RU16613U1 - COMBINED ENGINE FOR AIRCRAFT - Google Patents

Abstract

Combined engine for aircraft, comprising a marching engine mounted in a single body and forming a block design, which is a dual-mode ramjet engine with a pulsating detonation combustion engine and a starting engine connected to a single control system, characterized in that the starting engine is a solid-fuel engine, freely embedded in the supporting body and resting on the front body on the central body, and its lamenitel installed in the critical section of the nozzle area of the block, is connected only with the launch of the system.

Description

Combined engine for aircraft

The utility model relates to power plants that do not have turbines or other engines that drive a compressor or supercharger, or rather, combined ramjet engines.

There is experience in the use of combined engines, consisting, for example, of turbojet (TRD) and rocket (RD) engines, or a combination thereof, having a common drive and housed in a single housing. In mass terms, such engines are more profitable than a simple combination of turbojet engines and taxiways.

Known rocket-turbine engine of the combined type, shown in Fig.5.3. RI Kurziner "Jet engines for high supersonic flight speeds. M.: Engineering, 1989, p. 167. The combined ATR engine was proposed for a promising single-stage military aerospace system and can be worked out, according to foreign experts, in 10 ... 15 years. This type of engine is characterized by an extension of the range of attainable speeds and altitudes. Despite the fact that this type of engine has not yet been mastered by any country, the further development of rocket and space technology now requires its further improvement, for example, in the development and creation of an aerodynamic aircraft. However, prospective 21st century aircraft require a wide range of smooth changes in their flight speed, from subsonic to hypersonic, as well as for their engines to operate economically at any altitude up to airless space.

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It significantly expanded the technical capabilities of the engine, allowing to realize the flight of an aircraft (LA) in a wide range of altitudes and speeds. This is achieved by combining in one design two types of engines: a pulsating detonation combustion engine (PDDG) and a dual-mode ramjet engine (ramjet). The proposed engine design will allow you to change the speed of the aircraft, starting from its subsonic values and ending with hypersonic.

However, this scheme is characterized by a prolonged transition to the march mode of the engine. This is due to the low frequency of detonation pulses currently being implemented by this type of engine, which reduces the value of the starting thrust.

The objective of the utility model is to increase the initial flight speed of the aircraft and its more rapid transition to the march mode of operation.

The solution to this problem is achieved through the use of a solid rocket engine (solid propellant rocket engine) as the starting mode of operation.

The task is achieved in that the starting engine is a solid-fuel engine freely embedded in the bearing body and resting on the central body with its front bottom, and its igniter, installed in the region of the critical section of the nozzle block, is connected only with the starting system.

The drawing shows the structural layout of the combined engine for aircraft, which is a combination of two engines in a single design: marching and starting. The main engine combines in a single design PDDG and dual-mode ramjet.

that aircraft in outer space and at all intermediate modes of engine operation. The gas turbine engine (2) is designed to create traction at high speeds of flight of the aircraft. Both engines provide marching operation of the combined engine.

The starting engine (3) is a solid propellant rocket engine and is designed to increase the initial flight speed of the aircraft and its more rapid transition to the march mode of operation.

PDDG consists of a case with windows 4, a central body 5, a fuel component supply system 6, an initiation system 7, a retractable cone 8, and flaps 9.

A double-circuit ramjet consists of a housing 10 with wings 11, connected to the supporting housing 4 by pylons 12, and elements of the fuel component supply system 13.

The solid propellant rocket motor consists of a housing 14 and a solid fuel charge 15 and a nozzle block 16 fixed thereon, as well as an igniter 17.

The combined engine can operate in several modes of operation. At the same time, the supply of fuel components to the gas turbine engine and the turbojet engine is carried out by a unified fuel component supply system and upon command from a common control system. The operation of the solid propellant rocket motor is carried out autonomously from the launch system.

The first mode of operation of the combined engine is the start mode.

On the day the engine starts, it is necessary to apply a signal to the igniter 17. The products of its combustion fill the free volume of the solid propellant chamber. With increasing pressure in the chamber above the minimum pressure of stable combustion and reaching the ignition temperature of the solid fuel charge 15, it ignites. After knocking out the plugs together with the igniter 17, the expiration of combustion products occurs, resulting in a thrust. When the aircraft reaches a flight speed of ... 3 or more, and after complete combustion of the solid fuel charge, the combined engine switches to marching operation.

When this occurs, the opening of the valves 9, after which the speed pressure of the oncoming air of the solid propellant rocket motor. loosely nested in a bearing housing, throws back. As a result of this, the chamber of the combined engine, which is the first circuit, is removed and the engine is tuned to the second mode of operation.

The second mode of operation of the combined engine is a joint PDDG mode with an ejector traction amplifier.

Starting position. The aircraft is in the prelaunch position. While the sash 11 PDDG are in the initial (neutral) position, the front sash 9 ramjets are raised, and the rear (output) - in the initial (neutral) position. Retractable cone 8 in the initial (retracted) position. Before starting the engine, the PDDG detonation chamber is initially filled with the working mixture from the fuel component supply system 6. The cavity “b. Upon completion of its filling, the initiation system generates a detonation pulse, under the action of which the working mixture detonates. The resulting detonation wave propagates only towards the outlet nozzle. Its forward propagation is hindered by a system of shock waves formed as a result of the interaction of the detonation wave with the central body 5. The detonation wave, leaving the PDDG nozzle, turns into a shock wave, which, directed to the output part of the housing 10, creates a vacuum at its entrance. Due to the arising effect of ejection, an additional component of the thrust is created.

also filling the internal volume of the housing 4 with another portion of the working mixture. The process is then repeated. At the same time, only fuel is supplied to the PDDG detonation chamber as fuel, and air from the environment is used as an oxidizing agent.

The thrust of the combined engine in the first mode of its operation is created due to the interaction of the detonation wave with the central body, due to the outflow of detonation products through the nozzle and due to the ejection effect arising at the entrance to the ramjet. Due to the created traction, the aircraft moves away.

The third mode of operation of the combined 1P1DG is the joint regime of PDDG and ramjet. This mode is carried out during the flight of the aircraft to speeds.

Starting position. The aircraft is in flight on a trajectory. In this case, the sash 9 PDDG are covered, and the retractable cone 8 is advanced so that it provides a given mode of operation. PDDG.

Front and rear wings 11 ramjets are covered. The front flaps provide a given air flow rate, and the rear flaps provide the required value of the critical section area formed between the exit section of the PDDG nozzle and the flaps 11.

PDDG works similarly to the above mode. The components of fuel for ramjet engines are fuel from the supply system as the oxidizing agent of ambient air.

The ramjet launch is preceded by the process of filling the cavity with a working mixture. As it fills, an ignition command is issued. Both the supply of fuel and the ignition of the working mixture are carried out by the elements of the supply of fuel components and their ignition 13. The thrust ramjet is created due to the expiration of combustion products from the combustion chamber.

with a binocular engine, it consists of rods created by both PDDG and ramjet.

The fourth mode of operation of the combined engine is the combined regime of the PDDG and the hypersonic ramjet engine (GPVRD). This mode is carried out during the flight of the aircraft with speeds .. .5.

Starting position. The aircraft is in flight, while the front ramjet flaps 11 are in the neutral position and the rear flaps are in the open position, which ensures the process of supersonic combustion of the working mixture in the ramjet chamber and further acceleration of the combustion products. The position of the remaining moving parts corresponds to the second mode of operation, but with tuning them to a predetermined engine operation mode corresponding to the required flight speed of the aircraft.

A distinctive feature of the engine in this mode is that the supersonic air flow is practically not inhibited in the ramjet chamber, which ensures the supersonic combustion process in it. Since the flow of combustion products into the ramjet is supersonic, there is no need to create a critical section, and further acceleration of the combustion products is carried out by increasing the cross-sectional area of the outlet channel of the nozzle.

The total thrust of the combined engine is the sum of the thrust of the PDDG and the scramjet, however, the scramjet creates the main component.

The fifth mode of operation of the combined engine is a dual-circuit detonation combustion engine. This mode of operation is used during the flight of an aircraft with speeds. In this case, the scramjet begins to work in the regime of SDG. For this, the retractable cone 8 occupies such a position and shape that the velocity of the flow of the working mixture into detonation chambers is equal to the velocity of propagation of the detonation wave. The components of the fuel are oxygen released from the air, and entering the air intakes due to the pressure head and fuel of any aggregate state, but before being transferred to the mixing chamber

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into a gaseous state and capable of detonating. Its supply is carried out both due to the feed system, placed B cone and in the housing, and due to the ejection effect.

The whole mixing process can be divided into two sections: initial and main. The mixing sections will also have corresponding sections.

In the initial section of the mixing chamber, fuel in the form of an ejected gas is continuously captured by a high-speed jet of air and carried away into the mixing zone. This flow with a known approximation can be likened to a turbulent jet moving in a turbid stream. Due to the presence of transverse pulsating velocity components characteristic of a turbulent flow, flows are introduced into each other, forming a gradually expanding mixing zone - the boundary layer of the jet of the working mixture. Within the boundary layer, the initial formation of the working mixture occurs and its parameters gradually change. Outside the boundary layer of the initial section of the suprasensory chamber, there are unperturbed flows of the ejected and ejected components of the working mixture.

In the main part of the mixing chamber, the homogeneous working mixture is finally formed and the zones of undisturbed flow of its components disappear. The length of this zone depends on the configuration and size of the cone, their ratio with respect to the size of the air intake, flight speed, organization of the feed system, etc. From literature it follows that the relative length of the ramjet mixing chamber is 8-10.

Let us call the cross section of the engine chamber, in which the alignment of the working mixture parameters ended, both in the flow and in the cross section of the chamber, “boundary section. At a distance of ... 3 from the boundary section, the initiator is installed.

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directions where the mixture is located. Moreover, its axial component is directed to the sides i-v.E} Ca. l other component towards the nozzle part of the engine chamber

Due to the fact that the fast and the movement of the detonation wave and the flow of the working mixture are approximately equal and directed towards each other, a standing detonation wave is formed, which divides the engine chamber into two parts: mixing and detonation chambers. Depending on the velocity flow parameters, the standing detonation wave can move somewhat along the axis of the engine chamber: forward by ... 3 to the boundary layer and backward by ... 3 to the expanding part of the engine chamber.

This mode of operation is used during the flight of an aircraft with a maximum flight speed ().

The sixth mode of operation of the combined dvitel is a dual-circuit PDDG. This mode of operation is used during the flight of an aircraft in rarefied layers of the atmosphere or in outer space.

Starting position. The aircraft is in flight in rarefied atmospheric layers or in outer space.At the same time, the leaflets 9 of the SPDG are completely closed, the retractable cone 8 is in the initial position, the front shutters AND ramjets are closed, and the rear ones are open, which forms the second contour of the PDG. A two-component working mixture, consisting of both fuel and oxidizer, fills the cavities a, b, and b into the engine using the component supply system 6 As they are filled from the initiation system, a detonation pulse is supplied from the engine control system. The working mixture located in cavity b detonates. The resulting detonation wave begins to propagate towards the PDDH nozzle. In addition, through special windows made in the housing 4, it propagates into the second circuit of the PDDG (cavity “in the ramjet”) and causes detonation of the working mixture in it. The resulting detonation wave rushes towards the ramjet nozzle. In the future, the process is repeated again with a frequency specified by the control system of two bare hells.

The thrust of the combined engine is created both due to the interaction of detonation waves with closed flaps 9 and 11, and due to the outflow of detonation products through the outlet nozzles of both circuits.

The proposed design of the combined engine will provide an opportunity for the development in the next century of both a new manned transport-space and aerospace aircraft, and new types of weapons.

The proposed scheme will expand the range of changes in the speed of the aircraft, starting with its subsonic values and ending with the maximum possible at various altitudes of its flight.

The constructive implementation of various types of engines in a single device can significantly improve the mass and geometric characteristics of aircraft compared to their autonomous use. In addition, pulsating detonation combustion engines are characterized by low consumption of fuel components and low, pressures of their supply to the detonation chamber, simplicity of design and the absence of moving parts, high efficiency and difficulty in detecting an aircraft by air defense and missile defense. This type of engine works on the entire flight path and can use such fuel components that have a wide, diverse and cheap raw material base.

Claims (1)

Combined engine for aircraft, comprising a marching engine mounted in a single body and forming a block design, which is a dual-mode ramjet engine with a pulsating detonation combustion engine and a starting engine connected to a single control system, characterized in that the starting engine is a solid-fuel engine, freely embedded in the supporting body and resting on the front body on the central body, and its lamenitel installed in the critical section of the nozzle area of the block, is connected only with the launch of the system.