RU2205287C2 - Ramjet engine - Google Patents

Abstract

FIELD: aircraft industry. SUBSTANCE: proposed ramjet engine, comprising system of intercoupled sets of ramjet engines, contains diffuser, nozzle, central body of diffuser incorporating combustion chamber, provided with fuel manifolds, flaps, detonation channels, valves and detonator. Combustion chambers of system of set are connected by detonation channels providing detonation of fuel mixture in each combustion chamber. Each set of system of ramjet engines contains diffuser, nozzle, diffuser central body. Combustion chambers located in diffuser are provided with flaps and louvers. Detonator is provided with cylinder, piston and energy accumulator. Combustion chamber of one set of ramjet engine is connected with detonator by means of channel with valve. Detonation channels are furnished with valves, and detonation is provided in series in each chamber in one direction to closed cycle. EFFECT: increased power. 7 dwg

Description

 The invention relates to transport engineering, in particular to jet engines, and can be used for installation on aircraft.

Known designs of ramjet and ramjet ramjet engines as heat engines is a mechanism consisting of a diffuser, a combustion chamber and a nozzle. Traction in them is created due to the reaction of oxidation of hydrocarbons, oxidizing agent (air) and the energy released in this process. [1]
This technical solution assumes the presence of accelerators and engine operation at a certain air flow rate. At various operating modes in them under moderate supersonic and hypersonic speeds, incomplete combustion of the fuel and unstable combustion take place. At supersonic flow rates, problems with starting the engine are possible.

Known pulsating detonation combustion engine containing in a single housing two power plants - pulsating and ramjet engines. [2]
However, this solution is quite complicated in design and implementation of systems management processes.

 The problem to which the invention is directed, is to develop a ramjet engine that provides an automatic process of detonation combustion of the fuel mixture by creating a unidirectional movement of the detonation wave under any conditions of launch and flight, with the simplicity of design, the usual similar scheme Ramjet.

 The problem is solved due to the fact that in a ramjet engine containing a system of interconnected aggregates of ramjet engines containing a diffuser, nozzle, a central body of the diffuser with a combustion chamber located in it, having fuel manifolds, dampers, detonation channels, valves and a detonator, and the combustion chambers of the aggregate system are connected by detonation channels providing detonation of the fuel mixture in each combustion chamber, according to the invention, each of the system of ramjet engines contains a diffuser, nozzle, central body of the diffuser, the combustion chambers are located in the latter and have shutters and shutters, the detonator contains a cylinder, a piston, an energy accumulator, and the combustion chamber of one ramjet engine is connected to the detonator through a channel with a valve, detonation channels are equipped with valves, and detonation is provided sequentially in each chamber in one direction in a closed cycle.

 The technical result is the start, warming up and operation of the engine in any conditions, the automatic process of detonation combustion of fuel due to the distribution of the energy of the explosion on the engine units. The total power of all units is equal to the total ramjet power. The midship is equal to the sum of the midsection of all engine units, also in its other parameters.

 Figure 1 shows a General view of the ramjet; figure 2 is a section aa of figure 1; in FIG. 3 - section BB of figure 1; figure 4 shows the detonator; figure 5 shows the combustion chamber during the preparation of the fuel mixture; figure 6 - combustion chamber during the explosion; 7 is a combustion chamber during its purge.

 The ramjet engine contains a detonator 1, engine units 2, a central body 3, a diffuser 4, a combustion chamber 5, a nozzle 6, valves 7, 8 of detonation channels 9, detonation channel 10 of detonator 1 and valve 11 of detonation channel 10.

 The detonator 1 contains a cylinder 12, valves 13, 15, 18, 19, 21, 22, 23, a shock absorber 14, an energy accumulator 16, a piston 17, a valve 20 of the detonation channel 9 of the detonator 1.

 In the combustion chamber 5 there is an air damper 24, shutters 25.

 The start and heating of the ramjet is carried out by means of a detonator 1 (Fig. 1), from which detonation is transmitted to one of the engine units 2 through the detonation channel 10 of the detonator 1 (Figs. 3, 4), which leads to ignition of the fuel mixture in the combustion chamber 5 of one of ramjet aggregates (figure 2). The energy of the explosion finds an exit through the open shutters 25 (Fig.6). Residual exhaust gases are removed from the combustion chamber 5 by blowing through the air damper 24 with the open shutters 25 (Fig.7). Further, when the shutters 25 and the open air shutter 24 are closed, the incoming fuel from the nozzles of the fuel manifold is mixed with air (Fig. 5), the air shutter 24 is closed, the combustion chamber 5 is ready for a new operating cycle.

 Part of the detonation energy from the combustion chamber 5 of the first unit (FIG. 3) is transmitted via the detonation channel 9 of the combustion chamber 5 in the direction of the open valves 7 and 8 to another combustion chamber 5 of the ramjet assembly, where the fuel mixture detonates and the above processes occur. Depending on the specified number of units (two or more), this conversion mechanism goes from the combustion chamber 5 to the combustion chamber 5 of the ramjet units in the direction of the open valves 7 and 8 through the detonation channels 9 of the combustion chambers 5 to the combustion chambers 5 in a closed cycle in automatic mode.

 The detonator 1 (figure 1) operates until complete warming up and steady-state operation of all ramjet units and the entire ramjet engine system. It is included in the work in cases of interruptions or termination of the entire system of ramjet aggregates.

 The detonator 1 (figure 1) provides a detonation wave and other components of the explosion of the combustion chamber 5 (figure 2, 3) of the ramjet assembly. The piston 17 (Fig. 4) compresses the fuel mixture and the explosion energy in the cylinder 12 before detonation through the open valve 20 of the channel 10 of the detonator 1 and the open valve 11 of the channel 10 of the detonator 1 (Fig. 3, 4) through the detonation channel 10 enters the combustion chamber 5 (Fig.3) of the ramjet assembly. The force pulse on the piston 17 (FIG. 4) is smoothed and absorbed by the energy accumulator 16 and the shock absorber 14. The automatic operation of the mechanism is provided by the valves 13, 15, 18, 19, 21, 22, 23 in cooperation with the valves 20 and 11 of the detonator 1 (FIG. 4, 3).

 A disadvantage in the proposed mechanism for the operation of a ramjet engine is a slightly large hydraulic loss, which can be reduced by various engineering solutions for the execution of engine parts.

 The advantages include a multiple increase in engine power due to detonation fuel combustion, in which there is an increase in temperature and pressure compared to conventional ramjet. This is the result of chemical factors in the complete oxidation of hydrocarbons, as well as the action of mechanical energy in the form of a detonation wave. The exhaust gases are environmentally friendly. The engine is stable under all conditions, reliable start in any conditions and at high altitude. Due to the location of the combustion chamber in the central body, the length and weight of the engine are reduced.

Sources of information
1. V.S. Zuev, V.S.Makaron Theory of ramjet and rocket-ramjet engines, M., 1971

 2. Patent RU 2142058, cl. F 02 K 7/20, 1999

Claims (1)

 A ramjet engine comprising a system of interconnected ramjet engines comprising a diffuser, a nozzle, a diffuser central body with a combustion chamber located therein, having fuel manifolds, dampers, detonation channels, valves and a detonator, and the combustion chambers of the aggregate system are connected detonation channels, providing detonation of the fuel mixture in each combustion chamber, characterized in that each of the system of units of ramjet engines The device contains a diffuser, a nozzle, the central body of the diffuser, the combustion chambers are located in the latter and have shutters and shutters, the detonator contains a cylinder, a piston, an energy accumulator, while the combustion chamber of one unit of a ramjet engine is connected to the detonator through a channel with valves, detonation channels equipped with valves, and detonation is provided sequentially in each chamber in one direction in a closed cycle.

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