12.

Starting (ramjet) occurs by switching a reversible turbine to compressor mode (the turbine works as an electric motor). Initial airflow is induced. In the narrow part of the diffuser of the main engine and the mini-engine, the potential energy of the incoming air flow is transformed into its kinetic energy. Described by Bernoulli kx ^2/2 ↓ + mv ^2/2 ↑ = const. Since the air flow rate is greatest in this part of the diffuser, a fuel injection and fuel injection mode occurs in mini-engines and in the main engine. Air and fuel mix in this part of the channel. The mixture breaks out into the expanding secondary chamber of both engines. The reverse transformation of kinetic energy into potential energy occurs. Described by Bernoulli kx ^2/2 ↓ + mv ^2/2 ↑ = const. The pressure is increasing. A directional explosion occurs in the secondary chamber of the mini-engine and the secondary chamber of the main engine. From the same chamber as nozzles, gases are discharged to the outside. At least the first three mini-engines are equipped with means for igniting the working mixture (for example, spark plugs). There is a series of directed explosions from mini-engines and one directed explosion from the main engine. The energy of directed explosions creates the effect of a traveling wave, entraining air and a working fluid like a turbine, which leads to an increase in the thrust of the engine. Explosions of mini-engines intensify the explosion of the main engine, and an explosion inside the main engine intensifies the explosions of mini-engines. For example, the thrust vector from 18 mini-engines Fm and the thrust vector from the main engine Fo create a common resulting vector Fres = 18Fm + Fo. The flow of air and fuel, in addition to the linear component, also has a circular component. The path of the flow in a spiral increases the length of the working fluid, increases the combustion time and the combustibility of the fuel, which allows the use of fuel with heavier and longer molecules. The expanding secondary hyperbolic chamber, in addition to creating the conditions for a directed explosion, now discharges gases outward as a nozzle. If the length of the ramjet engine, for example, is 3 m, then the total length of the Secondary combustion chamber is 1.5 m. This is enough to make an explosion and bring the gases out.

Ramjet control system

The process of operation of a ramjet engine is controlled by a fuel injection system. The use of mini-engines allows you to expand the operating modes of the jet engine at each stage of flight of the aircraft. When the engine is standing or moving at low speed, a reversible turbine 6 (made as an electric machine) in electric motor mode pumps air, making it easier to start the engine. At this stage, a sequential pulse fuel injection system is activated. A pulsating combustion mode of a jet engine is the common name for all combustion modes. Continuous burning is a special case of a pulsating combustion mode, since it is practically impossible to obtain absolutely continuous burning. At the initial stage, when the engine starts to move or moves at low speed, the forced pulsating combustion mode with large pulsations of the combustion intensity prevails. At high speed, the engine control system (not shown) selects the optimum mode of operation. Burning turns into continuous. To improve the start of a jet engine, for example, hydrogen can be used as fuel. In a ramjet engine, with its general symmetry, the system of directional explosions and the spiral motion system of the working fluid creates an asymmetry of internal processes, which prevents the movement of gases in the opposite direction.

Operation of the air intake, aerodynamic struts and reversible turbine

The air intake and aerodynamic struts have sharp edges, which will reduce the drag of the engine and further increase its efficiency. Sharp edges can destroy foreign objects in the air stream. Reversible has two modes of operation.

First mode. When the engine is standing or moving at low speed. In this case, the electric machine operates as an electric motor, which drives the blades for the initial discharge of air flow.

The second mode. After cruising speed with the aircraft, the electric machine acts as a generator to power the aircraft systems.

Engine cooling

In the proposed ramjet, the energy of combustion of the fuel is distributed throughout the entire volume of the engine casing, and not only in the combustion chamber as in a typical jet engine. This reduces the overheating of the elements and their mechanical stress. Fuel enters from the housing to the injector-nozzle-nozzle. Fuel passes through the housing, cools it and raises its temperature, which contributes to combustion.

The advantage of this ramjet is that the primary chamber and the secondary chamber of the ramjet engine and the mini-engine carry universal, combined functions. There is no need for a multi-circuit compressor, in a special nozzle. The task of this minimum set of elements is not to slow down, but to increase the speed of the working fluid along the entire path of its advancement.

EFFECT: increased efficiency of the engine is achieved by reducing turbulence losses during engine operation due to the absence of a sharp change in the direction of gas flow through the engine.

EFFECT: increased possible speed of the aircraft is achieved due to less gas movement in the direction perpendicular to the direction of flight and a higher rate of combustion reaction inside the engine.

EFFECT: increased reliability is achieved by a simpler engine design.

Industrial application. The invention can be successfully applied in the production of jet engines with a universal combustion mode for aircraft.

Claims (5)

1. A ramjet engine comprising a housing, a main air intake, a primary chamber of variable cross-section, a secondary chamber, a main fuel injector, characterized in that it comprises a series of mini air-jet engines adjacent to the inner walls of the primary chamber of variable cross-section, in the inner space a reversible turbine with blades mounted on aerodynamic struts is located in the air intake; the secondary chamber is made in the form of a diverging diffuser. 2. The engine according to claim 1, characterized in that the diverging diffuser is made in the form of a figure of rotation of the hyperbola. 3. The engine according to claim 1, characterized in that the aerodynamic struts are made in the form of blades located at an angle to the axis. 4. The engine according to claim 1, characterized in that the aerodynamic struts are located at an angle of 45 degrees to the axis of the main engine. 5. The engine according to claim 1, characterized in that the air intake is provided with sharp leading edges.

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