EA015726B1 - Combined jet multimode engine - Google Patents

Abstract

The invention relates to propulsion engineering, in particular, to jet engines and comprises combustion and jet chambers, an air intake, jets, a compressor disposed above a front jet chamber, fuel and compressor pumps arranged at one stator with a two stroke rotary piston engine (RPE) allowing to serve as a drive in case there is no outer oxidizer source and comprising a rotor embodied as flat rings with inserted therebetween piston barrels and pistons connected by rods. The RPE also provides supply of working components through fuel and compression jets for injecting them into partially emptied working chamber and together with the compression and fuel pumps is mechanically connected through driving gears at its outer side, and also comprises a transfer mechanism located in the RPE middle, through which pass all gas/liquid flows entering through the compressor and fuel-gas branch pipes also passing through the compression and fuel pumps and outgoing into two combustion chambers arranged at one axis oppositely and reaching reactive combustion chambers variety of use thereof determines multimode engine operation.

Description

The invention relates to engine, in particular to jet engines. The engine is proposed to be used in aviation, astronautics. It consists of an air intake, a compressor, a two-stroke rotary-piston engine with repeated use of the working fluid, fuel and compression pumps, a substance distribution mechanism, rear and front thrust combustion chambers, jet chambers, nozzles regulating the direction and density of exhaust gas flows, ignition systems, and management.

The level of technology

There are various propulsion systems, whose function is the creation of jet thrust, ensuring the movement of the aircraft in space, divided into two groups - rocket and air-jet (Kulagin VV Theory, calculation and design of aircraft engines and power plants, Moscow, Mashinostroenie, 2002). For example, turbojet, rotor-jet, direct-flow, rocket liquid and solid fuel, pulsating, etc. The disadvantages of such structures are some low efficiency, the use of a turbine or the ceiling of the application (in atmospheric layers that do not contain oxygen, can not be used). Different variants of jet engines, for example, a turbojet, described in RF patent No. 2237185 C1, Р02К 3/00, Р02С 7/06, use a similar scheme of engine operation, namely the capture of oxygen from the environment entering the engine through the air intake to the compressor, along with other gases (nitrogen and others), used as a heated working fluid and participating in the formation of jet thrust, further mixing of oxygen with fuel and oxidation of the latter with release of thermal energy in the chambers, and the output of combustion products and non-combustion gases through a nozzle. As a result, jet thrust is produced by dropping combustion products and gases, which are only heated, with great speed and low mass. This scheme is solved differently for different jet engines, for example, the use of a mechanical drive is driven by a turbine engine by a turbine, by a rotary jet engine by a rotor, by a separate mechanism in the form of an internal combustion engine; or mixing air with fuel — either by spraying the latter or turning it into a gaseous state and then mixing and other options; or a design solution for locating mechanisms to improve engine efficiency. In general, one of the modes of operation of a jet multi-mode engine resembles the scheme used in air-jet engines. When the engine is operated only according to this scheme, it is impossible to use it in an environment that does not contain oxygen.

Rocket engines, in comparison with air-jet engines, also work in an oxygen-free environment, but in the dense layers of the atmosphere, it is still more efficient to use air-jet engines. Rocket engines are divided into solid-fuel and liquid-fuel ones (VE Alemasov. Theory of rocket engines, Moscow, Mashinostroenie, 1989), for example, RF patent 2148181 Р02К 9/48 describes a rocket engine with fuel in a liquid state, but at the same time they have several disadvantages among them, low efficiency, the need to use a stepped engine placement system (if the task is to put a payload into orbit), the use of additional mechanisms for launching rockets, and the complexity of control.

And there is also a separate class of jet engines - a combined one, to which the proposed technical solution belongs, combining both the signs of an air-jet and a rocket engine. Known combined engines are a combination of turbine and direct-flow (TPD), or rocket and direct-flow (RPD) or rocket and turbine (RTD) engines (Kulagin V.V. Theory, design and calculation of aircraft engines and power plants, Moscow, Mashinostroenie, 2002). A reactive multi-mode engine differs from those listed by using a motor mechanism (internal combustion engine) as a mechanical drive that generates mechanical energy not only when the oxidizer is received from the environment, but also in its absence, using it from additional tanks.

A variety of propulsion systems are known, the purpose of which is to convert the energy of expanding gases into rotational mechanical motion. For example, such as rotary, turbine, piston, blade, rotary-piston engines and their various combinations, characterized by the mechanism for converting the pressure of expanding gases into rotary motion, by the tactfulness of the flow of the cycles, the structure of the working chambers and the mutual placement of mechanical parts. The purpose of their use is not to use them in the absence of external sources of oxidant, and during their work the working fluid changes with each cycle. Whereas in a rotary-piston engine (RPD) with repeated use of the working fluid, used as a mechanical drive in a reactive multi-mode engine, it is possible to operate it in the absence of an external oxidizer. Rotary piston engine has the same mechanism of operation of the piston, as in piston engines, namely reciprocating. Flammable mixture is formed through injection. But unlike the others, along with the fuel nozzle, it also has a nozzle that injects squeezed air or oxygen into the working chamber. The mechanism of converting reciprocating motion into rotation

- 1 015726 body has similarity with the mechanism described in the piston machine from RF patent 2157892 С2, Р01В 9/06, Р02В 75/32, Р16Н 21/28, in which, as in the RPD, the piston is fixed fixedly to the rod, which performs a return -accessive movements due to changes in the bend of the rotor. In the case of RPD re-use of the working fluid pistons and piston cups are placed in the rotor, and the rod is fixed on the tracks of a fixed distribution ring, made in the form of an ellipse, and due to this bending, reciprocating movement of the piston is provided.

The objective of the invention is the possibility of using reactive multi-mode engine above the ceiling of the use of air-jet engines, in more rarefied layers containing a small amount of oxygen, and in an atmosphere-free space when switching from an operation mode similar to that used in air-reactive engines, for the mode in which the oxidizer for engine operation is taken from additional tanks, as well as the possibility of an aircraft apparatus using these engines, vertical n doma and descent.

In the first mode, the engine operates in atmospheric layers containing oxygen, which enters the compressor through the air intake, is compressed in it, and, after passing through the air channels, mixes with the injected fuel mixture, entering the combustion chamber for ignition.

The engine has, in addition to the main thrust - the front, for braking the aircraft, for example, when descending into the atmospheric layers of the earth. And by reducing the speed to the required level, when entering into dense layers, there is no need to have special braking systems and heat-resistant layers on the device, which additionally makes it possible to use wings for improved aerodynamic characteristics of the device, while in rocket technology the use of wings is The load is limited due to the air resistance of dense layers during vertical acceleration and lowering of the apparatus into the atmosphere and ineffectively. Combining the front and rear thrusts simultaneously, it is possible to provide vertical lifting and lowering of the aircraft in the conditions of using special flexible nozzles, controlling them, changing the direction of the gas flows at a sufficient angle to form a lifting impulse. The front nozzle, when the aircraft uses only rear thrust, as in conventional aircraft, tapers to a minimum, ensuring the flow of the structure when flying in atmospheric layers.

The second mode is designed to operate the engine in discharged air, containing a small amount of oxygen, or in airless space and is activated at altitudes that are the ceiling of the use of jet engines. In this case, the flow through the air compressor stops the air, and instead of air, oxygen enters the engine from additional tanks.

The disadvantage of this technical solution is the need to apply a more efficient cooling system, as well as the complexity of some engine components.

The technical result is the use of the built-in rotor-piston engine (RPD) in the jet engine for driving its mechanisms. A feature of this engine is the simultaneous supply to the working chambers of compressed air or oxygen from the compression pump and fuel from the fuel pump and re-use of the working fluid (burnt gases) with partial removal of excess gases after completion of the working stroke through the exhaust valves, leaving the necessary number of compression chambers in the working chambers. gases for further injection into them of fuel and oxidizer. This gives the RPD the ability to work in an oxygen-free space, driving jet fuel and compressor high-pressure pumps and other mechanisms.

A rotary piston engine is a rotor in the form of flat rings interconnected, with pistons inserted into it, performing reciprocating movements, rotating on a cylindrical body, the core of a jet engine, on which the rotors of the fuel and compression pumps rotate in the center, in the movement of a rotary-piston engine, and feeding not only the jet engine, but also its (RPD), through the distribution system of substances located in the core of the jet engine. RAP is a push-pull. Duty cycle: injection of compressed air or oxidizer and fuel into the working chamber with compressed gases after they are compressed by the piston and ignited, the working stroke when the piston is withdrawn, at the end of which excess working fluid is removed through the exhaust valve, compression of the left burned gases by the piston followed by the start of another cycle.

The invention consists in the modes of operation of a jet engine, allowing the engine to operate in different environments. A general view of the engine is shown in FIG. one.

In the first mode (the mode of use of the oxidizer from the environment) through the air intake 1, air enters the compressor 2 (Fig. 2) and is compressed, then the part goes through the air channels 3, entering the combustion chamber 4, where it mixes with the injected fuel flow for combustion, another part through other air channels 5 enters the reactive chamber 6. A part of compressed air, passing through the air channels 5, goes to the oxygen switch 7 (performing the function of switching or closing flows (air, oxygen), and then air-oxygen pipe 8 to the compression pump 9, which pumps air into the RPD 10, already supplied under high pressure, along with the fuel.Working the RPD 10 sets in motion all the mechanisms of the jet engine .The burnt gases from the RPD 10 are output to the jet chamber 6.

- 2,015,726 fuel nozzles 11 are supplied under a certain pressure to the fuel pump 12, then under high pressure are distributed through the high pressure nozzles 13, most of it goes to the jet fuel nozzle 14 (injecting fuel into the combustion chamber 4) through the high pressure fuel switch 15, the rest enters the RPD 10.

In the second mode (mode of use of the oxidizer from the tanks), the air intake 1 and compressor 2 are turned off. The air channels 3, 5 (Fig. 3) are closed by the dial switches 16, 17 (Fig. 4, 5). An oxidizer enters the engine from the oxygen pipes 18 to the engine, heading for the compression pump 9 through oxygen switches 7, which in the first mode were switched to compressed air. The compression pump 9 at the same time already brings the oxidizer not only to the RPD 10, but also to the combustion chamber 4 to the reactive oxygen nozzles 19, as a result of which it is necessary to increase the flow of the compression pump 9, which is solved by switching to a certain feed level immediately when the second mode is turned on. The supply of the oxidizer from the compression pump 9 to the oxygen jet nozzle 19 goes through high pressure oxygen switches 20, which previously closed the passage. The movement of fuel proceeds in the same way as in the first mode of operation.

The front draft jet chamber 6 is located in the middle with respect to the air intake 1 and the air compressor 2.

Using one of the modes, it is possible to change the thrust (switching on the front, rear, or simultaneous operation) while directing the fuel and oxidizer flows with high pressure fuel switches 15 and high pressure oxygen switches 20 connecting the fuel 12 and compression 9 pumps and jet fuel and oxygen nozzles 14 , nineteen; as well as when using the dials 16, 17, closing or opening the air flow in the front or rear of the reactive chamber.

In both modes of the engine, simultaneous operation of the front and rear thrusts is possible for vertical ascent or descent, and it is necessary to change the direction of the jet nozzles 21 downwards by a certain angle. What can be solved by changing the position of the switches 15, 20 from single-flow to single-flow position, the position in which the fuel and oxygen substance is sent simultaneously to the jet nozzles 14, 19, related to the back and forward travel.

Working, fuel 12 and compression 9 pumps feed simultaneously RPD 10 and jet nozzles 14, 19 and with a decrease or increase in the supply of fuel and oxidant, the distribution of substances will evenly correspond to the flow capacity of the nozzles. Increasing the fuel supply in the fuel pump 12, while simultaneously increasing the supply in the compression pump 9, the power of the RPD 10 increases, increasing the power of the jet engine.

FIG. 6 shows a rotary-piston engine for re-use of a working fluid, which is a rotor 22 (FIG. 7) in the form of two flat rings fastened together with piston cups 23. The rotor is inserted into the stator (core of a jet engine) 24 on a rotor track 25 (Fig. 8), tightly closed by partitions 26 (Fig. 10). Bearings 27 are installed between rotor 22 and stator 24, gear rims 28 are placed on the other side of rotor disks 22 to transfer mechanical energy to receiving gears 29 and further from them to transfer shafts 30, which are connected to fuel 12, compression 9 pumps and other mechanisms. Through the transfer shafts 30 is driven to the compressor 2.

The work of a rotary piston engine

In RPD, the duty cycle consists of two cycles. During one revolution of the rotor, the piston 31 (FIG. 11) makes two working strokes and two reciprocating movements. The piston head 32 is directed towards the center of the jet engine, the piston skirt 33 is inclined in the direction of the rotor 22. The piston 34 is fixed to the piston 31, on which the outer 35 and inner rollers 36 are mounted, which are inserted into the distribution ring 37 along which they run. The distribution ring 37 is attached to the external motor housing and has an elliptical shape. After the start of the working stroke, at the beginning of which the fuel 39 and compressor 40 are injected into the working chamber 38 by the nozzles (FIG. 13), the fuel and oxidizer pressurize the gases on the piston 31, which is retracted inwardly to the bend of the distribution ring 37, transmitting the movement to the rotor 22 After a quarter turn of the rotor, the first cycle of the cycle ends with a piston outlet 31, at the end of which excess gases are discharged by an exhaust valve 41 (a valve opening when a certain pressure is exceeded) from working chamber 38.

The second cycle begins with the compression of the working fluid (burnt gases). The distribution ring 37 is narrowed and this leads to the return of the rod 34 with the piston 31, the working chamber 38 is compressed, squeezing the working fluid in it, the piston window 42 approaches the injection window 43 (the recess where the fuel 39 and compression nozzles 40 are located). The second cycle ends with the compression of the working body. After the windows 42, 43 coincide, the next cycle begins, by injecting fuel and oxidant into the combustion chamber.

FIG. 12 shows stem connections 32.

Compression rollers 44 are placed between the piston windows 42 to seal the working chambers 38, which run along the inside of the rotary track 25, on which are placed injection

- 3 015726, 43 and exhaust ports 45 (Fig. 10, 11).

The device for fuel 12 and compression 9 pumps is similar and similar to RPD 10 (Fig. 14), although it has some difference from RPD 10. They consist of fuel and compression rotors 46 inserted into rotor tracks 25 (Fig. 15), closed by partitions 26 The bearings 27 are placed between the rotors 46 and the stator 24. The rotors, like in the RPD 10, have the form of flat rings connected to themselves and inserted between them piston fuel or compression cups 47. Adjusting the flow of fuel, air or oxygen to the pumps 9, 12 produced by changing the bend of the fuel and compression distribution rings 48 shown in FIG. 16, 17.

The progress of the fuel and compression pumps 12, 9.

The piston of the pump 49 in one revolution of the fuel and compression rotors 46 makes two reciprocating movements, producing two injections, the distribution of fuel, air and oxygen goes depending on the operating modes. The substance enters the compression chamber 50 from the inlet port 51 (FIG. 9) after the injection of the substance is completed when the piston 49 is retracted, which retracts to a level that allows the expansion of the distribution ring 48 to expand, then when the distribution ring 48 is narrowed, the substance is compressed in the compression chamber 50. When the fuel or compression piston window 52 reaches the valve window 53 (FIG. 9), the substance from the compression chamber 50 will flow to the high pressure valve 54 (valve through which the substance passes above a certain high pressure) and substance ohodit therethrough as long as the pressure in the compression chamber 50 drops below a valve capacity 54.

FIG. 23 and 24 additionally show the connections of the high-pressure valves with the distribution mechanism 55.

The distribution mechanism 55 shown in FIG. 2, 18, 19, 20, 21, 22, controls the flow of fuel, air and oxygen in a jet engine. It consists of oxygen switches 7, high pressure fuel and oxygen switches 15, 20, nozzles 8, 11, 13, 18, dial switches 16, 17.

The dial switches 16, 17 perform the function of closing the passage from the air ducts 3, 5 to the combustion chamber 4 and the engine's reaction chamber 6 and switch when either the engine is running or the direction of thrust is changed. In the first mode, they are open, when turned on, the second one closes, and also closes when one of the reactive chambers is turned off. They have the form of a hollow cylinder with holes made on the sides for air to pass through them, rotating the switches, it is possible to displace the holes, thereby blocking the passage of air through them, or opening them.

Oxygen switches 7 (Fig. 21) have the form of a disk with a curved passage done in it, changing its position, one nozzle is blocked and the other opens, switches when the engine is changed, and during the first mode it lets air through and the second oxygen.

Oxygen and high pressure fuel switches 15, 20 (Fig. 19, 20), as well as oxygen switches 7, have the form of a disk, but with the three inputs made in it connected in the middle, the two inputs are located closer to each other, relative to the third at an angle of 45 °. Changing the position of the disk leads to a change in the direction of flow of the substance or to its closure. Switches 15, 20 have 4 positions, the inclusion of which depends on both the mode of operation of the jet engine and the direction of engine thrust. Oxygen high-pressure switches 20 in the first mode of operation close the passage to the oxygen jet nozzles 19. When the second mode is turned on, they can direct the flow either to one of the reactive oxygen nozzles 19 of the combustion chambers 4 forward or reverse, or both at the same time. The high-pressure fuel switches 15 direct the fuel to the jet fuel nozzles 14 of the rear and front thrust, depending on the need to use one of them, as well as the high-pressure oxygen switches 15.

Switching the operating modes of the jet dual-mode engine, you can use the engine in conditions more suitable to one of the modes. So in dense layers of the atmosphere containing oxygen, it is more convenient to use the mode of operation in which the engine operates on the principle of air-jet, characteristic of relatively low fuel consumption (relative to rocket engines), while the aircraft accelerates to sound speed, rising to a sufficient height and less dense, to the borders, where the use of this mode is ineffective. Further, at altitudes that are more rarefied and therefore more efficient for rocket engines, it is better to use the mode of operation of a reactive multi-mode engine, in which the oxidizer is taken from additional tanks. The engine can be used when descending from low orbits from the first cosmic velocity, for decelerating the vehicle and as a result of mitigating atmospheric resistance.

Sources of information taken into account

1. Kulagin V.V. Theory, calculation and design of aircraft engines and power plants, Moscow, Mashinostroenie, 2002

2. Alemasov V.E. Theory of rocket engines, Moscow, Mashinostroenie, 1989

3. RF Patent No. 2237185 C1, Е02К 3/00, Е02С 7/06, 2003

- 4 015726

4. RF patent № 2148181, Р02К 9/48, 1998

5. RF patent № 2157892 С2, Р01В 9/06, Р02В 75/32, Р16Н 21/28, 1999

Claims (1)

A combined jet engine comprising an air compressor, a rotary piston engine, a fuel and air / oxidation pump, a distribution system, ignition and combustion chambers, the rotary piston engine being made in the form of a rotor consisting of disks mounted on a cylindrical a stator, on its tracks with bearings, and between them cylinders with pistons connected to the rods and tilted in the direction of movement of the rotor, while the rods at the other end are equipped with rollers, a cat others move along an ellipsoid track installed separately from the rotor on the jet engine body; the fuel and air / compression pumps driven by the rotary piston engine provide fuel, compressed air or an oxidizing agent for the rotary piston engine to the ignition and combustion chambers, as well as the fuel and air / oxidation pumps, as well as the rotary piston engine, in the form of disks with cylinders and pistons contained between them, directed in the opposite direction of the rotor movement, with an additional roller on the rod adjacent to another ellipsoid track, which ensures possibility to delay the injection piston for fuel and air or oxidant; and the rotary piston engine in the stator on a cylindrical surface has channels for supplying fuel, compressed air or an oxidizing agent and exhaust gas exhaust windows; and also in the stator on the cylindrical surface near the fuel and air / oxidation pumps there are elongated channels for supplying fuel, compressed air or an oxidizing agent and a window for discharging said substances from the pumps; the distribution system is also configured to switch the operating modes of the jet engine between the air-jet and rocket engines and contains flow switches and a plug that change the supply of compression air to the oxidizer from the tanks and close the windows through which air is supplied from the compressor to the combustion chamber, while the distribution system arranged so that it connects the supply of fuel and oxidizer to the rotary piston engine and the ignition chamber, the combustion chamber of which is a continuation.