DE4402941B4 - Combined engine with integrated working methods as ejector for turbocharged, cooled or liquefied air, as a ramjet engine and as a supersonic ramjet engine - Google Patents

Abstract

combined Engine with integrated working methods as ejector for turbocharged, cooled or liquefied Air, as a ramjet engine and as a supersonic ramjet engine, characterized in that the Motor comprises a main current (1), an air inlet (110), which comprises a converging part (111) and a neck (112), a Main combustion chamber (120) and an ejection nozzle (130) that the engine also a secondary current (2) one inlet (180) which is upstream from the neck (112) of the air inlet (110) of the main stream (1) is located and has movable flaps (161), in turn of air cooling or air liquefaction pipes (163) crosses and for regulating the amount of air entering the secondary flow (2) optionally in various positions, including a position of complete closure, can be brought, wherein the secondary flow (2) comprises the following elements: a Cryogenic Compressor (210), which feeds into the inlet (180) of the secondary current (2) introduced, chilled or liquefied Ingesting air, an ejector combustion chamber (220) containing fuel and with in the cryogenic compressor (210) compressed, cooled or ...

Description

The The invention relates to a combined engine according to the preamble of patent claim 1. This engine integrates at least one mode of operation Ejector accelerator for turbocharged, refrigerated or liquefied Air, a way of working as a ramjet engine with combustion at subsonic speed and a mode of operation as a supersonic ramjet engine with a combustion at supersonic speed. Such a combined engine can be at a supersonic speed Apply moving, aerobic vehicle and allows it with the help a single step, starting from a height Z = 0, a speed from Mach 15 and then to reach an earth orbit.

In an essay by Nobuhiro TANATSUGU, published in SAE Technical Paper Series, April 1990 entitled "Development Study on Expander Cycle Air Turbo-Ramjet with intake Air Cooler for space Plane "has already been launched Embodiment of a Motors proposed the first stage of a vehicle with two forms combined stages. This article specifically describes an engine in the form of a chilled air dam, wherein in the combustion chamber a heat exchanger is available. Such an engine does not show the combination of at least three successive, different ways of working within a spacecraft with a single stage are integrated.

you has already suggested, in an aerobic spacecraft a cooling the trapped air during the course of Acceleration phase by heat exchange with liquid Hydrogen.

The DE 36 17 757 C1 discloses an air-breathing missile propulsion system in which in the air-breathing propulsion phase, the oxygen contained in the atmosphere as an oxidant and in the outside air-independent propulsion phase in the spacecraft entrained oxidizer allows the combustion process in the combustion chamber of the rocket engine. The airflow entering the rocket propulsion system through air inlet doors passes through a main compressor and is subsequently split, with the larger portion passing directly into a combustion chamber via a regenerative precooler, while the smaller portion is fed to a high pressure compressor stage and also from there through the regenerative precooler into a high pressure gas generator where a gaseous fuel burns with the injected partial air stream. The pre-combusted fuel-rich gas drives a main turbine, from which it is passed into the combustion chamber, where it burns with the larger, directly fed via the regenerative pre-cooler air partial flow and expands in a combustion chamber associated with the exhaust nozzle.

The DE 40 16 897 C1 discloses a method for recovering liquid oxygen from pent-up and cooled ambient air in aircraft moving at high velocity in the atmosphere. The recovered liquid oxygen can be stored in a tank or fed directly to an engine.

The DE 39 12 331 A1 discloses an integrated turbocharged turbojet engine comprised of a gas turbine engine having a compressor, combustor, and turbine and a ramjet engine mounted in parallel therewith, both engines being alternatively closeable via flaps, such that the air entering through the air intake is either the gas turbine engine, the ramjet engine, or both can be fed.

It The object of the invention is to realize a combined engine, its structure is optimized and the complete integration of various Includes operating modes. This combined engine is still a small footprint and have a low weight.

The object is achieved by a combined engine with integrated operations as an ejector for turbocharged, cooled or liquefied air, as a ramjet engine and as a supersonic ramjet engine, which is characterized in that it comprises a main stream having an air inlet, a converging part and a Neck, having a main combustion chamber and a discharge nozzle, and further comprising a secondary flow having an inlet located upstream of the throat of the main air intake and having movable flaps which in turn are traversed by air cooling or air liquefaction conduits and for regulating the flow in the secondary flow entering air quantity are optionally in different positions, including a position of complete closure, can be brought, the secondary flow comprising the following elements: a cryogenic compressor, which in the inlet of the secondary flow introduced, cooled or liquefied air, an ejector combustion chamber, which is fed with fuel and in the cryogenic compressier ter, cooled or liquefied air, and the drive of the cryogenic compressor serving turbine, which is fed with combustion gases, which in turn generated in the Ejektorbrennkammer and are discharged after leaving the turbine via a set of nozzles in the main combustion chamber of the main stream, so that the motor is successively operable in the following ways: via the secondary flow as an ejector for turbocharged, cooled or liquefied air, wherein the movable flaps are in the open position, via the main flow as a ramjet with subsonic combustion, wherein the movable flaps can be successively first in the open and then in the closed position, and the main flow as a supersonic ramjet engine with supersonic combustion, with the movable flaps closed.

The air cooling or air liquefaction pipes, which are associated with the movable flaps are starting fed by a reservoir with combustible fuel, wherein the flammable fuel leaving the cooling ducts during the Operation as ejector for turbocharged, refrigerated or liquefied Air of the supply of the ejector combustion chamber with fuel is used.

During the Operation as ramjet engine with subsonic combustion Means are provided to keep the movable flaps open and around an intermediate reservoir cooled air, over the movable flaps in the inlet of the secondary flow introduced will liquefy and store, with the combustible fuel, the cooling lines leaves, to Supply of the main combustion chamber with fuel is used.

Preferably be while working as an ejector for turbocharged, cooled or liquefied Air the combustion gases formed in the ejector combustion chamber in the main stream over Nozzles introduced in retractable Intermediate plates are arranged during the operation as Ramjet engine with supersonic combustion at least partially withdrawn are.

As well is during the operation as a ramjet engine with subsonic combustion a combustible fuel into the main stream via retractable intermediate plates arranged arranged nozzles, the while the working phase as a ramjet engine with supersonic combustion at least partially withdrawn are.

The movable flaps are constructed stepwise and in the flow direction arranged in front of a neck of the air inlet in the main stream.

The Ejector combustion chamber is between the cryogenic compressor and arranged the turbine.

Of the combined engine can be an additional heat exchangers include that in secondary current in the flow direction is arranged behind the movable flaps and air cooling or Air liquefaction lines which are crossed by a combustible fuel.

Preferably are the cooling pipes of the additional heat exchanger fueled by combustible fuel coming from the air cooling lines exit, which cross the movable flaps.

Of the combined engine can also at least one conventional one Rocket motor comprise, starting from reservoirs with liquid fuels fed and has a widening nozzle part, which is in itself expanding part of the discharge nozzle of the main stream opens.

Optional For example, the combined engine may be charged with liquid oxygen Reservoir to cover during working as an ejector for turbocharged, refrigerated or liquefied Air an extra Amount of oxygen in the Ejektorbrennkammer, during the operation as a supersonic ramjet engine an additional Amount of oxygen in the main combustion chamber and otherwise an amount of oxygen in the conventional engine to inject.

Further can Means be provided to during the way of working as a supersonic ramjet engine combustible fuel into the main combustion chamber both axially and inject orthogonally.

For example The combined engine can be used as an ejector for turbocharged, cooled or liquefied Air between the speeds of Mach 0 and about Mach 2, as a ramjet engine with subsonic combustion between the Speeds of about Mach 2 and Mach 6, as a supersonic ramjet engine between the speeds of about Mach 6 and Mach 15 and else as Rocket engine above a speed of Mach 15 work.

thanks the presence of a secondary current with a stem and movable flaps that are active during the aerobic phase be cooled by the combustible fuel, which subsequently in the Air injectors or burned in the main stream, you get at the same time an increase the amount of air trapped, a reduction in the external resistance and an increase the thrust.

by virtue of the achieved coupling between the organs, the way of working As an ejector ensure, and the main stream, for the operation as a ramjet available stands, the space requirement and the mass of the arrangement are smaller as at complete separate units.

Further features and advantages of the invention will become apparent from the following description of preferred embodiments, which are given by way of example and not limitation of the invention thereto, in conjunction with the accompanying drawings. Show it:

1 a block diagram showing various elements which essentially form a combined engine according to the invention, and

2 a schematic view showing an installation example for the various elements that make up the combined engine according to the invention.

1 shows the general arrangement of the main elements, which form a combined engine according to the invention, during 2 the positions of the various elements that make up the engine can be seen with respect to each other.

Of the Combined engine according to the invention, the Completely integrated and comprises a single main exit thrust nozzle, it is possible to with a single step from the ground to an earth orbit to get.

• a) eine Arbeitsweise als Rakete mit gekühlter oder verflüssigter Luft (auch Arbeitsweise als Ejektor für turbokomprimierte, gekühlte oder flüssige Luft genannt), die parallel mit einer Arbeitsweise als Staustrahltriebwerk mit Unterschallverbrennung arbeitet, und zwar bei Geschwindigkeiten zwischen Mach 0 und etwa Mach 2,5;
• b) eine Arbeitsweise als Staustrahltriebwerk mit reiner Unterschallverbrennung bei Geschwindigkeiten zwischen etwa Mach 2,5 und Mach 6.

The mode of operation of the combined engine comprises a first acceleration phase which, in terms of the speeds achieved, is between Mach 0 and Mach 6 and in turn subdivides into two modes of operation:

• a) operating as a rocket with cooled or liquefied air (also referred to as an ejector for turbocharged, cooled or liquid air) operating in parallel with a subsonic combustion ramjet engine operating at speeds between Mach 0 and Mach 2.5 ;
• b) an operation as a ramjet engine with pure subsonic combustion at speeds between about Mach 2.5 and Mach 6.

At the acceleration phase closes a way of working as a ramjet engine with supersonic combustion (or operation as a supersonic ramjet engine) on, for Speeds between Mach 6 and Mach 15.

A classic or conventional liquid fuel propellant phase (eg, liquid oxygen and a combustible fuel) may take the place of the supersonic ramjet engine, in the speed range above Mach 15 to Earth orbit via a conventional rocket motor 300 , a combined engine 100 assigned.

Looking at the 1 and 2 it can be seen that the combined engine is essentially a main flow or main flow 1 , which is used for the operation as a ramjet with combustion at subsonic speed and for the operation as a ramjet with combustion at supersonic speed. Further, the combined engine includes a secondary flow passage or secondary flow 2 which functions as an ejector for turbocharged, cooled or liquefied air.

The main stream 1 includes an air inlet 110 , a main combustion chamber 120 and an ejection nozzle 130 , The inner part of the air inlet 110 has a converging part 111 on that in a neck 112 ends.

The secondary current 2 is outside the main stream 1 and has a stem 181 on that together with the outer wall of the air inlet 110 an air intake 160 in the secondary stream 2 certainly. Part of the air, which is in the main stream 1 over the converging part 111 the air intake 110 is taken over openings 113 in the secondary stream 2 introduced. The openings 113 are in the converging part 11 the air intake 110 left out and can be wholly or partly by a sentence 160 movable flaps 161 which in turn are perpendicular to the longitudinal axis X'X of the main stream 1 directed axes 162 are pivotable. The flaps 161 are gesteu ert on a not shown on the drawing linkage. Air cooling or air liquefaction 163 comprising a set of tubes are the flaps 161 assigned to simultaneously the flaps 161 and to cool the air of the main stream passing through the openings 113 is caught, so the secondary current 2 to dine. The cooling pipes 163 are advantageously starting from a reservoir 140 over a line 141 supplied with a combustible propellant.

The flammable propellant, which comes from the cooling lines 163 the arrangement 160 the movable flaps 161 comes from a single line 145 in an additional heat exchanger 170 be introduced, in the secondary stream 2 in the flow direction behind the movable flaps 161 is arranged, in turn, in the inlet 180 of the secondary current 2 so as to more strongly cool or liquefy the air introduced into the secondary stream before entering a cryogenic compressor 210 which in turn passes through a turbine 230 is driven. This turbine 230 is fed with combustion gases in an ejector combustion chamber 220 generated, in turn, between the compressor 210 and the turbine 230 lies.

The through the cryogenic compressor 210 turbocharged air is released this way cooled very low temperature or through the heat exchanger 160 . 170 liquefied before using the cryogenic compressor 210 passes.

The trapped air can also pass through the passage of a separator 190 enriched, which allows to withdraw nitrogen molecules from the air, so that air with a larger proportion of oxygen results. The separator 190 For example, between the heat exchangers 160 and 170 to be ordered.

The ejector combustion chamber 220 is supplied with combustible propellant via a pipe 149 fed by the cooling lines 163 goes out, as well as with air passing through the cryogenic compressor 210 cooled or liquefied. If an additional heat exchanger 170 Applicable, can originate from this heat exchanger combustible propellant also serve the ejector combustion chamber 220 over the wires 146 and 147 to dine.

If necessary, even liquid oxygen from a reservoir 152 over a pipeline 155 into the ejector combustion chamber 220 be initiated.

The from the turbine 230 escaping gases pass through a pipe 231 in a buffer chamber 243 and are about a sentence 240 of nozzles 242 into the main combustion chamber of the main stream 1 pushed out.

The buffer chamber 243 can also be fed with combustible propellant, either directly from the reservoir 140 over the pipeline 142 or over the pipeline 148 starting from the cooling lines 163 and the additional heat exchanger 170 ,

The gases or the flammable propellant that enters the buffer chamber 243 be discharged into the main combustion chamber 120 ejected from the main stream, which in turn is supplied via the air inlet with air. The ejection takes place via the sentence 240 the nozzles 242 , The nozzle set is preferably on retractable intermediate plates 241 mounted, which allow the nozzles 242 either completely or only partially into the main stream 1 exit or are completely withdrawn into the space from the buffer chamber 243 is formed.

A small independent nozzle 250 passing through the pipeline 143 is fed with combustible propellant, allows the axial injection of combustible propellant at the level of the main combustion chamber 120 at the beginning of the diverging part of the nozzle 130 regardless of or in combination with the sentence 240 the retractable nozzles 242 , depending on the current working phase of the engine.

It is of course possible to provide several ejectors, which have several secondary currents 2 be fed, the latter being aligned above and with one or more main currents. In this case, the various ejectors, which in particular a turbocompressor 210 . 230 and an ejector combustion chamber 220 have identical structures and functions such that it suffices to refer in the following only to a single ejector.

A conventional rocket engine 300 can optionally be added to the combined engine according to the invention. The rocket engine 300 includes a combustion chamber 310 and a nozzle with a sonic neck 320 and a diverging section 330 which is integrated in a rear body of the vehicle and in the diverging part of the main nozzle 130 opens. The rocket engine 300 is starting from the reservoir 140 over the pipeline 144 fed with combustible propellant, as well as from the group of reservoirs 150 with liquid nitrogen. The group of reservoirs 150 can be a reservoir 151 which serves to receive the liquid air that is in the secondary stream 2 after passing the heat exchanger 160 which in turn forms the cooled flaps 161 and the additional heat exchanger 170 includes, as well as a reservoir 152 , which contains liquid oxygen, which is stored at the start. The liquid oxygen gets into the injector of the combustion chamber 310 of the rocket engine 300 introduced, starting from the reservoirs 151 and 152 over pipelines 153 and 154 ,

The Flammable propellant may for example be liquid hydrogen or a Hydrogen sludge, which is also referred to as hydrogen "slush".

below will the operation of the combined engine according to the invention described in his various work phases.

When working as an accelerator during a first phase, the movable flaps 161 of the secondary current 2 in open position (Mach 0 to about Mach 2.5). Part of the air intake 110 trapped air thus enters the secondary stream 2 ,

The main heat exchanger 163 that in the movable flaps 161 are arranged cool this amount of air. If necessary, an additional heat exchanger 170 in the secondary stream 2 integrated to lower the temperature of the trapped air to the required level or one Air liquefaction effect.

The cooled or liquefied air in this way is then in the cryogenic compressor 210 compressed and into the combustion chamber 220 of the ejector, where it is combusted together with combustible fuel that has served it in the heat exchangers 160 . 170 to cool or liquefy.

As already stated above, an amount of oxygen can also enter the chamber 220 over the pipeline 155 be injected and burned together with air and combustible propellant to recover a possible thrust delta.

The combustion gases are then in the turbine 230 partially relaxed, which is the cryogenic compressor 210 in an expansion-type cycle. Subsequently, these gases are in the main stream 1 ejected (ramjet stream), through the nozzles 242 in the retractable intermediate plates 241 are arranged.

The through the main stream 1 trapped air quantity is in the main combustion chamber 120 of the ramjet together with the gases burned by the ejector of the secondary flow 2 come here, and incidentally with a share of combustible propellant.

Near Mach 2.5 becomes the ejector of the secondary flow 2 for cooled or liquefied air extinguished, and the ejector combustion chamber 220 , which is no longer supplied with fuel, and the accelerator are in the working phase of the ramjet with subsonic combustion.

Two Options are now possible.

In the first case, the movable flaps 161 closed and in the air intake 110 Trapped air is completely burned with combustible propellant, which is deposited on the retractable intermediate plates 241 arranged nozzles 242 is injected.

In the second case, the movable flaps remain 161 opened while working as a ramjet with subsonic combustion.

The secondary current 2 trapped air quantity is then cooled and liquefied so that it is in an intermediate reservoir 151 can be stored. It serves as an oxidant in the pure rocket mode in the rocket engine 300 ,

The rest of the air intake 110 trapped air is in turn burned in the main stream together with the combustible propellant, which is the liquefaction of the air of the secondary stream 2 has served and over in the retractable intermediate plates 241 arranged nozzles 242 was injected.

In both cases, the operation continues as a ramjet engine with subsonic combustion to near Mach 6. Starting from about Mach 6, the operation goes into that of a ramjet engine with combustion at supersonic speed (so-called "supersonic ramjet"). If the movable flaps 161 have remained open, they now go to the closed state.

• – Ausstoß einer vorverbrannten Mischung aus brennbarem Treibmittel und H₂O mit Hilfe von Einspritzeinrichtungen. Die Einspritzung wird mit Hilfe kleiner Raketenmotoren realisiert. Die hohe Temperatur der injizierten Gase (> 1000° K) und die Anwesenheit von Radikalen (OH) gestatten es, die Verbrennung von Luft/brennbares Treibmittel einzuleiten. Dieses Verfahren erfordert dennoch die Bereitstellung von Sauerstoff (Reservoir 152), wobei dieser Sauerstoff auch für ein Funktionieren des Motors während der Arbeitsweise als Raketenmotor am Ende des Raumfluges dient.
• – Thermische Selbstentzündung einer brennbaren Mischung. Diese hängt im wesentlichen von der Temperatur und dem Druck der Mischung sowie von deren Anreicherung ab. Eine Mischung brennbares Treibmittel/Luft entzündet sich spontan, wenn es möglich ist, sie lokal auf ihrer thermischen Selbstentzündungstemperatur zu halten. Diese Temperatur ist im allgemeinen stromabwärts einer Stoßwelle leicht zu erreichen. Der Nachteil dieses Vorgehens liegt im vollständigen Druckverlust, wie er durch die Stoßwelle erzeugt wird. Um einen beschränkten Einfluß auf die Leistungsdaten zu haben, muß diese Bildung einer Stoßwelle lokal sein und kann durch einen Mach-Effekt über eine Mach-Scheibe realisiert werden, die auf das Ausströmen der Luft eine starke Verzögerung wenigstens in einer mittleren Zone erzeugt.

To facilitate the start of operation as a supersonic ramjet engine, a pilot flame may be used, which may be obtained by the following means:

• - Output of a pre-combustible mixture of combustible propellant and H ₂ O by means of injectors. The injection is realized by means of small rocket engines. The high temperature of the injected gases (> 1000 ° K) and the presence of radicals (OH) allow the combustion of air / combustible propellant to be initiated. Nevertheless, this process requires the provision of oxygen (reservoir 152 ), which also serves to operate the engine during operation as a rocket engine at the end of spaceflight.
• - Thermal self-ignition of a combustible mixture. This depends essentially on the temperature and the pressure of the mixture and their enrichment. A mixture of flammable propellant / air spontaneously ignites when it is possible to keep it locally at its thermal autoignition temperature. This temperature is generally easy to reach downstream of a shock wave. The disadvantage of this approach is the complete pressure loss, as generated by the shock wave. In order to have a limited influence on the performance data, this formation of a shock wave must be local and can be realized by a Mach effect on a Mach disk which produces a strong deceleration at least in a central zone upon the outflow of air.

The Temperature and the pressure of the outflow are then sufficient high to locally stabilize the combustion.

The reactive zone plays the role of a pilot flame for the remainder of the outflow.

Since the temperature shutdown to the Zwi rule plates 241 for which durability is prohibitive, they are partially withdrawn, but a wall injection point for combustible propellant is maintained.

This Injection point allows to obtain a stable supersonic combustion, independently of, like the discharge velocity is, especially at high Mach number.

The Working phase as ramjet engine with supersonic combustion sets up close from Mach 15 onwards.

The Air volume is growing with the Mach number of the flight. With iso-enrichment, therefore, the amount of flammable grows Propellant with the Mach number of the flight. With small Mach number of Flight is the accumulation of the mixture near 1, and it may be the total amount of combustible propellant injected to be burned. A better combustion efficiency will be obtained by orthogonal injection (which improves the quality of the mixture).

On the other hand At high Mach number, only part of the injected combustible becomes Blowing agent burned. The rest takes part in the combustion phenomena do not participate and behave like a kind of inertia. As the temperature at the inlet of the Combustion chamber is high, occur numerous dissociation phenomena (endothermic Reactions) within the effluent in the course of the burning up.

There the average gas velocity within the combustion chamber is high, the residence time is low. This results in a reduction of Effectiveness of combustion.

Under these circumstances is the orthogonal injection that allows good mixing and combustion conditions to receive, no longer necessary. The axial injection gives then the possibility exploit the axial injection dynalpie of the combustible propellant.

It is nevertheless to be found that a Part of the combustible propellant are injected orthogonally can (stoichiometric Amount), the rest is injected axially.

From Mach 15 continues the still existing mode of operation as a ramjet engine with supersonic combustion The thrust continues and pushes the vehicle into orbit.

A different possibility may be in the injection of oxygen during the end of the aerobic phase consist.

This oxygen injection from the reservoir 152 It makes it possible to free itself from the presence of a rocket motor, which might be required at the end of the flight. This injection allows the aerobic engine to function in layers of the atmosphere that have a very low density.

On otherwise it allows the stored cold oxygen (91 ° K), the supplied air to cool. The combustion temperature is therefore less high, the dissociation phenomena are less significantly and the effectiveness of combustion is growing.

If it still proves necessary, one uses for the end the trajectory of Mach 15 to the Earth's orbit a conventional Rocket engine LOX / flammable propellant.

Throughout the aerobic phase, the stem and air intake (set 160 the flaps 161 ) is actively cooled, using the combustible propellant, which subsequently either in the Luftejektorbrennkammer 220 or in the mainstream 1 is burned.

These Cooling allows an increase in the trapped air quantity, a reduction of the external resistance by reduction the thickness of the boundary layer and a delay of the transition laminar-turbulent, an increase the total enthalpy of the flammable propellant, what it does by a appropriate relaxation allows the amount of movement of the combustible Injecting agent during injection and thus to increase the thrust.

Claims (13)

Combined engine with integrated operation as an ejector for turbocharged, cooled or liquefied air, as a ramjet engine and as a supersonic ramjet engine, characterized in that the engine has a main flow ( 1 ) comprising an air inlet ( 110 ), which has a converging part ( 111 ) and a neck ( 112 ), a main combustion chamber ( 120 ) and an ejection nozzle ( 130 ), the motor further comprises a secondary current ( 2 ) having an inlet ( 180 ), which upstream of the neck ( 112 ) of the air intake ( 110 ) of the main stream ( 1 ) and movable flaps ( 161 ), which in turn are supplied by air cooling or air 163 ) and to regulate into the secondary flow ( 2 ) entering air in different positions, including a position of complete closure, can be brought, wherein the secondary flow ( 2 ) comprises the following elements: a cryogenic compressor ( 210 ) in the inlet ( 180 ) of the secondary stream ( 2 ) introduced, ge cooled or liquefied air, an ejector combustion chamber ( 220 ) with fuel and with in the cryogenic compressor ( 210 compressed, cooled or liquefied air, and a turbine serving the drive of the cryogenic compressor ( 230 ), which is fed with combustion gases, which in turn in the Ejektorbrennkammer ( 220 ) and after leaving the turbine ( 230 ) about a sentence ( 240 ) of nozzles ( 242 ) into the main combustion chamber ( 120 ) of the main stream ( 1 ), so that the motor can be operated successively in the following ways: via the secondary flow as an ejector for turbocharged, cooled or liquefied air, wherein the movable flaps ( 161 ) are in open position, over the main stream ( 1 ) as a ramjet engine with subsonic combustion, wherein the movable flaps ( 161 ) successively first in the open position and then in the closed position, and via the main flow ( 1 ) as a supersonic ramjet with supersonic combustion, the movable flaps ( 161 ) are closed. Engine according to claim 1, characterized in that the air cooling or air liquefaction lines ( 163 ), which the movable flaps ( 161 ), starting from a reservoir ( 140 ) are fed with combustible fuel, wherein the combustible fuel, which the cooling lines ( 163 ) leaves during operation as an ejector for turbo-compressed, cooled or liquefied air of the supply of the ejector combustion chamber ( 220 ) with fuel. Engine according to claim 2, characterized in that means are provided during operation as a ramjet engine with subsonic combustion in order to move the movable flaps ( 161 ) and in an intermediate reservoir ( 151 ) cooled air coming in through the movable flaps ( 161 ) into the inlet of the secondary flow ( 2 ) is liquefied and stored, the flammable fuel 163 ) leaves, for feeding the main combustion chamber ( 120 ) with fuel. Engine according to one of claims 1 to 3, characterized in that during operation as an ejector for turbocharged, cooled or liquefied air in the Ejektorbrennkammer ( 220 ) formed combustion gases into the main stream ( 1 ) via nozzles ( 242 ) inserted in retractable intermediate plates ( 241 ) are arranged, which are at least partially withdrawn during operation as a ramjet with supersonic combustion. Engine according to one of Claims 1 to 4, characterized in that, during operation as a ramjet engine with subsonic combustion, a combustible fuel is injected into the main flow ( 1 ) via retractable intermediate plates ( 241 ) arranged nozzles ( 242 ) is introduced, which are at least partially withdrawn during the working phase as a ramjet with supersonic combustion. Engine according to one of claims 1 to 5, characterized in that the movable flaps ( 161 ) constructed stepwise and in the flow direction in front of a neck ( 112 ) of the air intake ( 110 ) in the main stream ( 1 ) are arranged. Engine according to one of claims 1 to 6, characterized in that the ejector combustion chamber ( 220 ) between the cryogenic compressor ( 210 ) and the turbine ( 230 ) is arranged. Engine according to one of claims 1 to 7, characterized in that it comprises an additional heat exchanger ( 170 ), which in the secondary flow ( 2 ) in the flow direction behind the movable flaps ( 161 ) and having air cooling or air liquefaction conduits traversed by a combustible fuel. Engine according to claim 8 and one of claims 2 or 3, characterized in that the cooling ducts of the additional heat exchanger ( 170 ) are fed starting from combustible fuel, which from the air cooling lines ( 163 ), which the movable flaps ( 161 ) cross. Engine according to one of claims 1 to 9, characterized in that it also comprises at least one conventional rocket motor ( 300 ) starting from reservoirs ( 140 . 151 . 152 ) is fed with liquid fuels and a widening nozzle part ( 330 ), which in the widening part of the ejection nozzle ( 130 ) of the main stream ( 1 ). Engine according to any one of Claims 1 to 10, characterized in that it contains a reservoir of liquid oxygen ( 152 ), during operation as an ejector for turbo-compressed, cooled or liquefied air, an additional amount of oxygen into the ejector ( 220 ), while operating as a supersonic ramjet an additional amount of oxygen in the main combustion chamber ( 120 ) and otherwise an amount of oxygen in the conventional engine ( 300 ) to inject. Motor according to one of Claims 1 to 11, characterized in that it comprises means ( 240 . 250 ) during operation as a supersonic ramjet combustible fuel into the main combustion chamber ( 120 ) both axially and orthogonally. Motor according to one of claims 1 to 12, characterized that he as an ejector for turbocharged, refrigerated or liquefied Air between the speeds of Mach 0 and about Mach 2, as a ramjet engine with subsonic combustion between the Speeds of about Mach 2 and Mach 6, as a supersonic ramjet between the speeds between about Mach 6 and Mach 15 and otherwise works as a rocket engine above a speed of Mach 15.