DE3835489A1 - Use of additive mixtures as a means for increasing the vaporisation rate and combustion rate and also the combustion stability of liquid propellants and fuels injected into rocket combustion chambers or high-performance combustion installations - Google Patents

Abstract

Additive mixtures which consist of a) organic compounds with highly conjugated pi -bond systems and longwave main absorption bands in the wavelength range from about 350 to 1200 nm, b) organic surface-active substances and c) organic solvents and suspending agents for the components a and b, are used as agents for increasing the vaporisation rates and combustion rates and also the combustion stabilities of liquid propellants or fuels and oxidisers for rocket engines or other high-performance combustion installations which are likewise operated with liquid fuels and in which there are combustion problems comparable to those in rocket engines and caused by disturbances in energy transfer. The additive mixtures are injected into the combustion chamber together with the propellants or fuels and the oxidisers with uniform distribution, which is as symmetrical as possible, in a geometrically optimum manner in accordance with defined economical methods. Owing to their property of exchanging radiation energy, highly conjugated pi -bond systems effect in combination with surface-active substances faster, more uniform activations of major fractions of molecules participating in the combustion up to the stage of the state ready for reaction, which is tantamount to enhanced stabilisation of the combustion process.

Description

The invention relates to the use of additive mixtures consisting of yellow to deep black colored organic compounds with highly conjugated π- binding systems, surface-active organic substances and organic solvents or suspending agents as agents for increasing the evaporation and combustion rates of liquid fuels, including, if appropriate, the liquid Oxidators and the resulting increase in the stability of the combustion process taking place in rocket combustion chambers and similar high-performance combustion plants.

In general and from the patent literature, it is known to use organic dyes with highly conjugated π- binding systems, in particular azo dyes, disazo dyes or anthraquinone dyes, as additives for coloring fuels, in particular jet fuels, gasoline fuels, diesel oils, gas oils and heating oils, etc. for the purposes of labeling, marking or to use classification of mineral oil or synthetic products (see also DE-PS 15 45 246, GB-PS 11 08 981, US-PS 34 76 500, 34 94 714, 40 09 008, 40 49 393, 40 56 367, 40 82 501, 43 15 756, DE-AS 22 11 182, 23 33 358), but the relevant literature does not show the use according to the invention of colored organic compounds in combination with surface-active substances, which is based on a completely different task and problem .

A problem that the experts have not yet encountered was often not a satisfactory solution trouble-free sequence of the combustion process in the Combustion chambers of liquid rockets. Type, scope, Causes and effects of malfunctions that occur can be very different, possibly also be complex in nature. Parallel or successive  Cause various disorders to occur possibly, sometimes in synergistic effects, the failure of important functional elements, even aggregates, which in the case of liquid rocket engines for Failure of a space mission can result. The diversity of sources of interference and which can potentially resulting from faulty procedures its negative technical and economic consequences make it necessary any possibility of Eliminate the causes of the disrupted technical Functions, but at least reducing the susceptibility to faults to fully utilize the individual functional units.

A relevant functional system in engines for liquid rockets represent the liquid fuel and the liquid oxidizer in conjunction with the Conveying system for the liquids mentioned, with the Injectors and the combustion chamber. In this and through this system the crucial process takes place when starting a rocket, namely the combustion. Disturbing vibrations often occur in the combustion chamber with sometimes strongly increasing amplitude in the different Frequency ranges leading to instability of the Incineration with the possible consequence of destruction of the Engine can lead.

By interaction between the combustion chamber pressure and the Injection systems generate low-frequency vibrations (Frequency <100 Hz, "chugging" = cough). These disappear if the pressure in the injection system is equal to that half combustion chamber pressure or greater. With growing Combustion chamber pressure and with increasing delivery pressure increases however, the frequency of the vibrations and their amplitude falls. Frequency and amplitude are also of the qualitative and quantitative composition of the fuels or fuel mixtures as well as the characteristic Length of the combustion chamber depends.  

Low frequency vibrations occur for the following reason: The fuel injected into the combustion chamber does not burn immediately, but must first evaporate and be warmed to the ignition temperature. According to KÁRMÁN, the time difference required for this, the so-called running time, is the cause of the low-frequency vibrations in the event that it reaches a certain amount or exceeds it. The running time τ is not a constant, but depends on the state in the combustion chamber.

If the acoustic natural vibrations of the gas column in the combustion chamber are excited by any mechanism, high-frequency vibrations arise, i.e. sound waves (frequencies <1000 Hz, "screaming" = screeching). The laws existing for a vibrating gas column then approximately apply to the frequencies that occur. The gas column in the combustion chamber can oscillate in the direction of the axis or perpendicular to it according to N · L = const. for longitudinal waves and N · D = const. for transverse vibrations (N = frequency, L = length, D = diameter). The most dangerous are the transverse shafts, which generally lead to the rapid destruction of the engine. The amplitude of the vibrations decreases with increasing pressure, but the dependency is weaker than with low-frequency vibrations. With small chamber lengths, the amplitude increases with the chamber length in order to decrease again from a certain chamber length and finally to converge towards zero.

In numerous theoretical and experimental works one has tried the phenomena of combustion instability analyze. A complete mathematical recording of the phenomenon has so far been possible not yet possible, but a good one  qualitative understanding of this extremely complex Processes already conveyed the results of this work. In this context, the work of CROCCO, RAYS, v. KÁRMÁN and LEVINE pointed out. After our Today's notion, every running engine is a diverse one vibrating system, in which the in the combustion chamber contained gas mass usually with a whole spectrum oscillated by vibrations. To prevent this Vibrations grow beyond the permissible level different methods in use. For example, you have for liquid rockets, behind the injection head attached, which are to prevent the injected Rays sprayed by the vibrations of the gas column and be mixed and in this way the combustion process influence negatively. It is also believed that they have a Reduction in amplitude will take effect. Even hypergolizing Additions in very small amounts, such as. B. lithium additives too ammonia, the chemistry of the combustion reaction change. However, their effect is, at least high-frequency vibrations still controversial.

To the problems of the combustion mechanism and the causes / Complex effect of destabilization of combustion in the combustion chamber to understand better, it is useful to show certain basic facts.

For the generation of an effective, fast drive beam by burning the liquid fuel (liquid Hydrogen, hydrazine, dimethylhydrazine, liquid ammonia, Kerosene) with liquid oxygen is said to burn like this quickly and as completely as possible with one if possible high pressure and at the highest possible temperature. The prerequisite for this is the injection of both Fuel components in the combustion chamber (up to several thousand kilograms / second) in such a way that the liquids be atomized finely and so intimately and so quickly mix as possible. The liquid droplets should be very small and uniform in size to one  fast, continuous, even and quantitative To achieve evaporation. The fuel mixture must immediately ignited when the valves release the supply to the combustion chamber be without significant amounts of the precious Fabric leave the nozzle unburned or even come off Distribute and collect in the combustion chamber so that a Explosion occurs. The chemical reaction of the Fuel components, combustion, temperatures occurring are on the order of a few thousand Degrees, they have to be so high because of the temperature the jet velocity or exit velocity depends, which reach the highest possible amount should. The energy generated by the combustion reaction, especially thermal energy acts in a complicated thermodynamic and reaction kinetic process on the liquid droplets not yet in the combustion stage heats them up, causes their evaporation, splits the molecules and activates them, so leads them into an energetic state that is the most reactive Represents the precursor of the combustion reaction.

In the core zone of combustion is the energy difference between the energetically higher electron terms of the unreacted fuel molecules (incl. oxidizer molecules) and the energetically lower electron terms of the molecules reacted in the combustion reaction primarily as electromagnetic energy, d. H. as light and heat radiation free, but changes in the interaction with the molecules of those immediately adjacent to the core zone Zone to a certain extent in convective Heat around (high kinetic energy).

Another portion of the primary radiation energy arrives in the middle and in the outer zone or in selected Districts of these zones and also interacts in them with molecules present which result in higher combustion verification energy levels increased will.

Another portion of the primary radiation energy is radiated through the individual zones to the outside without using  significant interaction between the fuel molecules to be, is therefore from the active reaction happening switched off.

The amount of the individual energy components depends pressure, temperature, constructive and geometric Design of the combustion chamber and the chemical nature and the molecular size of the fuels in question. Either the convective heat as well as the radiation energy, in particular Heat radiation, cause the liquid to evaporate Fuels and their subsequent molecular cleavage, activation and transfer to the combustion reaction.

In the event that all or almost all of them are injected into the combustion chamber Fuel molecules also the continuous combustion reaction could be fed through inclusion both convective heat as well as radiation energy, under the condition of a given balance of percentages of the individual energy shares, the Combustion process in the combustion chamber essentially run smoothly and without serious disruptions. Such a, Almost ideal combustion mechanism is very rare in practice. Most often that happens Combustion more or less incomplete and irregular, because - depending on the combustion system - a changing proportion of fuel molecules unburned through individual combustion zones flows through or in less hot peripheral zones in the event of local vortex formation at the combustion center moved past. This then leads to the training of Above mentioned interference in the form of low and high frequency Vibrations; furthermore due to the lower sales the rate of combustion as well as the temperature of the fuel gases associated with a loss of kinetic Energy and jet exit speed reduced.

The cause of this incomplete and inhomogeneous combustion process can be seen in the fact that the proportion of Radiant energy from the center of the combustion chamber out of those approaching this center, yet  unreacted gas or liquid molecules of the fuel is to be transferred is too low to this Molecules in the activated, reactive energy state bring to. Even those in the peripheral zones unreacted molecules occur only to an insufficient extent Interaction with the effective radiation energy. The intensity is already weakened through their partial conversion to convective heat. The one emitted in the area above the peripheral zones Energy also remains unused.

Although the share of secondary convective heat energy is relatively high, it does not completely evaporate the liquid droplets, split the gas molecules and activate their fission products. In particular, those liquid droplets or gas molecules which are located in the zones and peripheral zones which are further away from the combustion center, from the hottest zone, absorb little convective heat because this is transferred at too low a speed. With regard to the convective heat transfer, the running time τ (time difference between the time at which the fuel is injected and when the fuel reaches the ignition temperature. The evaporation and heating of the fuel must take place during this period) is too high to reach the core zone the combustion can still be reacted to. As already mentioned above, the unreacted fuel molecules in their physical heterogeneity (differences in droplet size, temperature and degree of activation) are the cause of the formation of the disturbing mechanical vibrations, which destabilize the combustion process as a whole.

The problem outlined, the real combustion mechanism underlying, already implies that Task. After recognizing the probable causes destabilization or combustion in the combustion chamber a rocket engine, it is the task of the present  Invention to provide a method which is suitable for the emergence of the above, the combustion destabilizing low frequency and high frequency Switch off longitudinal and transverse vibrations, at least the vibration amplitude below to keep the harmful limit. The solutions to this Task through constructive measures, for example in the arrangement and design of certain device elements the combustion chamber or the fuel injection system or by changing the geometry of the combustion chamber are currently largely exhausted and also did not lead to the desired continuous success the particular task arises, the combustion process in a physico-chemical way so influencing that he has a faster and uniformly strong heating of the injection nozzles on all sides leaving liquid droplets with their subsequent rapid and complete evaporation and activation of all possible gas molecules in the reactive state, overall stabilization experiences.

This task is accomplished by using in the liquid Fuel or fuel / oxidizer system to be introduced Additive mixtures consisting of

• a) one or more organic compounds colored from yellow to deep black, which contain highly conjugated f -binding systems and whose long-wave main absorption bands are in the wavelength range from approx. 350 to 1200 nm,
• b) one or more organic surfactants Fabrics for the purpose of reducing surface tension of the liquids listed below and
• c) organic solvents or suspending agents for components a and b , in particular from the series methylene chloride, tetrahydrofuran, dioxane, heptane, octane, n-butanol, tert-butanol, pentanols, hexanols, heptanols, octanols, toluene, xylenes, nitrobenzene , Benzyl alcohol, mesitylene, ethylbenzene, n-propylbenzene, cumene, n-butylbenzene, isobutylbenzene, tert-butylbenzene, p-cymene, liquid phenols, fatty amines, ether amines and others

solved. The quantitative weight of components a and b to one another is - in parts by weight - approx. 0.5 to 10: 1.

Component c , which acts as a solvent or suspending agent for the two components a and b , is used in an amount sufficient to produce a complete solution or stable suspension of the two components. The combination of the two components a and b is contained in the combustion system in an amount of 2.5 to 18 percent by weight, based on the total amount of the fuel or fuel injected into the combustion chamber, the oxidizer and the aforementioned respective additive mixture.

The additive mixtures which can be used according to the invention are suitable as means for increasing the rate of evaporation and the rate of combustion and the combustion stability of liquid fuels or fuels (including oxidizers) in rocket engines (component c: compare claim 1). However, these additive mixtures can also be used in other high-performance combustion plants, such as jet engines, generally gas turbines, high-temperature furnaces and combustion plants, for example melting furnaces, waste incineration plants, chemical high-temperature reactors, etc., in which similar disturbances resulting from combustion instabilities with harmful effects, such as noise or material wear, can occur use promisingly.

All liquid fuels and fuels (including oxidizer) or fuel and fuel mixtures for rocket engines and other high-performance stills that are practical Operation to train combustion instabilities with harmful vibrations tend to be experienced by the incorporation of the additive mixtures which can be used according to the invention principally an improvement in their combustion stabilities or complete switch-off from incomplete Combustion-related disorders. These additive blends  are in the sense mentioned, in particular in the following, frequently used, liquid, partially cryogenic Effective on fuels or fuel mixtures used: liquid hydrogen, liquid oxygen, Hydrazine, asymmetrical dimethylhydrazine, alcohols, Hydrocarbons, preferably kerosene, more liquid Ammonia.

The preferred to be found in claims 2 to 19 and particularly advantageous embodiments of the invention illustrate the possibilities it contains varied design. But this is necessary because the desired effects to be achieved in Be graded within the scope of the task to be solved must, because of the diversity of chemical Composition and scope of application of each Fuels and fuels as well as the different physical conditions in the combustion process, due to the particular design features the combustion chambers.

The introduction of the combinations of the two mixture components a and b used according to the invention into the liquid fuel or fuel / oxidizer system has a decisive influence on the chemistry of the combustion process in the combustion chamber in the direction of largely switching off (reducing the amplitude) of the low-frequency and high-frequency vibrations. The two components act synergistically in the system: component a as a whole considerably increases the effect of the proportion of radiation energy, component b reduces the surface tension of the liquid droplets and thus the heat of vaporization. Result from it

• 1) a faster, more uniform and more complete evaporation of the liquid droplets within a shorter transit time τ both by heating by means of radiation energy and by reducing the evaporation energy due to a reduction in the surface tension of the liquid droplets,
• 2) rapid, uniformly strong heating on all sides in all zones of mixing and combustion of the gas molecules formed according to 1) to the activated, reactive state of the ignition temperature within the running time τ under the given condition of the large amount for the temperature gradient of the time and the path.

The mechanism of action triggered by the use of components a in liquid fuels is based on certain physico-chemical properties of the colored compounds, which can be derived from their molecular structure.

This mechanism of action and its causes are discussed in expediently explained in more detail below. For the better Understanding the essence of the invention can be related to this detailed explanations cannot be omitted.

As is well known, the colored organic compounds consistently contain highly conjugated f -binding systems (conjugated carbon / carbon double bond systems [chromophoric groups, optionally combined with auxochromic groups]). These give the molecule the property of absorbing, emitting and reflecting the electromagnetic radiation (also fluorescence) in the long-wave UV range, in the visible and / or ultra-red spectral range. The wavelength λ _max for the main absorption band of the respective colored organic compound increases on the one hand with the number of double bonds in the uninterrupted resonance chain, and on the other hand with the degree of delocalization of the π -electrons in the conjugated chain. For example, the cyanine dyes used according to the invention absorb at substantially longer wavelengths than the symmetrical 1, ω- diphenylpolyenes used according to the invention with the same number of π bonds in the two conjugated chains to be compared. The reason for the wavelength difference can be seen in the fact that the π electrons in the diphenylpolyene molecule have a relatively low degree of delocalization, while in the cyanine dye molecule, which is present as a positively charged ion, due to the symmetrical distribution of the positive charge (symmetrical charge resonance) over the whole molecule are almost completely delocalized, are in the state of a one-dimensional electron gas that can move freely along the chain. The energy difference between the uppermost π- electron guest of the ground state and the first excited term (1st electron jump) in which the jump electron moves after the jump is smaller for the cyanine dyes than for the 1, ω- diphenyl polyenes. The jump of a π electron of a diphenylpolyene molecule into the first excited state is more energy-intensive because the uppermost energy term occupied by the π electron of the ground state in the diphenylpolyene molecule is below the corresponding term in the state of the one-dimensional electron gas by the amount of the delocalization energy (disturbance energy V ₀ of KUHN's electron gas). As a result, the diphenyl polyenes absorb at shorter wavelengths and the cyanines at longer wavelengths. The comparison of these two classes of compounds makes it clear that the position of the main absorption bands is not only determined by the chain length of the respective conjugated π- binding system, but also by the peculiarities of the molecular structure of the molecular structure. In this context it should also be mentioned that organic molecules of more or less complicated structure with π- binding systems can have two or more excitable conjugated resonance chains in differently oriented molecular axes; this structural condition is expressed by the appearance of more than one absorption band. Depending on the wavelength difference of the maxima, the bands belonging to them can be in superposition to one another, so that an absorption spectrum which already extends over a larger wavelength range results. For the use according to the invention of the compounds with highly conjugated π- binding systems, it is also important that the absorption strength of the molecules in question for electromagnetic radiation increases with increasing resonance chain (increase in the molar extinction coefficient and the oscillator strength), quite obvious, because with a longer chain length the Cross section of the molecule and thus the probability of a hit, ie the interaction of the photons with the molecular electrons becomes more effective. As can easily be seen, the physical molecular properties mentioned are based on precisely applicable laws. For this reason and because of the diversity of the different molecular structures, the use of numerous variants is possible within the scope of the invention to achieve the object. Sharp differentiations and gradations in the type and strength of the desired technical effects can be achieved, so that flexibility in adapting to the respective, often different technical requirements and existing conditions, such as combustion chamber geometry, injection speeds and pressures for the liquid fuels and the oxidizer, chemical compositions of the fuels and fuels, temperature differences, combustion chamber pressures etc. is guaranteed.

The colored organic compounds with highly conjugated π- binding systems, whose long-wave main absorption bands are in the wavelength range from 350 to 1200 mm, are introduced into the liquid fuel or fuel / oxidizer system in the most uniform possible distribution with the additive mixtures used according to the invention, and have a total effect on combustion Combustion chamber space due to its property of intensive radiation absorption, emission and reflection, a remarkable, leaping increase in the effective proportion of available and usable radiation energy (light and heat radiation) compared to the proportion of convective heat compared to liquid fuel / oxidase mixtures that do not contain such substances. This largely prevents the combustion process from being destabilized.

The molecules of the colored organic compounds with highly conjugated π- binding systems are in the combustion chamber in the combustion chamber in a uniform distribution and the required concentration after being introduced into the fuel or fuel / oxidizer mixture together with the surfactants according to component b . Compared to the fuel or fuel and oxidizer molecules, the molecules of the colored compounds are of considerable size, which is synonymous with a large cross-section of action or capture and a greater probability of hits for photons.

Overall, these molecules absorb a larger proportion of the primary radiation originating from the hot combustion center, and to a certain extent also the proportion that would otherwise be converted into convective heat, which can only be transported slowly, in the immediate vicinity of the combustion center. Furthermore, they still absorb a portion of the light and temperature radiation that would otherwise emit unused without significant interaction with the fuel or fuel / oxidizer molecules through the individual mixture zones to the outside. The radiation absorbed by the molecules of the colored organic compounds is emitted again as secondary radiation, which in turn either heats up the liquid or gaseous fuel phase surrounding it and activates it at the energy level of the ready-to-react state or is transferred to other colored molecules in accordance with component a . In turn, absorption and emission take place, with part of the emitted radiation, as already explained, being available for heating up the fuel particles and part for the transfer to the molecules of the colored compounds. This process is repeated on all sides as often as required in accordance with the available molecules of the colored compounds according to component a . In this way, the radiation energy primarily generated during combustion is uniformly and very quickly (speed of light) in all directions from the center of the combustion via the colored organic molecules that act as radiation transmitters to the fuel particles located in all combustion zones, including the peripheral zones their heating and activation passed on. The proportion of convective heat that is moving far too slowly from the combustion center in order to be able to heat and activate the fuel droplets or gases before they arrive in the reaction zones is lower in favor of the proportion of radiation energy. Likewise, the proportion of radiation energy that is emitted unused in the absence of component a is more closely involved in the heating and activation process due to the presence of the molecules of component a in all, including in the marginal zones of the combustion, in accordance with the statistical spatial Distribution of the radiation energy a certain percentage of it is emitted back in the direction of the reaction coil. A certain proportion of the primary radiation energy generated in the combustion center is not absorbed by the molecules of component a , but reflected. This portion can also still be effective in terms of activating the liquid and gaseous fuels or the oxidizers.

The presence of the compounds of components a in the fuel or fuel-oxidizer mixtures of the combustion chamber means the formation of a corresponding system of uniformly distributed absorbing, emitting and reflecting temperature and light radiators, each of which receives and emits radiation from all sides in its area Represent center. Overall, as can easily be seen from the above, this system brings about a considerable concentration and amplification of the radiation energy over the entire area of the reaction process. This effect results in a more uniform evaporation, an increase in the evaporation rate, the conversion of fuel or fuel (including oxidizer) and thus the combustion rate. This ultimately results in an increase in the temperature and thus in the speed of the exit jet. Overall, the desired stabilization of the combustion is achieved with a simultaneous reduction in the disturbing and dangerous acoustic vibrations.

In principle, all colored organic compounds which contain highly conjugated π- binding systems with main absorption bands in the range from 350 to 1200 nm are suitable as component a for the use according to the invention. These are generally compounds with the following complementary colors: yellowish green, yellow, yellow orange, orange, orange red, red, purple, violet, indigo blue, blue, teal green, green, black. The spectral colors to be assigned to them are, starting from the UV range: violet (yellowish green), blue (yellow), greenish blue (orange), bluish green (red), green (purple), yellowish green (violet), yellow (blue), orange (greenish blue) ), red (bluish green). This is followed by the ultra-infrared range. It is known that black-colored compounds absorb almost all visible radiation and mostly also areas of the infrared radiation.

As with the shift of the main absorption bands in the direction longer waves the absorption strength (molar extinction coefficient and oscillator strength) and thus also the Emission strength increases, with a view to achieving the highest possible radiation intensity and energy density Use of colored organic compounds in the following Order of their complementary colors red → violet → blue → teal → black increasing more effectively. At those found in rocket engines for liquid fuels Combustion temperatures of up to 4000 ° C then also take place another sudden increase in the intensity of the emission radiation with shift of the band maximum after shorter Wavelengths. For certain engine systems with certain Fuel combinations in which, for example  the instability of combustion and the associated Training of disturbing acoustic vibrations stronger and are of such a nature that their elimination can only be done by the most intense energetically broad radiation in the longer wave Spectral range (broad Absorpt.Spectr.) can, it is convenient and inexpensive black or bluish green to purple to red colored organic compounds or such dyes of varying concentration, into the fuel or fuel / oxidizer system introduce. In other cases, in which higher energy radiation but of lower intensity colored compounds or dyes are required to be used with short-wave main absorption bands Spectral range. Depending on the specific task also combinations of two or more colored connections or dyes with specific, complementary Spectra come into play when a certain selective Range of absorption, emission or reflection is required to special destabilization of the To be able to eliminate combustion.

The colored organic compounds or dyes incorporated in the combustion reaction zones are subject to chemical changes in the areas of very high temperatures. Depending on their molecular structure, they are more or less quickly converted into a graphite-like, microcrystalline pyrocarbon or into soot particles after entering the zones of different temperatures. However, they do not lose their property of acting as temperature or light emitters. Rather, the graphite-like carbon or soot as the so-called black body is one of the most intense energy emitters, quite apart from the fact that the colored compounds develop their effectiveness fully before they are pyrolytically converted into elemental carbon, for example red, violet, blue, bluish green etc. energy emitters and their transition to the black emitter while maintaining their radiative function takes place continuously within an extremely short duration of action, the emission radiation increasing in intensity and spectral width and reaching its maximum when the possible in the respective combustion process and which is due to the chemical structure of the emitter , specific, optimal level of black radiation is present. Thus, the new technical teaching also solves the problem of introducing a black body or black radiator that emits maximum effective radiation energy in the form of uniformly and finely divided elementary graphite-like or soot-like pyrolysis carbon into the fuel or fuel / oxidizer system of a combustion chamber. Incorporation takes place via the stage of the organic colored compounds or dyes which is primarily to be introduced into the mixture and which, in its function as colored emitters, represents an already very effective precursor of the black emitter. Although other organic compounds that do not contain highly conjugated f -binding systems would be pyrolytically converted into elemental carbon, ie into a black body (radiator), at very high temperatures in the fuel or fuel mixture, however, in the period up to its formation the radiation cannot be amplified, as is the case when component a is used according to the invention. As soon as it enters the combustion chamber, it acts as a colored radiator, a requirement relevant for stabilizing the combustion. According to the invention, dark, almost black dyes can also be used anyway, which differ only slightly from an ideal black radiator.

The introduction of only carbon particles into the combustion chamber together with the fuels and oxidizers for the purpose of the presence of black ones Bodies or black spots in all reaction zones would be in terms of optimal stabilization  the combustion is desirable. The difficulty of this However, the way to go is that the carbon particles mostly different in the suspensions to be injected Have sizes, are not distributed finely enough, and tend to agglomerate. This fact closes but the possibility of inadequate stabilization of combustion.

As already mentioned above, all colored organic compounds or dyes are suitable as component a , which contain highly conjugated π- binding systems with main absorption bands in the range from 350 to 1200 nm. For example, the following connection and dye classes can be used: azo dyes, anthraquinone, quinacridone, phthalein dyes, cyanine dyes, merocyanine dyes, polymethine dyes, indigo dyes, triphenylmethane, Benzanthronfarbstoffe, Anthanthronfarbstoffe, Carbazolfarbstoffe, carotenoids, Dibenzpyrenchinone, polyphenylenes, Tetracarboximidfarbstoffe, phthalocyanines, polyacetylenes u. Ä.

Colored organic compounds or Dyes called, which are due to their chemical Structure and property of light and Thermal radiation as particularly advantageous and effective in the sense of the use and solution according to the invention to prove the task. They are:

• 1) The symmetrical 1, ω -diphenylpolyenes of the general formula C₆H₅- (CH = CH) _n -C₆H₅worin n means 4 to 8.
  • a) The Diphenyloctatetraen
    (Absorption maxima: 361 nm, 378 nm, 402 nm; complementary color: yellow).
  • b) The diphenyl decapentaen
    (Absorption maxima: 380 nm, 397.5 nm, 423 nm; complementary color: yellow-orange).
  • c) Diphenyldodekahexaene
    (Absorption maxima: 400 nm, 417 nm, 443 nm; complementary color: brown-orange).
  • d) The Diphenyltetradekaheptaen
    (Absorption maxima: 412 nm, 434 nm, 462.5 nm; complementary color: copper bronze colors).
  • e) The Diphenylhexadekaoctaen
    (Absorption maxima: 428 nm, 450 nm, 480 nm; complementary color: bluish copper red).
• 2) The symmetrical diphenylpolyenalazines of the general formula C₆H₅- (CH = CH) _n -CH = NN = CH- (CH = CH) _n -C₆H₅worin n means 2 to 4.
  • a) Diphenylpentadienalazine
    (Maximum absorption: 383 nm; complementary color: golden yellow).
  • b) Diphenylheptatrienalazine
    (Absorption maximum: 415 nm; complementary color: red-orange).
  • c) Diphenylnonatetraenalazine (absorption maximum: 448 nm; complementary color: bluish copper red).
• 3) The symmetrical difurylpolyenalazines of the general formula C₄H₃O- (CH = CH) _n -CH = NN = CH- (CH = CH) _n -C₄H₃Oworin n means 1 to 4.
  • a) The difurylacroleinazine
    (Absorption maximum: 380 nm; complementary color: yellow).
  • b) The difurylpentadienalazine
    (Absorption maximum: 410 nm; complementary color: golden yellow organ).
  • c) The difurylheptatrienalazine
    (Absorption maximum: 439 nm; complementary color: copper bronze colored).
  • d) The difurylnonatetraenalazine
    (Maximum absorption: 467 nm; complementary color: bluish copper red).
• 4) The cyanine dyes of the general formula where n is 1 to 4, in particular the cryptocyanine with n = 1 (1,1'-diethyl-4,4'-carbocyanine iodide). The cryptocyanine is an effective sensitizer for red and ultra-red.
  (Absorption maximum: approx. 830 nm; complementary color: reddish black).
• 5) The deep green pernigranilin dye of the following formula:
• 6) The dye aniline black (an inner phenylphenazonium salt) of the following formula:
• 7) The dye indigo of the following formula: (Maximum absorption: 590 nm; complementary color: blue in xylene).
• 8) The dye violant throne of the following formula: (Absorption maxima: 497 nm, 530 nm, 586.5 nm; complementary color: red-violet; soluble in xylene).
• 9) The dye isoviolanthrone of the following formula: (Absorption maxima: 504.5 nm, 544 nm, 584.5 nm in xylene; complementary color: violet).
• 10) The black dye circumanthracene of the following formula:
• 11) The blue compound pentacene of the following formula:
• 12) The cyan compound hexacene of the following formula:
• 13) The blue dye indanthrone of the structural formula:
• 14) The dye flavanthrone of the structural formula: (Absorption maxima: 511 nm and 841 nm).
• 15) The black pigment indanthrene black BB, the is formed by nitriding the violin throne (Constitution not yet known exactly).
• 16) The dye pyranthrone of the structural formula: (Absorption maxima: 545.4 nm and 622.0 nm).
• 17) The dye anthanthrone of the structural formula:
• 18) The dye dibenzopyrenchinone of the structural formula:
• 19) The benzanthrone dye anthraquinoline of the structural formula:
• 20) The dye anthraquinoline quinone of the structural formula:
• 21) The alizarin blue dye of the structural formula:
• 22) The dye alizarin of the structural formula:
• 23) The acridone dye indanthrene red RK of the structural formula:
• 24) The dye indanthrene brown R of the structural formula:
• 25) The dye dipyrazole anthronyl from the series of dialkyl dipyrazole anthrones of the general formula: In the case of dipyrazole anthronyl, R = H. In the case of the dye indanthrenrubin R, R represents the group C₂H₅.
• 26) The dye indanthrenkhaki 2G (a dye from the carbazole series) of the structural formula:
• 27) The colored p-polyphenylenes, e.g. B. the quinquephenylene of the structural formula:
  (Complementary color: yellow-orange)
• 28) The olive green dye corulein A of the structural formula:
• 29) The tetracarboximide dye cis-indanthrene bordeau RR of the structural formula:
• 30) The Safranin T dye of the structural formula:
  (Absorption maximum: 539 nm)
• 31) The Mauvein dye of the structural formula:
  (Absorption maxima: 543.8 nm, 537.3 nm)
• 32) The phthalocyanine dyes, e.g. B. the deep blue Cu phthalocyanine of the structural formula:
• 33) The triphenylmethane dye malachite green of the formula:
  (Maximum absorption: 616.9 nm)
• 34) The triphenylmethane dye rosaniline of the formula:
  (Absorption maxima: 546.5 nm, 490 nm)
• 35) The colored compounds polyenaldehydes, e.g. B. Phenylpolyenaldehydes of the Structural Formula: (Absorption maxima for n = 4, 5, 6: 390 nm, 405 nm, 430 nm).
• 36) The dyes α- carotene and β- carotene.
• 37) The carotenoid dyes lycopene, crocetin and bixin
  ( α- carotene: 10 conjugated double bonds, absorption maximum 524 nm. Crocetin: 7 conjugated double bonds, absorption maximum 482 nm;
  Bixin: 9 conjugated double bonds, absorption maximum 523.5 nm).
• 38) The metal complexes of organic colored compounds and dyes.

The above, a representative selection performing colored compounds and dyes can depending on the specific task and desired effect in Targeted depending on their constitution will.

The specific task in each case results from the type of fuels or fuels or oxidizers used, that is to say the combustion system, and from the structural conditions of the type of combustion chamber. The peculiarities of the different constitutions of the compounds of component a enable a nuanced gradation and combination of desired properties and effects through the special selection that is necessary in view of the complexity of the combustion process and in adaptation to the task to be modified. In this regard, for example, the combination effect that can be achieved by using metal complexes of organic colored compounds or dyes should be emphasized. On the one hand, these compounds act as energy emitters, on the other hand, they activate the combustion reaction in the combustion chamber due to their increased catalytic activity. Copper naphthalocyanine is an outstanding special representative of this class of compounds, which is important in terms of application technology and is interesting in its chemical and physical diversity, also because of the function of copper as a very effective oxidation catalyst in combustion processes. Furthermore, there is an additional activation of the fuel molecules and the associated increase in the rate of combustion and stabilization of the combustion by introducing into the combustion system those colored compounds or dyes as component a which, if possible, have appreciable to high amounts for their dipole moments and dielectric constants. Compounds that have these properties induce in the surrounding molecules, e.g. B. in fuel molecules a polarization of the electrical charges, synonymous with an increase in energy level and approaching the reactive, activated state. As is known, the size of the dipole moments and the dielectric constant can be roughly estimated from the chemical constitution of the molecules. But it can also be measured and calculated exactly.

Taking into account the existing - already legal - relationships between chemical constitution and physicochemical properties and effects of the type of compound according to component a , it is therefore possible to solve the particular tasks according to the invention, ie to eliminate specific, gradually different instabilities of combustion , targeted use of certain substances or combinations of substances, both qualitatively and quantitatively.

The possible selective combinations of the compounds of component a with the compounds of component b and the solvents and suspending agents of component c also provide a considerable range of variation in the use of the additive mixtures according to the invention. This is also necessary because of the different chemical and physical behavior of the different fuel mixtures during the combustion process in the different combustion chamber systems.

The principle of application of the invention is based on first of all carefully studying the combustion process of liquid fuel mixtures in its processes in test combustion chambers. After the availability of test results and data on the type, cause and strength of the instabilities of combustion and the disturbing and dangerous vibrations caused by them, taking into account the chemical compositions of both the fuel mixtures and the potentially available components a, b and c, a targeted one can be carried out Selection of additive mixtures to be introduced into the combustion system is carried out, which represent an optimum of effectiveness in eliminating the instability of the combustion for the system in question.

However, the essence of the invention also includes selected ones Additive mixtures of the type mentioned in such fuel and Introduce combustion systems that work flawlessly without occurring Instabilities or malfunctions work or at which are statistically very unlikely to the occurrence of combustion instabilities and mechanical disturbing vibrations. In these cases take over the additive mixtures not only have a prophylactic protective function, but they also cause an increase the combustion rate and shape the Combustion process more economical.

The additive mixtures to be used according to the invention contain, as component b, surface-active substances which, as already mentioned above, have the property of reducing the surface tension of the liquid fuels or fuels and of the liquid oxidizers.

The synergistic interaction of the two mixture components a and b results in a more uniform and smaller droplet size of the liquid fuels injected into the combustion chamber and their faster and more complete evaporation, which is synonymous with increasing the combustion speed and stabilizing the combustion.

The compounds listed below issue one preferred the large number of surfactants  Selection of for solving the problem according to the invention particularly suitable, the surface tension of the used liquid fuels, fuels and oxidizers reducing compounds.

These are the following connections:

In the additive mixtures used according to the invention, individual components of the aforementioned compounds or any appropriate mixtures thereof can function as component b to reduce the surface tension. The optimal choice of surfactants largely depends on the composition of the fuels, but the chemical constitution of the solvent does not remain without an influence on their function of reducing the surface tension of the liquid fuels and fuels and oxidizers. If possible, the selection must be made so that there is a synergistic interaction of all substances involved in the combustion reaction. The molecular structure, the melting and boiling points as well as the molar polarizations and the dielectric constants of the individual compounds of component b represent essential property and activity criteria that allow the most suitable compounds to be easily selected as additives for the various types of fuel or fuel systems.

The two components a and b are taken up in the solvents or suspending agents corresponding to component c . The additive mixtures used according to the invention are then introduced into the combustion system in the form of a solution or suspension.

The function of component c is in principle fulfilled by most organic solvents or solvent mixtures, including organic liquid compounds and mixtures of liquid compounds which are not a priori identified as solvents, but which have the property of certain solid organic substances, such as those of the component a to solve. While the compounds of component b dissolve very well in most organic liquids or solvents, certain colored compounds and dyes of component a are sparingly soluble or insoluble in various solvents. But the fluids referred to in the following as a solvent and suspending agent component are for making the present invention usable additive mixtures c particularly suitable: aromatic hydrocarbons, eg. B. alkylnaphthalenes, diphenyls, polyphenyls, ethylbenzene, n-propylbenzene, n-butylbenzene, isobutylbenzene, n-butylbenzene, isobutylbenzene, tert.-butylbenzene, toluene, xylenes, cumene, paracymol, mesitylene; Heptane, octane, nonane, n-decane, n-undecane, n-dodecane, n-tridecane, 3-methylpentane; Alcohols, e.g. B. ethanol, propanol, 1-butanol, 1-pentanol, 1-hexanol, 1-heptanol, 1-octanol, isopropyl alcohol, isobutyl alcohol, sec-butyl alcohol, tert-butyl alcohol, isopentyl alcohol, active amyl alcohol ((-) - 2 -Methyl-1-butanol), tert-pentyl alcohol, cyclopentanol, cyclohexanol, benzyl alcohol, α- phenyl ethyl alcohol, β- phenyl ethyl alcohol; liquid phenols, e.g. B. alkylarylphenols, preferably mixtures between alkylarylphenols and hydrocarbons (there is no crystallization of the dyes); Ether, e.g. B. tretrahydrofuran, dioxane, phenetol, anisole, di-n-butyl ether; Amines, e.g. B. methyaniline, o-toluidine, m-toluidine, m-chloroaniline, 2-butylamine, cyclohexylamine, benzylamine, α- phenylethylamine, β- phenylethylamine; preferably fatty amines with 6 to 36 carbon atoms, ether amines with at least one O atom, in particular mixtures of 15% fatty amines and ether amines; Methylene chloride.

The solubility of the differently structured colored compounds or dyes can be very different in the numerous liquids which act as solvents. In solvent mixtures obtained by systematic adjustment, an increase in the solubility for the compounds of component a is generally achieved. When choosing the most suitable solvent, the chemical constitutions of both the compounds of component a and the solvent to be dissolved must of course be taken into account. The type and strength of the interactions between the molecules of the solvent and the substance to be dissolved and the resulting solvent capacity depend mainly on the following constitutional and resulting physical properties:

• 1) Type and number of molecules that make up the respective molecules Atoms and percentage of each atom type.
• 2) Molecule size and type of structure of the molecules (type of Sequence of atoms, compound class, functional Groups).
• 3) Molecular geometry, especially configuration, degree of Symmetry (type of ring formation, chain lengths).
• 4) Binding type (single bond system, double bond system, in particular conjugated double bond systems, charge resonance, Complex formation tendency (ion complex, semipolar Complex, charge transfer complex), salt formation tendency, Hydrogen bonding, chemical bonding forces 2nd order, e.g. B. from the Waals binding forces, inductive Field effects).
• 5) Physical properties resulting from the constitution like the dipole moment, the molar polarization and the dielectric constant.

After determining the above-mentioned properties of both the solvent and the substance to be dissolved, it is possible, using certain rules and on the basis of theoretical considerations and simple experiments, to find the optimal solvent for each substance to be dissolved. A rule of thumb, for example, is that a substance dissolves in a solvent the better the more the two are similar in their constitutional and physical properties (similia similibus solvuntur). Insofar as certain compounds of component a should be sparingly soluble in the specified solvents, even at higher temperatures, it is necessary to prepare stable colloidal solutions or suspensions of these compounds by grinding them into very fine particles in colloid mills and mixing them in with very rapid, continuous stirring the solvent or suspending agent mixed with component b is slowly and in small, uniform proportions.

Components a and b are used in a weight ratio to one another of approximately 0.5 to 10: 1. Component c is present in the additive mixtures which can be used according to the invention in an amount sufficient to keep components a and b completely in solution or to be able to form a stable colloidal solution or stable suspension of the two components.

The combination of the two components a and b is incorporated into the combustion system in an amount of approximately 2.5 to 18 percent by weight, based on the total amount of the fuel or fuel injected into the combustion chamber, the oxidizer and the respective additive mixture.

The introduction of additive mixtures into the combustion system, d. H. into the fuels or fuels and the oxidizer, can be in the fuel or fuel tanks or already before filling them by the usual appropriate ones Mixing processes take place.

The additive mixtures can also be from a separate Containers for the additives directly into the combustion chamber the fuel or fuel and the oxidizer injected in an even, symmetrical distribution immediately after they leave the respective tanks.  The outlet nozzles of the additive container are located itself in an optimal geometric arrangement and lowest Distance from the outlet nozzles for the and fuels and the oxidizer.

Furthermore, the additive mixture can also be used in the Fuel and injected into the oxidizer separately namely in the feeds to the combustion chamber directly before they are injected into the combustion chamber. To this This is done before the liquids are injected in the combustion chamber a good mix of all at the Burning reactants.

Injecting the additive mixtures into the combustion chamber from a separate container for additional mixtures mainly the advantage that such additive mixtures, the

• 1) are in the form of solutions, which with certain Fuels or fuels or oxidizers are no longer stable, to form homogeneous solutions more in the tanks capital, or the
• 2) in the form of colloidal solutions or suspensions and therefore also with fuels, fuels and oxidizers are not stable, homogeneous mixtures are able to form

with high efficiency in the combustion chamber Perform function.

Colored compounds of component a , which have excellent properties as energy emitters and transmitters of light and heat radiation, but which may be difficult to dissolve in organic solvents, can nevertheless be used easily and successfully in the sense of the invention by the latter method.

Finally, it is possible to heat additive mixtures containing colored compounds of component a , which are sparingly soluble at room temperature in high-boiling organic solvents, but are slightly soluble at higher temperatures, in the separate container for additives up to a maximum below the boiling point of the solvent and then into the To inject the combustion chamber.

Claims (22)

1. Use of additive mixtures consisting of

• a) one or more yellow to deep black colored organic compounds which contain highly conjugated f -binding systems and whose long-wave main absorption bands are in the wavelength range from approx. 350 to 1200 nm.
• (b) one or more organic surfactants for the purpose of reducing the surface tension of the liquids below and
• c) organic solvents or suspending agents for components a and b , in particular from the series of aromatic hydrocarbons, preferably alkylnaphthalenes, diphenyls, polyphenyls, ethylphenyls, ethylbenzene, n-propylbenzene, isopropylbenzene, n-butylbenzene, isobutylbenzene, tert.-butylbenzene, toluene , Xylenes, cumene, paracymol, mesitylene; aliphatic hydrocarbons, preferably n-hexane, 1-methylpentane, 3-methylpentane, n-heptane, isoheptane, n-octane, isooctane, n-nonane, isononane, n-decane, isodecane, n-undecane, isoundecane, n-dodecane, Isododecane, n-tridecane, isotridecane; Alcohols, preferably methanol, ethanol, 1-propanol, isopropanol, 1-butanol, isobutyl alcohol, sec-butyl alcohol, tert-butyl alcohol, 1-pentanol, isopentyl alcohol, active amyl alcohol, tert-pentyl alcohol, cyclopentanol, cyclohexanol, benzyl alcohol, α -Phenylethyl alcohol, β- phenylethyl alcohol; liquid phenols, preferably alkylarylphenols, dye-preventing mixtures of alkylarylphenols and hydrocarbons; Ether, preferably tetrahydrofuran, dioxane, phenetol, anisole, diethyl benzyl ether, di-n-butyl ether; Amines, preferably methylaniline, o-toluidine, m-toluidine, m-chloroaniline, 2-butylamine, cyclohexylamine, benzylamine, α- phenylethylamine, β- phenylethylamine; preferably fatty amines with 6 to 36 carbon atoms, ether amines with at least one O atom, in particular mixtures of 15% fatty amines and 85% ether amines; Methylene chloride

as an agent to be incorporated into liquid fuels and fuels, in particular in liquid hydrogen, ammonia, hydrazine, alcohols, amines and / or hydrocarbons, preferably kerosene and optionally also in the liquid oxidizer, to increase their evaporation and combustion rate and to improve combustion stability in Rocket combustion chambers for liquid rockets and in high-performance combustion plants, the quantitative ratio of components a and b to one another - in parts by weight - being approximately 0.5 to 10: 1, one for the complete dissolution of components a and b or for the production of a stable suspension of components a and b a sufficient amount of components c functioning as solvents or suspending agents is to be used, and the combination of components a and b in an amount of approximately 2.5 to 18 percent by weight, based on the total amount of the propellant or fuel injected into the combustion chamber, of the oxidato rs and the aforementioned additive mixture, is contained in the combustion system. 2. Use of additive mixtures according to claim 1, containing as component a one or more colored organic compounds from the series symmetrical 1, l -diphenylpolyenes of the general formula C₆H₅- (CH = CH) _n -C₆H₅worin n is 3 to 8;
symmetrical diphenylpolyenalazines of the general formula C₆H₅- (CH = CH) _n -CH = NN = CH- (CH = CH) _n -C₆H₅worin n means 2 to 4; symmetrical difurylpolyenalazines of the general formula C₄H₃O- (CH = CH) _n -CH = NN = CH- (CH = CH) _n -C₄H₃Oworin n is 1 to 4; Cyanine dyes of the general formula wherein n is 1 to 4, in particular cryptocyanine; Pernigraniline, aniline black; Indigo dyes; Violant throne, isoviolanthrone, nitrated violant throne (indanthrene black BB), circumanthracene; Benzanthrone dyes, in particular indanthrone, flavanthrone, pyranthrone, perylene, caledonjade green (indanthrene brilliant green FFB); Carbazole dyes, especially indanthrene brown R; Dibenzpyrene; Anthanthrone dyes, in particular anthanthrone; Dibenzopyrenquinones, especially indanthrene gold yellow GK; Anthraquinoline, anthraquinoline quinone; Alizarin dyes; Acridone dyes; Dialkylpyrazole anthrone dyes; Pentacen, hexacen, polyacetylene; Carotenoids; Polyphenylenes; CORULEIN A; Tetracarboximide dyes; Safranin T, Mauvein; Phthalocyanine dyes, especially copper phthalocyanine; Triphenylmethane dyes, phenylpolyenaldehydes, metal complexes of organic colored compounds or dyes. 3. Use of an additive mixture according to claims 1 and 2, containing as component a a mixture of equal parts by weight of diphenyloctatetraene, diphenyl decapentaene, diphenyldodekahexaene, diphenyltetradekaheptaen and diphenylhexadekaoctaen. 4. Use of an additive mixture according to claims 1 and 2, containing as component a a mixture of diphenyldodekahexaene, diphenyltetradekaheptaen and diphenylhexadekaoctaen in a weight ratio of 3: 3: 1. 5. Use of an additive mixture according to claims 1 and 2, containing as component a a mixture of diphenylpentadienalazine and diphenylheptatrienalazine in a weight ratio of 0.5 to 2: 1. 6. Use of an additive mixture according to claims 1 and 2, containing as component a a mixture of diphenylheptatrienalazine and diphenylnonatetraenalazine in a weight ratio of 0.5 to 2: 1. 7. Use of an additive mixture according to claims 1 and 2, containing as component a a mixture of difurylacroleinazine, difurylpentadienalazine and difurylheptatrienalazine in a weight ratio of 1: 1: 1 to 2. 8. Use of an additive mixture according to claims 1 and 2, containing as component a the reddish-black, an absorption maximum at 830 nm cyanine dye having cryptocyanine. 9. Use of an additive mixture according to claims 1 and 2, containing as component a the carotenoid dyes crocetin and / or bixin. 10. Use of an additive mixture according to claims 1 and 2, containing as component a mixtures of red to blue, to deep green to black dyes whose absorption maxima are in the wavelength range from about 400 to about 1100 nm, from the series flavanthrone, pyranthrone, violanthrone, Isoviolanthron, nitrated violanthron, anthanthron, cryptocyanine, indigo dyes, indanthrone, pernigraniline, aniline black, bixin, α- carotene, perylene, dibenzopyrene, dibenzopyrenquinones, the dyes in the range of longer waves than 600 nm being present in a higher proportion by weight in the respective . 11. Use of an additive mixture according to claims 1, 2 and 10, containing as component a mixtures of red to blue, to deep green to black dyes whose absorption maxima are in the wavelength range from about 500 to about 1000 nm, and individual dyes or dye mixtures yellow to yellow yellow-orange to orange-red to red complementary color, the absorption maxima of which lie in the wavelength range from about 350 to about 500 nm, from the series of symmetrical diphenylpolyenes, diphenylpolyenalazines, difurylpolyenalazines, phenylpolyenaldehydes, the two differing dye types in a weight ratio of 0.5 to 2 in a weight ratio : 1 are present in the organic dye component. 12. Use of an additive mixture according to claims 1 to 11, containing as organic, surface-active mixture component compounds of the general formula C _m H _{2 m +1} -C₆H₄-O- (CH₂-CH₂-O) _n -Horinin m 1 to 10 and n Can be 1 to 16. 13. Use of an additive mixture according to claims 1 to 11, containing organic, surface-active Compound component compounds from the series Ethylene oxide, dioxane, dipropyl ether, diisopropyl ether. 14. Use of an additive mixture according to claims 1 to 11, containing organic, surface-active Compound component compounds from the series Hexanol, lauryl alcohol, cyclohexanol, trimethylene glycol. 15. Use of an additive mixture according to claims 1 to 11, containing organic, surface-active Compound component compounds from the series Mesityl oxide, acetylacetone, acrolein, tert-butyl methyl ketone, Cyclohexanone.   16. Use of an additive mixture according to the claims 1 to 11 containing organic surfactants Compound component compounds from the series Ethylamine, propylamine, cyclohexylamine, dimethylamine, Trimethylamine, triethylamine. 17. Use of an additive mixture according to the claims 1 to 11 containing organic surfactants Compound component compounds from the series Fluoromethane, chloromethane, bromomethane, iodomethane, chloroethane, 1-chloropropane, 2-chloropropane. 18. Use of an additive mixture according to the claims 1 to 17 than in liquid fuels, in particular liquid hydrogen, kerosene, hydrazine, alcohols and / or Ammonia agent to increase the Evaporation and combustion rate and the Combustion stability in rocket combustion chambers and high-performance combustion plants, the agent already in Fuel or fuel tank is incorporated. 19. Use of an additive mixture according to the claims 1 to 17 than in liquid fuels, in particular in liquid hydrogen, kerosene, hydrazine, alcohols and / or ammonia and what is to be introduced into the liquid oxidizer Means to increase the evaporation and Burning rate and stability in rocket combustion chambers and high-performance combustion plants, the agent from a separate container for the Additives into the combustion chamber under even symmetrical distribution in the fuel and is injected into the oxidizer immediately after it Leaving the respective tanks.   20. Use of an additive mixture according to the claims 1 to 17 and 19 as in liquid fuels, especially in liquid hydrogen, kerosene, hydrazine, Alcohols and / or ammonia as well as in the liquid oxidizer agent to be introduced to increase their evaporation and burn rate as well as improving the Combustion stability in rocket combustion chambers and high-performance combustion plants, taking the mean from the separate Containers for the additives in the fuel or Fuel and in the oxidizer separately in the respective Liquid feeds to the combustion chamber immediately before the injection of which is injected into the combustion chamber. 21. Use of an additive mixture according to the claims 1 to 17, 19 and 20 as in liquid fuels, especially in liquid hydrogen, kerosene, hydrazine, Alcohols and / or ammonia as well as in the liquid oxidizer agent to be introduced to increase their evaporation and burn rate as well as improving the Combustion stability in rocket combustion chambers and high-performance combustion plants, the means in the separate Container for additives electrically up to a maximum of below the boiling point of the solvent is heated and then injected into the combustion chamber.