RU2371599C1 - Hypersonic ramjet engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: hypersonic ramjet engine comprises air intake, concurrent combustion chamber and fuel feed system. Jet supercharger is mounted at the concurrent combustion chamber inlet and aligned with it. Separating nozzle is arranged between air intake and combustion chamber.

EFFECT: longer life.

4 cl, 5 dwg

Description

The invention relates to all branches of technology where it is possible to use a hypersonic air jet, in particular to aircraft engine building, in particular to hypersonic ramjet engines, which can also be used for fire fighting equipment, namely, devices for extinguishing burning fountains (torches) on gas, oil and gas wells, etc.

Known extinguishing device according to the patent of the Russian Federation N2039212. The fire extinguishing device of the fountain is designed so that exhaust fire-extinguishing jets of turbojet engines are fed into the combustion zone, which are placed evenly along the ring relative to the axis of the torch, and the jets are directed in pairs towards one another at the same angles relative to the torch, ensuring the jets are in contact. This device has inherent disadvantages - the complexity and cumbersome means of extinguishing, the impossibility of full automation.

The well-known design of ramjet engine (ramjet), consisting of an air intake, a combustion chamber and an accelerating nozzle. A disadvantage of the known device is an auxiliary start and the inability to use at subsonic speeds.

The well-known design of a gas turbine engine, consisting of an air intake, an axial compressor, a combustion chamber, an axial turbine, sometimes an afterburner and an accelerating nozzle. A disadvantage of the well-known device is low resource, high gyroscopic moment, high cost and high drag.

A known design of a hypersonic ramjet engine consisting of an air intake, a ramjet combustion chamber and a fuel supply system, see, for example, RU 2262000.

A disadvantage of the known device is an auxiliary start and the inability to use at subsonic speeds.

An object of the invention is to increase operational characteristics while reducing cost and increasing the resource of work.

The problem is solved by creating a hypersonic ramjet engine with an air intake, a ramjet combustion chamber and a fuel supply system, while an additional jet jet is installed coaxially with the ramjet combustion chamber, and the air intake is separated from the combustion chamber by a separation nozzle.

A nozzle is installed coaxially with the direct-flow combustion chamber at the outlet, which regulates the pressure in the combustion chamber.

In the combustion chamber, power is taken to power the jet supercharger.

Additionally, there is a gas transformer with a check valve, a receiver, a gas switch and a start-up system.

The invention is illustrated by drawings, which depict:

figure 1 - hypersonic ramjet jet engine with a jet supercharger (GPVRDSN) in idle mode;

figure 2 - GPVRDSN, operating in a subsonic mode;

figure 3 - GPVRDSN, operating in supersonic mode;

4 is a gas transformer;

5 is a fuel valve fuel switch with an accelerator valve and an ejector.

A hypersonic ramjet jet engine with a jet supercharger (GPVRDSN) does the job, creating a jet stream.

GPVRDSN can work in three main modes, not counting the transient modes, these are: idling (Fig. 1.); working stroke (Fig.2.); working stroke at speeds above sound (Fig.3.).

Consider the design and functional purpose of the nodes scramjet (figure 1, figure 2, figure 3). Through the air intake 1 and the jet pump 2, in which the fuel is ejected, atmospheric air enters the scrubber into the separation nozzle 3. During idling and subsonic operation, air is fed to the separation nozzle by the jet of the supercharger 8, and at supersonic speeds due to the oncoming flow . Through the separation nozzle 3, the working mixture enters the combustion chamber 4, where during combustion it increases in volume. It should be noted that this is a multi-fuel design, at idle, it is preferable to burn high-octane heavy boiling gasoline, in proportion to solar oil or kerosene. In the operating mode, the optimal work on gas is methane, propane, butane or mixtures thereof. In supersonic mode, it is necessary to switch to a methane-hydrogen mixture, and in hypersound, to hydrogen. The primary fuse of the combustible mixture can be produced using a glow plug installed in the combustion chamber 4. A constant pressure of 8-10 kgf / cm ^{2 is} maintained in the combustion chamber due to the design of the nozzle 5, consisting of refractory plates 10 and calibrated springs 9. From the combustion chamber 4 part of the exhaust gases (and at idle, the entire exhaust volume) is taken through the exhaust channel 6 and fed to the gas transformer 7. In it, due to the accelerating nozzle 14, 15 (Fig. 4) and the reversal of the large mass gas flow on the braking cone 16, 17 formed mpuls compression on a small portion of high-pressure gas pipe 18, 19, about 1/5, but with a pressure of about 40 kgf / cm ^2. In the pipe 19, a check valve can be installed at low flow rates of the jet supercharger. Part of these gases after start is taken through the start valve 12, into the receiver 13 for subsequent pneumostart, and in general this gas goes to the Laval nozzle of the jet blower 8 of the jet pump 2.

All elements of the scramjet are connected in a single housing 11.

Figure 5 shows the fuel switching valve, which when it reaches 4 kgf / cm ² in the air intake and up to 10 kgf / cm ² inclusive carries out a proportional change of fuel according to a linear function.

The combustion zone in Fig.1-3 is indicated by the inscription "Heat Supply".

The fuel ejection zone is not shown, but is located in the area of the jet pump in the form of holes that inject perpendicular to the axis of the jet supercharger.

For the manufacture of the device, an oxide-resistant mirror foil of 0.1-0.3 mm is used, made of steel 12X18H10T according to GOST 5632-72. All connections are made by contact spot and roller welding. The internal high-temperature surfaces are coated with yttrium stabilized zirconia. Piping is made of steel seamless corrosion-resistant pipes according to GOST 9941-81. The nozzle shell 3 is made according to a multi-plate scheme, where the plates are spring-loaded due to their own elasticity and work according to the cantilever beam scheme, which is welded to the body by spot welding. In the fuel switching valve of FIG. 5, consisting of a housing 20, a spool with a control piston 21, the spring 22 needs to be carefully calibrated. Instead of springs 9, it is permissible to install pneumatic spring cylinders, in which at supersonic speeds it is permissible to relieve pressure with the formation of an inverse cone.

This device allows you to more efficiently create a hypersonic air stream, which is also relevant for aircraft engine building and industries where the use of a jet stream is possible.

Claims (4)

1. A hypersonic ramjet engine having an air intake, a ramjet combustion chamber and a fuel supply system, characterized in that a jet supercharger is additionally installed coaxially with the ramjet combustion chamber, and the air intake is separated from the combustion chamber by a separation nozzle. 2. The engine according to claim 1, characterized in that a nozzle controlling the pressure in the combustion chamber is installed coaxially with the once-through combustion chamber at the outlet. 3. The engine according to claim 1, characterized in that in the combustion chamber, power is taken to power the jet supercharger. 4. The engine according to claim 1, characterized in that it further has a gas transformer with a check valve, a receiver, a gas switch and a start-up system.

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