DE19815723A1

DE19815723A1 - Multistage ramjet engine for propulsion of high-speed aircraft

Info

Publication number: DE19815723A1
Application number: DE1998115723
Authority: DE
Inventors: Herbert Zemann
Original assignee: Individual
Current assignee: Individual
Priority date: 1998-04-08
Filing date: 1998-04-08
Publication date: 1999-10-14

Abstract

A motor-driven axial compressor (2) is mounted at the air inlet of a combustion chamber (4) and its power is sufficient to set the combustion chamber in operation. A short connecting pipe is fitted at the outlet of the combustion chamber, and by its other end the pipe is fitted to the inlet of an additional combustion chamber of the same size. The connecting pipe has air inlet openings which are designed and arranged so that external air is drawn in by passing combustion gases from the combustion chamber.

Description

description

Die Erfindung betrifft ein mehrstufiges Staustrahltrieb werk, zum Antrieb von Luftfahrzeugen. Der Vorteil des Stau strahltriebwerks ist, daß es keine größeren beweglichen Teile hat. Trotzdem findet es fast keine Verwendung, was in erster Linie daran liegt, daß ein Luftfahrzeug, in dem es eingebaut ist, erst eine relativ hohe Geschwindigkeit erreichen muß, bevor das Staustrahltriebwerk funktioniert. Die Erfindung macht es sich zur Aufgabe, diesen Nachteil zu beheben, so daß ein Flugzeug mit einem Staustrahltrieb werk, von einem Rollfeld aus starten kann. Erfindungsmäßig wird dies dadurch gelöst, daß ein, von einem Motor ange triebener Achsialkompressor, Luft in eine Brennkammer drückt, die dort mit Treibstoff angereichert wird. Nach erfolgter Zündung des Gemischs tritt der Strahl aus Ver brennungsgasen aus der Düse der Brennkammer aus, und trifft, nach kurzem Weg durch ein Verbindungsrohr, auf den Luft einlaß einer weiteren, gleich großen Brennkammer. Da der Lufteinlaß kleiner ist, als die Düse der Brennkammer, verengt sich der Weg des Gasstrahls, und es kommt zu einer starken Sogwirkung, so daß Luft aus dem, kurz vor der Verengung in das Verbindungsrohr einmündenden Luftkanal angesaugt wird, die, zusammen mit den Verbrennungsgasen, in Brennkam mer zwei eintritt. Dort wird Treibstoff eingespritzt, und das Gemisch zur Zündung gebracht. Vor den nachfolgenden Brennkammern drei und vier befinden sich ebenfalls Luft einlässe, wo sich der zuvor beschriebene Vorgang noch zwei mal wieder holt. Da die Größe der Brennkammern immer die gleiche ist, die Menge der Verbrennungsgase aber von Brenn kammerstufe zu Brennkammerstufe zunimmt, bleibt den Ver brennungsgasen nur die Möglichkeit, schneller zu werden. Die aus der Düse von Brennkammer vier ins Freie tretenden Verbrennungsgase, haben also eine, im Vergleich zum auslö senden Motor und Kompressor, große Energie. The invention relates to a multi-stage ramjet factory, for the propulsion of aircraft. The advantage of traffic jam jet engine is that there are no major moving Has parts. Still, there is almost no use of what primarily because an aircraft in which it is built in, a relatively high speed must reach before the ramjet works. The invention makes it its task to overcome this disadvantage fix so that an aircraft with a ramjet plant, can start from a runway. According to the invention this is solved in that a, by a motor driven axial compressor, air into a combustion chamber presses, which is enriched with fuel there. After If the mixture is ignited, the jet emerges from Ver combustion gases from the nozzle of the combustion chamber, and hits, after a short distance through a connecting pipe, on the air inlet of another combustion chamber of the same size. Since the Air inlet is smaller than the combustion chamber nozzle, narrowing the path of the gas jet, and there is a strong one Suction effect, so that air from the, just before the constriction sucked into the air duct opening into the connecting pipe which, together with the combustion gases, comes into combustion mer two entry. There fuel is injected, and the mixture ignited. Before the following Combustion chambers three and four are also air inlets where the previously described process is two more catches up again. Because the size of the combustion chambers is always that is the same, but the amount of combustion gases from Brenn Chamber level increases to the combustion chamber level, remains the Ver combustion gases only the opportunity to get faster. Those emerging from the nozzle of combustion chamber four Combustion gases, therefore, have one compared to the trigger send motor and compressor, great energy.

Eingebaut in ein geeignetes Flugzeug, liefert das Stau strahltriebwerk genügend Schub, um dieses, von einem Roll feld aus, zu starben. Mit steigender Geschwindigkeit des Flugzeuges, nimmt der Staudruck der Luft in den, mit ihren Öffnungen in Flugrichtung gerichteten Luftkanälen zu, und damit die Luftzufuhr zu den Brennkammern, was wiede rum eine stetige Leistungssteigerung des Staustrahltrieb werks zur Folge hat. Hat der Staudruck ein bestimmtes Maß erreicht, kann der Kompressor abgeschaltet werden, und die verstellbaren Turbinenschaufeln des Achsialkompressors werden so geschwenkt, daß sie der einströmenden Luft, mög lichst wenig Wiederstand entgegensetzen. Die Anzahl von vier Brennkammern ist willkürlich gewählt, der gewünschte Effekt kann vielleicht auch mit einer anderen Anzahl von Brennkammern erreicht werden. Die Zeichnung zeigt ein Aus führungsbeispiel der Erfindung. Der stromlinienförmig verkleidete Motor 1, mit dem daran angeschlossenen Kom pressor 2, die Einlässe der Luftkanäle 3, die Brennkammern 4, die Lufteinlässe zu den Brennkammern 5, und die Verengungen des Gasstrahls, vor den Brennkammern 6.Installed in a suitable aircraft, the jam jet engine provides enough thrust to die from a taxiway. As the speed of the aircraft increases, the dynamic pressure of the air in the air channels with their openings in the direction of flight increases, and with it the air supply to the combustion chambers, which in turn results in a steady increase in performance of the ramjet engine. Once the dynamic pressure has reached a certain level, the compressor can be switched off, and the adjustable turbine blades of the axial compressor are pivoted in such a way that they oppose the incoming air with as little resistance as possible. The number of four combustion chambers is chosen arbitrarily, the desired effect can perhaps also be achieved with a different number of combustion chambers. The drawing shows an exemplary embodiment of the invention. The streamlined engine 1 , with the connected compressor 2 , the inlets of the air channels 3 , the combustion chambers 4 , the air inlets to the combustion chambers 5 , and the constrictions of the gas jet, in front of the combustion chambers 6 .

Claims

1. Multi-stage ramjet engine for driving aircraft, characterized in that an axial compressor driven by a motor presses air into a combustion chamber, which is enriched with fuel there. After the mixture has ignited, the jet of combustion gases emerges from the nozzle of the combustion chamber and, after a short distance, hits the air inlet of another combustion chamber of the same size through a connecting pipe. Since the air inlet is smaller than the nozzle of the combustion chamber, the path of the gas jet narrows and there is a strong suction effect, so that air is sucked out of the air duct that opens into the connecting pipe shortly before the constriction, which, together with the combustion gases, two enters combustion chamber. Fuel is injected there and the mixture is ignited.

2. Multi-stage ramjet according to claim 1, characterized in that before the subsequent firing chambers three and four also open air inlets, where the process described above occurs two more times repeated.

3. Multi-stage ramjet according to claim 1, characterized in that the size of the four Brennkam is the same, but the amount of combustion gases is of Combustion chamber stage increases to combustion chamber stage, so that the Combustion gases only the possibility remains faster to become. The one from the nozzle of combustion chamber four into the open Coming combustion gases, so have a, in comparison to the triggering motor and compressor, great energy.

4. Multi-stage ramjet according to claim 1, characterized in that the ramjet, a built into a suitable aircraft, this from a standing position, from a runway.

5. Multi-stage ramjet according to claim 1, characterized in that the dynamic pressure of the air in the, with their openings in the direction of flight Air channels, with increasing speed of the aircraft increases, and thus the air supply to the Brennkam mern, which in turn a steady increase in performance of the Ramjet engine results.

6. Multi-stage ramjet according to claim 1, characterized in that when the back pressure is a has reached a certain size, the compressor is shuttered can be tet, and the adjustable turbine blades of the axial compressor are pivoted so that they are the incoming air, as little resistance as possible put.

7. Multi-stage ramjet according to claim 1, characterized in that the number of four focal chambers is chosen arbitrarily, and the desired Maybe with a different number of effects Combustion chambers can be reached.