DESC011204MA - - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

Registration date: December 6, 1952. Advertised on November 3, 1955

GERMAN PATENT OFFICE

The invention relates to a method for operating propellant gas generators that produce fire gases by deflagration and devices for performing such methods.

According to the possibility of the high explosion pressure, under which such fire or propellant gases can be generated, in flow energy implement and use nozzle and blading arrangements for this implementation there is already a fire gas gradient, given by the pressure, temperature and heat content of the fire gases (Enthalpy), processed in turbine arrangements and the mechanical energy generated either given as external work of the deflagration turbine system or used for the purposes the system itself, for example to compress the operating media, such as air and fuel gas, related.

In the course of development, the same endeavors occurred as with steam turbines or after Gas turbines working on equal-pressure processes to keep increasing pressures and temperatures, to improve the thermal efficiency. So it grew, the total enthalpy of fire gas accordingly, the difference between the application pressure prevailing in front of the turbine wheels and the back pressure behind the turbine wheels, in the direction of flow of the fire gases seen, and it finally reached values that are not in the case of one-step processing

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were manageable more satisfactorily. One therefore went to gradual subdivisions of the Total gradient according to the pressure and fitted the turbine rudder to the state of the fire gases in the individual levels of payment if possible. That in the individual deflagration chambers for each deflagration The total volume of l'Yuergas generated was initially not subdivided. Later became although known, also the total amount of fuel gas

ίο to subdivide yourself into 'IVil quantityii, whereby one for Each subset has a special nozzle and blade arrangement that is as adapted as possible to its condition provided, which required a special, controlled shut-off device for the purge chamber.

> 5 (compared to the large number of turbine stages that became necessary!) And limited control elements In practice, however, one has to process the fire gases separately for me to prepare the chamber for the next charge as so-called residual gases from the deflagration canine had to be removed so that good filling conditions arise.

Ki nc such Verpuffungsbrennk raft turbine arrangement is illustrated in Fig. ι of the drawing

af) light. One recognizes the Vcrpuffungskanimer ι that Charge air inlet valve 2, the after charge air valve 3, the ISrcim gas inlet valve 4, the ignition device 5 and the nozzle valve. This is shown in the open state. Those so dismissed highly tensioned and highly heated fire gases flow to the nozzle arrangement 1, which is the first Turbine stage trained two-ring Curtis wheel 7 is arranged upstream. The second turbine stage is used by the also two-speared Curtisrad S educated. The Curtisrad S is initially arranged upstream of the nozzle arrangement II, that of the residual gases is applied; for this purpose is in the connection line o. to the pre-puff chamber T to the controlled exhaust valve 10 is provided.

In addition to the nozzle arrangement II "for the residual fire gases, a second nozzle arrangement IJ" is provided, which is used to process the fire gases flowing out of the wheel 7. In order for these gases to flow to the wheel arrangement S at as constant a pressure as possible, the nozzle antechamber 11 in front of the nozzle arrangement 11 is connected to an expansion tank 13 via the connector 12 (\ vr is located in the air flow line 14 to prevent unnecessary heat transfer So the fire gases initially flowing over from wheel 7 into the nozzle antechamber 11 with relatively high pressure and thereby compensates for the pressure peak.On the other hand, it stores the fire gases and, when the pressure drops, relays them to the nozzle arrangement according to the course of the expansion line with correspondingly high pressure 11 ₁ , from.

The 1) jerk-time diagram of such a process is illustrated in FIG. 2, in which the

The drawn line shows the pressure in the spraying chamber 1, while the dashed line corresponds to the pressures occurring in front of the nozzle arrangement 11. 2 shows the pressure increase following the ignition at time 15 and the expansion 18 commencing at time 17 when the nozzle valve is ofF-intimate the charge air valve 2 had opened in order to discharge the residual fire gases via line 9 and the still open outlet valve 10 to the nozzle arrangement II _ft . A short time after the point in time 20, the fuel gas valve 4 opens and the charge air valve 2 closes. Under the action of the subsequent charge air valve 3, the pressure increase in the chamber takes place, which is illustrated at 21. It can be seen that the expansion tank 13 causes only insignificant fluctuations in the fire gas pressure 22 upstream of the nozzle arrangement JI ₁ , and that favorable wheel efficiencies can be expected at least in the turbine stage 8 as a result of the application of propellant gases that are essentially balanced in pressure.

A closer examination of the corresponding QF diagram shown in FIG. 3 shows, however, that these expectations linked to the pure pressure curve do not come true to the expected extent. In the Q-FV diagram of FIG. 3, which is the usual CKS'-egg tropic diagram, ζ. B. according to Pflaum, with the percentages of the amount of fire gas that have escaped, calculating the total amount of fire gas per deflagration chamber with 100%, combined as abscissas, where the ordinates correspond to the heat content of the fire gases in kcal / Nm ³ Line 22 of FIG. 2 corresponding lines 22 'or 22 _; , by no means occurs as a parallel or approximately parallel to the abscissa axis, which would be necessary if the wheel 8 too should represent the same or approximately the same fire gas gradient. On the contrary, a rather steeply rising course of this dash-dotted line was observed, from which it can be seen that both the wheel 7 and the wheel 8 have to process fire gases with a strongly changing gradient. However, the dashed line 22 "also shows that with the selected nozzle / cross-section ratio of / for nozzle arrangement 1 and / n" for nozzle arrangement II "with fu" : / j = 1.99 the gradient in the IT area ₍ , became very small for the two-ring Curtis wheel, so that its enthalpicantcil would be insufficient. This disadvantage can be _{remedied by changing the ratio of the narrowest nozzle cross-sections / U (} ,: /,. The dashed line 22 /, the course of the dividing line between the areas I and II "with a ratio f _lla : / i = 1.37. But nothing essential is changed in the basic characteristics of the dividing lines, it only improves the power distribution in the areas I and II _(f .

The states of the fire gases flowing out of the nozzle I can be seen in detail within the marked with I and hatched from top right to bottom left, the states of the

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from the nozzle II _ß flowing fire gases within the working area _{labeled II ß} and hatched from top left to bottom right and the states of the _{fire gases flowing from nozzle H 6} within the working area _{labeled H 6} and hatched from top right to bottom left. The surface area of the gusset 23 corresponds to the heat loss which occurs when the fire gases flow over from the outlet valve 10 to the nozzle H ₆ . The pressure and temperature line network is also indicated, but only applies to the double line going vertically downwards from point 17, this ordinate corresponding to the adiabatic fire gas gradients that occur.

The relationships shown in FIG. 3 already leave the task on which the invention is based recognize; because Fig. 3 shows that despite the gradual subdivision of the fire gas gradient, even in spite of the subdivision of the total amount of fuel gas generated in the event of a deflagration, with the Means of an expansion tank (13 in the system of FIG. 1) has not succeeded in the wheel assemblies (7 and 8) assign the same or even approximately the same fire gas gradient. Because in general

my aim is to ensure that the processed fire gas gradient is at most 45% of the optimum The gradient for which the turbine wheel is designed fluctuate, with the greatest fluctuation upwards at most 30%, downwards at most

.30 should be 15%. Only then can you be satisfactory Wheel efficiencies are expected, while otherwise also the thermodynamically most favorable Processes bad wheel efficiencies are so affected that no favorable ones Overall efficiencies are more to be expected.

According to the invention, the basic solution to this problem has been found and by numerous Calculations and tests have been confirmed as successful.

-40 The solution to the problem developed below is characterized based on procedures for Fires producing propellant gas generators by deflagration with processing of fire gas gradients in nozzle and blading arrangements and with lowering in the direction of flow of the fire gas behind a blading arrangement caused counterpressure during or almost during the expansion of the fire gases in the nozzle or blading arrangement,

: 5ο according to a determination of the counter pressure curve in the nozzle or blading arrangement the same or practically the same enthalpy changes occur and in particular the line of counter pressure in one

: 55 QF diagram, the ordinates of which are the heat content Q of the fire gases in kcal / Nm ³ and the abscissas of which are the percentages V of the volume of fire gas escaping from the total fire gas generated per deflagration and deflagration chamber.

'60 corresponds to the amount, occurs as an equidistant to the expansion line or approximately as such. It was stated above that this is based on processes in which the back pressure behind a blading arrangement during or almost during the expansion of the fire gases is lowered in the nozzle or blading arrangement. This statement concerns the already known proposal, the back pressure after the last stage one with at least two pressure stages working composite gas turbine to lower significantly in order to reduce the gradient between the Wheel pressure relieved residual fire gases and to increase this counter pressure, so that the resulting constant slope the blading can be better adapted, so that in the the second turbine stage results in higher efficiencies. On the other hand, remain with this method however, there are unsatisfactory efficiencies in the first turbine stage while according to the invention what is achieved is that the gradients are approximately the same in all stages, which means all turbine wheels with a higher efficiency than according to the earlier proposals achievable work.

The lowering of the counter pressure or the counter pressures can be done in a wide variety of ways and wise to be effected. There is, for example, the possibility of a To connect piston assembly, so that by removing the piston from the back pressure chamber away the back pressure is lowered. However, it is simpler to produce the counterpressure reduction by means of gases that are available in the form of fire gases in such turbine systems, see above that the counterpressure reduction in further implementation of the invention means to stretch the Fire gases synchronous expansion of the counter-pressure generating gases is made, with fire gases maximum tension of at least one nozzle or Blading arrangement are supplied and in the case of the expansion synchronous to the expansion in the nozzle arrangement, it is also expedient to use fire gases be subjected. In detail, such a method is expediently characterized by that fire gases with maximum generation voltage are only supplied to a nozzle and blading arrangement during the expansion synchronous to the expansion of the fire gases in the nozzle arrangement are advantageously subjected to fire gases that are taken from one of several deflagration chambers assigned to the same nozzle and blading arrangement, the Fire gases from one of the deflagration chambers assigned to the nozzle and blading arrangements " expediently be taken at a point in time in which there is a fire gas voltage in this chamber occurs which corresponds to the fire gas pressure that the fire gases at the end of the Have expansion in the nozzle arrangement, and wherein in the extraction chamber with a tension Fire gases generated above the extraction voltage up to the point in time when extraction begins are preferably brought into effect on the nozzle and blading arrangement, behind the fire gases from the same extraction chamber with smaller ones below the extraction voltage

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the pressures to generate a lowering with the expansion in the nozzle and blading arrangement al> Back pressure can be used. This can be done by offsetting the work cycle sequence several of the same nozzle and blading arrangements assigned deflagration canisters can be achieved, in which during the period of expansion from a deflagration chamber extracted Ectiergasc in the nozzle and loading luiigsanordnung from a different VerpuffungskaiiniHT extracted fire gases are used to produce the reduced counter pressure, whereby by supplying the ecuergases used to generate the counterpressure to further nozzle and inspection arrangements assigned to them, behind them, in turn, during the expansion of the above-mentioned energy gases in them Nozzle and blading arrangements, lowered fuel gas back pressures of the same type

ao, as well as by repeating this procedure for any additional turbine stages the same entlialpy changes in these further and additional turbine stages can be generated. Especially canoeing during the stretching an initially highly stressed partial fire gas joint in a nozzle and blading arrangement a lower-tension fire gas component line in the (legend pressure chamber of the same nozzle and Hescliaufelungsanordnung be relaxed after they are in a different explosion chamber with a higher air discharge than the one in the counterpressure chamber prevailing voltage had been generated, so that the enthalpy changes of the former Fcuergaspartmeiige in the nozzle and blading arrangement be kept approximately constant. Likewise, a lower-tension renewable gas section can be used relaxed by medium pressure in a second nozzle and air scoop arrangement are, while at the same time in the back pressure chamber of the second I'esehaufelungsaiiordnung a one third deflagration kainnier with an even lower one The partial amount of pressure withdrawn is released while generating a counterpressure curve, in which the wholeness of the second Verpun'inigskanimer initially with the middle one The partial quantity of the renewed gas withdrawn from the pressure is essentially constant, with the generation voltage that of the third deflagration chamber with the lowest pressure is greater than the highest generated in the back pressure chamber of the second nozzle and Hescliaufelungsanordnung Tension and being used as the lowest tension Eeticrgasteilinenge expediently Eeuergase are released from a deflagration chamber during its charge by means of the charge air as fuel combustion gases are displaced.

The present invention is based on the further knowledge that it can be achieved by subdividing the work cycle each deflagration chamber into one corresponding to the number of deflagration chambers Number of work cycle sections is possible, the work cycle sections preferably without to string together temporal pauses between them and without mutual temporal overlaps, so that the work cycle sections are processed with the same duration be able. If you offset the work cycle sequence of the chambers below and against each other by the Duration of each work cycle section, this results in a particularly simple solution to the task, to achieve that at least one chamber has the associated nozzle and blading arrangements at each operating time acted upon, with which an uninterrupted act of application is realized. Through this transmits the turbine shaft at any point in time when the associated generator is in the network is a positive torque, so that torsion phenomena, which previously caused disturbances, are eliminated Gave cause.

The displacement of the work cycles in the deflagration chambers a deflagration combustion turbine unit has already become known several times. This measure, however, was made for completely different reasons and to become a reality completely different technical tasks taken. Worth mentioning among these well-known Proposals is only an embodiment in which the work cycles are offset against one another in such a way that that the time spans of the residual fuel gas displacement are lined up next to each other. One achieved this allows the use of compressors with steeper characteristics and the discontinuation of the periodic, i.e. with breaks in succession, charge air extraction, was not yet able to string together the remaining work cycle sections, so that the advantages that can be achieved by realizing the present inventive concept could not yet be achieved, even if one bckanuter the time segments of the charge air openings Way would string together.

It is also known to simultaneously open charge air inlet and residual fire gas outlet organs when operating such deflagration chambers at the beginning of the work cycle section of the charge, including that of the residual fire gas displacement, and to close both organs, which are consistently designed as valves, with the supply of fuel expediently being carried out on a part of the Duration of this work cycle section extending time span takes place. Maintaining this charging method within the scope of the present invention is particularly advantageous because it eliminates special work cycle sections for flushing and introducing the fuel, so that with just four deflagration chambers you are able to achieve the required counterpressure reduction. In more general terms, this means that the fire gases are subjected to expansion for a period of time which is times the duration of a working cycle section, where η is an integer equal to 1 or greater than 1, with a preferred division of the working cycle of each deflagration chamber into at least η + 2 work cycle sections, where apart from the η expansion

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work cycle sections at least one work cycle section for charge including residual fuel gas displacement and at least one further working cycle section for ignition and deflagration occurs. When calculating the number of deflagration chambers, only the deflagration chambers are analogous to count, according to the time offset of the work cycles by a work cycle section at any time of operation

ίο working cycle sections that differ from each other transact. However, it is also conceivable, for example to limit the size of the chamber, to have chambers working in parallel, that is to say chamber groups to provide that are no different with regard to the cyclical offset of the work cycles behave like a single large chamber, i.e. each stand in the same work cycle section. In this case, the number of groups is added to the counting of the deflagration chambers Place of the individual chambers.

The present invention is based on the concluding finding that the increase in turbine efficiency, which according to the invention is achieved directly and indirectly by using, for example, single-ring blades can use high efficiency is of such importance that one has to rely on the previously used Achieving economic efficiencies can dispense with the use of waste heat. The thus means that the flue gas conditions outside the deflagration chambers and the nozzle and blading arrangements as well as the consumer level are maintained unchanged except for inevitable losses, for example through discharge of coolant with the absorbed cooling heat or by dissipating the intake the heat transfer medium serving the recooling heat with the recooling heat absorbed or else by releasing the exhaust gases from the deflagration turbine stage of the system with the tangible Heat that they generate when leaving the last blading arrangement, seen in the direction of the fire gas, exhibit.

Numerous proposals have become known, some of which are deliberate, some for reasons of drawing Simplification, the heat exchangers belonging to the system have not been shown are. However, it cannot be concluded from this that the present invention is involved underlying knowledge was assumed. Because as far as these systems on heat use Having deliberately renounced, they went from erroneous ideas about those to be achieved Efficiencies from, so that there is never anything about practical designs of such systems has become known. The same applies mutatis mutandis to the systems in which the heat is not used was shown because in these cases the use of heat was not important. The one who has become known in this way on the other hand, the present invention is based on the novel and peculiar finding that by combining it with the new operating procedure outlined above, the overall efficiency of detonation combustion turbines by significantly increasing the To increase turbine efficiency so that the profitability of the operation without waste heat recovery is guaranteed. Only this success justifies maintaining the system with unchanged Fire gas states outside the deflagration chambers and the nozzle and blading arrangements the deflagration turbine stage to operate, considering the inevitable losses due to radiation, heat conduction etc. refrains.

The devices used to carry out the described methods can be of the most varied Way to be run. They are preferably characterized by nozzle and deflagration chambers associated with blading assemblies having a plurality of controlled outlets for the extraction of fire gases for the purpose of generation during the expansion of the fire gas in the Nozzle or blading arrangements in the pressure of reduced counter pressures behind these blading arrangements, seen in the direction of flow of the fire gases, in connection with a design of the control during the opening the nozzle valve of a deflagration chamber that releases higher-tension fire gases corresponding nozzle valve of a further deflagration chamber closed, but at least one her further, lower-tensioned fire gases releasing nozzle valves is opened, which opened Nozzle valve connected to a back pressure chamber of the nozzle and blading arrangement which is acted upon by higher tension fire gases via the opened nozzle valve. In particular the control can be designed so that during the opening of a nozzle valve one deflagration chamber the corresponding nozzle valve of another deflagration chamber is closed, but at least one outlet valve opens the same for the residual flue gas and with the The back pressure chamber of the nozzle and blading arrangement is connected, which opened over the The nozzle valve is exposed to fire gases.

It has already been mentioned above that the enthalpy gradients occurring in the blades, which are quite similar, make it possible to occupy a carrier disk with at most one row of blades, so that the reversing blades, which previously led to great cooling difficulties, are no longer needed. Accordingly, carrier disks, which preferably form a common turbine rotor, can be fitted with at most one row of blades, the rotor preferably having two or three disks. According to the relationship between the working method and the number of deflagration chambers already discussed above, the number of deflagration chambers is equal to an integral multiple of the number of working cycle sections of a deflagration chamber, each deflagration chamber having at least η + ι fire gas outlets. It is useful under the η + ι controlled

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l'Yucrgasausllaßii at least η outlet organs (by regulation before nozzle and blading devices designed as nozzle valve. This means that at least one outlet element is provided for the discharge of the residual fire gases To be able to process part, η + ι controlled

ίο Eeuergasauslassc be designed as nozzle valves. The number of nozzle and blading arrangements, i.e. the number of turbine stages, is correspondingly large.

Is the propellant gas inlet line to the outlet valve assembly connected, which is naturally also in connection with the last blading arrangement in a fire gas-conducting connection, one wins the possibility of even the residual fire gases to the already mentioned, favorable design of the (Use the internal pressure so that the last turbine stage also has practically the same partial gradient assigned.

The ecuergas transfer lines within the deflagration turbine stages are advantageous with full, clear cross-section. So far you had to go into these gas transfer lines install the heat exchangers, with the clear cross-sections either narrowed by them or for the EaII have been extended to allow the gas velocities wanted to maintain unchanged. Of course, there was also the option of keeping the cross-section unchanged, by designing the pipe walls themselves as heat exchangers. But also this According to the invention, the possibility comes entirely in the case of an accident. The transfer lines are useful between the deflagration chambers and / or nozzle and blading arrangements of the deflagration turbine stage within half of the nozzle and blading arrangements the exhaust turbine stage receiving (iehäuses arranged. The preferably encased · Naturally, however, training does not exclude apprenticeship training. It is not the same required, a consumer turbine stage following the deflagration turbine stage in the propellant gas flow to form a housing or its housing from the one or those of the deflagration turbine stage to separate, since with all these possibilities the full advantages of the realization of the invention would arise. The term "stage" does not have the usual meaning of the turbine pressure stage, but rather that of the division of the thermal power plant into a propellant gas generating deflagration turbine stage and in a consumer stage fed with propellant gases, which can also be designed as a turbine, such as a multi-stage Parson turbine can and then the Eeuergasergie in mechanical or via a driven electrical generator converted into electrical, external work.

The mutual relocation of work cycle stages is known per se, for example to achieve that when only two deflagration chambers are assigned to a turbine runner, the blades of which on a relatively short, through the mouth of the discharge nozzle is continuously exposed to certain arc with working gas. at All of these well-known suggestions, to which it also belongs, for example, the residual fire gases in to lead a space independent of the wheel house pressure, the relaxation in the deflagration chambers to pressures prevailing before the second impeller stage or controls like that to ensure that no self-ignitions occur in the chambers, however, was always the same Counter pressure worked, so that strong enthalpy changes and accordingly unsatisfactory Wheel efficiencies occurred, the basic increase of which according to the invention proposed measures serve, thus by the proposals of the specified kind, the In purely structural terms, partially matching construction elements were used, but not known are.

The drawing shows an embodiment of the inventive concept using the example of a propellant gas generator designed as a deflagration combustion turbine with several chambers and two turbine stages to supply a power plant turbine that supplies external work.

Prop. 4 illustrates in a schematic representation the structure of a according to the invention oil propellant generator;

Prop. 5 shows the associated pressure-time diagram during

Prop. 6 the Q-F diagram of the same system reproduces;

Prop. 7 shows the Q-F diagram on a larger scale Scale showing a different working method;

Fig. 8 shows in a partial view in partial section a propellant gas generator with modified ones Versions of loading, nozzle and exhaust valves represent:

FIG. 9 shows a cross section through the propellant gas generator according to FIG. 8;

10 shows a schematic representation of a propellant gas generator with processing of the residual fire gases in a special blading,

FIG. 11 is a somewhat modified version compared to FIG. 10 Embodiment.

In FIG. 4, 24 designates the rotor wheel on which the two single-ring turbine runners 25 and 26 sit, which form the two turbine stages of the unit. Upstream of Beschaufelungsanordnung ² 5 "is the nozzle assembly I, associated with each of the aggregate Verpuflungskammern 27, 28 etc. is in fire gas conductive communication. These connections are labeled 29 and 30. The nozzles 29, 30 are closed off or connected to the deflagration chamber via controlled nozzle valves, which are indicated at 31 and 32. For the sake of simplicity, the control of these elements is not shown. However, the arrangement and control of the nozzle valves 31 and 32 can in principle be designed as

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This Fig. ι the valve 6 in a known manner and way illustrated. The ignition devices are denoted by 5, the charge air valves with 2. Corresponding to the design as an oil turbine, fuel supply lines are provided at 33, the injection ends of which are installed directly in the charge air valves 2. A ring line 34 supplies the deflagration chambers with charge air. Special reloading valves are not provided, because the deflagration turbine system, which is primarily designed for the production of propellant gases is to work according to the so-called open charging process, d. H. that still to be discussed The exhaust valve is not only open for the entire duration of the charge air valve opening in a chamber for the purpose of expelling the residual fire gas, but also during the beginning the fuel injection (or a possible fuel gas inlet) kept open. At this open charging one achieves particularly favorable mixing ratios of air on the one hand, Fuel or fuel gas on the other hand. In this respect, the structure corresponds to the deflagration internal combustion turbine with the described modification of the charging process basically the known turbine design according to Fig. 1.

According to the invention, the following further measures are now taken: Reference should first be made to the pressure-time diagram in FIG. 5, which the turbine system described so far obeys again in a manner known per se. In this diagram, A denotes the point in time at which the highest deflagration pressure has developed after the preceding ignition. By opening one of the nozzle valves 31, 32, starting from the point, the expansion occurs which, without the measures taken according to the invention, would proceed through the nozzles I to point C. There closes the viewed valve, and it opens one of the charge-air intake valves, at the same time the exhaust valve 10 of FIG. 1 corresponding exhaust valve, and it is under the action of the pursuing charge air the Ausschiebung the residual products of combustion along the line CE instead. At time E , charge air inlet and outlet valves close. Before that, the injection of the fuel via the line 33 took place at D , so that the already mentioned open charging is realized with the charge air inlet and outlet valves open. At point E there is a homogeneous, well-mixed, ignitable mixture in the chambers, so that only the ignition at time 15 is required to cause the steep pressure increase that would again lead to the occurrence of the highest deflagration pressure at point A of the next working cycle .

With regard to the processing of the fire gas gradient, the design of the propellant gas generator according to FIG. 4 described so far would not differ significantly from the design of the deflagration combustion power turbine according to FIG. 1. However, it was stated above that the working method of the system according to Fig. 1 is not fully satisfied because, as Fig. 3 shows, despite the arrangement of the pressure equalization tank 13, the desired constant of the fire gas gradient at the border of the areas I and Π _{α is} not entry.

The aim was for the counter-pressure line drawn as dash-dotted lines to run as parallel as possible to the abscissa axis. Even if the equidistance of this counterpressure line to the abscissa axis could have been achieved, relatively strongly changing fire gas gradients would still have to be processed in area I, ie through the wheel arrangement 7. In reality, not even the expected parallelism joined the counter-pressure line to the x-axis one, but the back-pressure line took a pretty steep slope upwards so that the change in slope in the area I grew and in region II _e not been satisfactory. These conditions required a fundamental change. If it were possible to change the counter-pressure line drawn in accordance with its real course in FIG. 3 so that it would run equidistant to the expansion line drawn in solid lines, then one would be able to achieve approximately constant fire gas gradients in the turbine wheels.

Such a counterpressure line, which would remain hypothetical without the means of the invention, is shown in FIG. 5 at 35 has been drawn. Their position has been determined in such a way that a number of others are more advantageous Conditions is sufficient. Because first of all, the average temperature stress of a Do not exceed the value that works with such a counterpressure curve Reliable in operation with known wheel constructions, wheel space designs and cooling options can be controlled without the material stresses exceeding the limit of the Achieve creep strengths of the materials. The distance between the two equidistant diagram lines should further be chosen so that inclines arise that the use of single-ring wheels with Allow circumferential speeds that are higher than 250 m / sec. are, for example around 300 m / sec. can be. After all, the counterpressure line should be below the critical line if possible Run counter pressure, which is between 0.5 and 0.6 of the pressure in the chamber for fire gases. This has the advantage that Laval nozzles can be used in which the flow conditions in front of the narrowest nozzle cross-section the same nozzle efficiency may be more turbulent than with non-enlarged nozzles. Since this The counterpressure line 35 is supposed to meet advantageous requirements, so it is also the narrower technical one Object of the present invention has been characterized. What for the nozzle arrangement and the turbine wheel assembly 25 has been carried out, applies mutatis mutandis to the Nozzle arrangement II and the turbine wheel arrangement 26, so that in relation to the latter in the diagram 5 would be to realize a counterpressure line that. by the dashed. Course 36 marked is.

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I> a succeeded with the means of the invention to realize this course of the counterpressures, the solution found according to the invention is thus already illustrated diagrammatically been.

In the pressure-time diagram of FIG. Point A in Fig. 5 starting expansion of the fire gases in the I iron arrangements I, 11, by the same or practically the same amount of fire gas in the Keseliaufeiungsanordiiungen 25, 26, given by the Et | uidistan /. the expansion line starting from point A and the opposing pressure lines 35, 36.

In order to constructively realize this invention illustrated in the pressure-time diagram, the propellant gas generator according to FIG. 4 has been modified in the following way compared to the previously usual structure of the Yerpiiffuiigsbreiinkraftturbinc according to FIG , 38 have been provided in the Yerpuffuiigskaninieni 27, 28, which are connected to the I iron vestibules 39, 40 of the nozzles II via nozzles I \\ ,. \ 2. There are also exhaust valves .13,. |. | have been arranged, which work via the nozzles .15,. | 6 directly on the Auslrömgeliäuse 47 of the Ttirbinenrades 26. The outlet housing.i "is connected to a power plant turbine via the propellant gas supply line 48, which can be designed as a multi-stage Arson turbine Capable of exploiting propellant gases leaving the vent housing.

All cooling and insulating jackets are for reasons of simplicity not shown.

As can already be seen from FIG. 5, the opposite pressure line 35 reaches the line of the charge air pressure /> ₍ , at a certain point in time.

If one were to drive the pressure line beyond this point in time, i.e. one would Let the fire gases expand in the nozzles 1 beyond the point in time which is the point of intersection the (pressure line 35 with the line of the charge air

If the pressure corresponds to in order to obtain the same or approximately the same fire gas gradient in this period starting from the point of intersection, a lower pressure would prevail in front of the nozzles II, seen in the direction of the exhaust gas, than in the outflow housing 47, as this would be with residual fire gases from the selected charging method Pressure of the charge air is fulfilled. So there would be cooling currents and braking effects on the turbine wheels, which are undesirable. For this reason, the expansion of the fire gases in the nozzles 1 must be terminated at a point in time which is before this point of intersection of the counterpressure line 35 with the line of the charge air pressure p ₀ . For safety reasons, this point in time is brought forward a little earlier than the stated cut point. It has been designated by B in FIG. 5. At point B , the nozzle valves 31, 32 close and the nozzle valves 37 and 38 open. The same nozzle valves close at point C and the outlet valves 43, 44 open to close at point E. The control times of the valves 31 and 32 or 37 and 38 or 43 and 44 and thus the working cycle sequences of the exhaust chambers 27, 28 etc. assigned to the nozzle and blading arrangements I, 25 and II, 26 are offset in time with respect to one another that ■ - during the period of expansion AB a higher-tensioned Fcuergas partial quantity taken from the deflagration chamber 28 in the nozzle and blading arrangement T, 25 - a lower-tensioned Eeuergaseilmcnge taken from clerVerpuff ungskammer 27 to produce the lowered counter pressure 35 in the nozzle antechamber 39, 40 and that - during the period of expansion of a ^{lower-tensioned amount of fuel gas taken from the \ T} erpuffungskammer27 in the nozzle and blading arrangement II, 26 - an even lower-tensioned partial amount of fuel gas taken from another, not shown, deflagration chamber to produce the lowered counterpressure 36 in the outflow space 47 . Accordingly, the nozzle valves 32 and 37 have been drawn in the open state, the nozzle valves 31 and 38 and the outlet valves 43 and 44 in the closed state. Another valve, not shown, corresponding to the outlet valves 43, 44 is to be thought of as open, so that an exhaust chamber (not shown) which discharges the lowest-tensioned partial amount of fuel gas is connected to the discharge housing 47. During the expansion AB (Ing. 5) of the higher-tensioned partial amount of fire gas, which is supplied via the open nozzle valve 32 of the nozzle arrangement I and the blading arrangement 25, of the total amount of fire gas generated in the deflagration chamber 28 during a deflagration, the counterpressure in the nozzle vestibules 39, 40, which leads to this Purpose in a manner not shown, for example by ring-shaped formation, are connected according to the counterpressure line 35 according to the expansion BC of the lower-tensioned subset of the total generated in the deflagration chamber 27 via the open nozzle valve 37 into the nozzle \ 'or rooms 39, 40 Amount of fire gas. It should be noted that the time taken in the previous sentence with respect portion stretch BC part of the diagram of Fig. 5 a diagram showing the pressure profile in one and the same chamber representing that therefore the back-pressure line 35 forming the Teilcxpansion AB in the Verpuffungskammer 28 Partial expansion BC of a lower-tensioned partial amount of fire gas released from the deflagration chamber 27 does not belong to the diagram in FIG

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Deflagration chamber 28 precedes so that during the period of partial expansion AB of the higher-tensioned partial amount of fire gas released from the deflagration chamber 28 via the nozzle valve 32, the deflagration chamber 27 already releases a lower-tensioned partial amount of fire gas, which according to its own, compared to the diagram in FIG. 5 by the time period AB advance pressure-time diagram is just subject to the partial expansion BC . This applies analogously to the extremely low-tension partial amount of fire gas which generates the counterpressure line 36 and which, in the exemplary embodiment, expands into the discharge housing 47 as a residual amount of fire gas pushed out of a chamber during the period CE. The pressure-time diagram of this chamber, which is not shown and which expels the residual fire gases, leads the diagram according to FIG. 5, which is assigned to the chamber 28, by the time measure AC . In other words, the course of the

ao work cycles in chamber 27 is brought forward in time compared to the progression of the work cycles in chamber 28 so that during the generation of the counterpressure progression 35 'in the nozzle vestibule 39, 40 with the help of the expansion, the vented through the opened nozzle valve 37 into the vestibule 39, 40 , lower-tensioned partial amount of fuel gas, the higher-tensioned partial amount of fuel gas released from the deflagration chamber 28 via the nozzle valve 32 is expanded in accordance with the partial expansion AB .

This temporal offset of the work cycles is correspondingly during the counterpressure curve

35 in the nozzle vestibule 39, 40 the counterpressure occurring in the outflow housing 47 according to the line

36 lowered. This fulfills the purpose of the invention. The partial amount of fire gas supplied to the nozzle and blading system I, 25 via the opened nozzle valve 32 is processed with approximately the same fire gas gradient, which is characterized by the expansion line AB and the approximately equidistant counterpressure line 35. The lower tensioned partial amount of fire gas acting on the nozzle and blading system II, 26 is processed simultaneously in this nozzle and blading arrangement II, 26 with the same fire gas gradient, since the line 35, now as the expansion line of this lower tensioned partial amount of fire gas, runs equidistant from the counterpressure line 36 of the outflow housing 47. However, these pressure-time diagrams do not reveal which fire gas gradient is found in the further processing of the partial amount of fire gas flowing out of the wheel 25, which has been partially processed and which was initially higher tension. For this purpose it is necessary to show the same relationships in the QF diagram shown in FIG.

In this diagram, the course of the lines A, B, C and E is illustrated again. The fire gas gradients can be read on the ordinate starting from A , the amounts of fire gas that have flowed out on the abscissa axis. The pressure and temperature line network is only indicated and applies again to the double line starting from A. This double line illustrates the state conditions during expansion. These changes appear in the Q - ^ - diagram as vertical adiabatic lines, but only in the ideal machine, in which no entropy changes occur during expansion, i.e. no heat losses in the walls and no heat dissipation takes place through friction on the impeller and the blades. Both requirements do not apply to the executed machine. However, careful investigations into the heat transfer on the gas side of walls in contact with the flue gas and calculations of the ventilation losses on paddle wheels and blades show that in carefully designed systems the operating methods in question lead to practically the same thing as the heat emitted and absorbed. It is therefore justified to assume adiabatic changes in state and, accordingly, vertical lines in the QA diagram and thus in the QF diagram. Also entered is the counterpressure line 35 drawn in dash-dotted lines and the counterpressure line 36 drawn in dashed lines. These lines determine the following areas in connection with the ordinates through the points B and C _{: I?} , I ₆ , II and III. The area I _a below the curve AB corresponding to the partial expansion AB corresponds to the work performance of the partial amount of fuel gas flowing out of the nozzle arrangement I, exerted on the wheel 25. The dash-dotted dividing line 35 between the areas I "and I ₆ corresponds to that in the nozzle vestibules 39, 40 occurring back pressure. This counterpressure line is mainly dependent on the number of working chambers, the number and size of the nozzle vestibules and the narrowest nozzle cross-sections. With the design of this counter-pressure line in the QF diagram, the wheel efficiency of the deflagration internal combustion turbine can be largely influenced. It is influenced in the most favorable manner if the means of the invention succeed in leading it equidistantly or approximately equidistantly to the line AB . A small deviation from the equidistance on the occasion of the filling of the nozzle vestibules 39, 40 must be accepted, but this deviation is too small for it to have an unfavorable effect on the degree of efficiency.

It also denotes I ₆ an area which corresponds to the work output of the higher-tension partial amount of fuel gas supplied via the nozzles I in the nozzle and blading arrangement II, 26. The working surface I _{6 is} delimited at the bottom by a dotted counterpressure line 36, which corresponds to the state of the fire gases in the outflow housing 47. The approximate equidistance between the counter-pressure line 35 drawn with dash-dotted lines and this line 36 drawn with dotted lines can again be seen, so that the changes in enthalpy that the partial amount of fuel gas supplied via the nozzle arrangement I find during processing in the second door bine stage are also approximately constant.

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The working area II, which corresponds to the available work, which the UI IT of a lower-sputtered partial quantity of fuel gas discharged from the nozzle valves 37, 38 in the door assembly IT, 26, can also be controlled. Due to the approximate equidistance between the curve asl / '- (' and the reverse pressure line 36 drawn in reverse, this lower-sputtered partial amount of fuel gas also finds almost the same fire gas gradient so that both turbine stages have approximately the same small gradient There is therefore the possibility of using these similar (incidence ratios largely ent-Si) It ¹ ChCIi (Ie Kad or a corresponding cad group with optimal efficiency and thus the traction fuel turbine to the rank of turbines with the same gradient This also applies to working area III of the power plant turbine.

! • 'ig. 7 shows a (JI ') diagram of an operating method, held on a different scale, in which a combustion which more or less approximates the constant pressure combustion has been combined with a constant pressure combustion. In the operating method which forms the basis of the diagram according to FIG It causes ignition in relatively close proximity to the nozzle valves 31 or 32, via which the highly tensioned partial fire gas is discharged into the first of the nozzle arrangements I would come to the löehstdruckspitze A that point. · / Fig. C corresponds so. Ks escaping gases whose combustion or explosion is more or less completed before the KmIe the period, which provided for the implementation of combustion or Verpuftung is, apart from the fact that this is naturally independent of this pre-opening of the nozzle valve le comes to an end.

This modified procedure thus replaces the pure (ileichraumburn) in which the combustion or deflagration to a large extent takes the form of constant pressure combustion or deflagration occurs. ICs are therefore those created by the expansion of the kitchen area Gases under a more or less constant tension after a certain pressure has been created discharged, which is maintained by dal.! the mixture in can parts for incineration or deflagration occurs that are further away from the nozzle valves. During this period During the processes there is initially a slight increase in pressure, after which a period is complete The same pressure follows, while the tension is restored when the combustion processes begin begins to lower. At this point it cuts

The pressure-time curve shows the expansion line of gases that have arisen through pure constant-space combustion. The curve .r in FIG constant volume combustion for the generation of a pressure of 50 ata to 64 ata has resulted, which would be reached when carrying out the combustion or deflagration as a pure constant volume combustion. It is seen that the curve χ approximately horizontally with respect to a very large part of the combustion gas volume runs, which during It should be noted that the curve χ conforms even more closely to the general course and the characteristics of the dash-dotted and dashed counter-buckling lines than the urn AB, so that even with regard to the initial time elements of the first partial expansion, expansion and counterpressure lines almost completely equidistant, practical h equidistant, run. More detailed investigations have shown that, despite the loss of working area in the diagram above line A ", the available output in the combined constant-pressure process is approximately the same as in the constant-pressure process Conditions are designed so that in connection with the higher wheel circumferential speeds the wheel efficiency can be significantly improved, for example to values of 70 to 76% .Similar results can also be obtained by pre-opening the nozzle valves with an introduction of auxiliary fuel, such as with a post injection of liquid fuel into the chamber, connects. This method has been in Fig. 7 y by the continuous line illustrated in which the nozzle valve is opened at a time, wherein the reiine constant volume combustion at a pressure in the closed chamber vo n 42 ata has resulted. The pressure rises momentarily as a result of the post-injection of fuel, the pressure rise being followed by a period of approximately horizontal pressure curve. Line y intersects expansion line AB and, like line χ , meets it at point B. The second method increases the amount of combustion that occurs at approximately constant pressure. While the pressure peak can be pulled down even further than in the first method, further increases in mechanical efficiency are possible.

What just on the basis of the embodiment of Fig. 4 for the release of a high tension Partial amount of fuel gas through the opened nozzle valve 32, for the simultaneous discharge of a lower tension Amount of fire gas through the open nozzle valve 37 of another Verpuffungskammcr and for the also simultaneous discharge of the Flue gas residue has been carried out from a further deflagration chamber through an exhaust valve was, applies cyclically to the entire partial quantities of fuel gas. That was the case, for example during the opening of the nozzle valve 31 of the deflagration chamber 27 with respect to a higher

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tensioned partial amount of fuel gas, the nozzle valve 32 of the deflagration chamber 28 is closed, but that The nozzle valve 38 of the same chamber is opened, so that the lowering in the nozzle antechamber 39, 40 of the back pressure took place, the. made sure that the nozzle valve 31 was opened to the Nozzle and blading system I, 25 brought into effect higher-tension partial amount of fire gas as a result of the equidistant course of expansion and counter-pressure lines in the aforementioned nozzle vestibules the same fire gas gradient. This cyclical exchange applies analogously to the lower stressed one Nozzle valves releasing partial amounts of fire gas and for releasing the residual fire gases Exhaust valves.

The invention is in no way limited to the two-stage illustrated in the exemplary embodiment Turbine arrangement limited. The lowering of the counter pressures can already be done with a single-stage

ao turbine arrangement are used to generate the same fire gas gradient in this. That is true correspondingly for units with more than two turbine stages, but it should be noted that The increase in the number of turbine stages results in an increase in the average stress temperatures corresponds, so that it depends on the material development which number of turbine stages is implemented in practice can be. Also compliance with the rest for the. practical deflagration combustion

power turbine construction eligible operating conditions presupposes the arbitrary increase in Number of turbine stages certain limits, the two-stage training currently regarded as the best measure, without the idea of the invention being exhausted in it, because in this respect other, the Scope of validity of the new rule for technical action not affecting factors decisive are.

As already the comparison of the dashed line 22 in FIG. 2 with the one drawn in dash-dotted lines 3, the course of the gradient boundary line shown in FIG. 3 is shown in dash-dotted lines, is not sufficiently characterized by the course of the pressure curve 22 will. Because besides the pressure are for the state of the fire gas, that in relation to another State results in a certain gradient, also determining the temperature and heat content of the fire gases. It would theoretically be possible to lower the slope boundary lines 35 and 36 in Fig. 6 to effect without the pressure of the fire gases, so the counter pressure with respect to an upstream Nozzle and blading system to change. Since this does not leave the essence of the invention would, then, is the expression counterpressure in this further. The sense of the counterpressure that corresponds to this Line in the Q-F diagram.

The diagram initially shows a pressure peak which occurs at point A and which corresponds to the maximum deflagration or explosion pressure P _1. At this point in the diagram, the first of the two nozzle valves 31 or 32 opens, so that the partial amount of fuel gas released via this nozzle valve is subjected to an expansion which lasts up to point B , since the nozzle valve mentioned closes at this point in time. The time span of 0) ⁰ SPS seconds, which runs between points A and B , is dimensioned in such a way that only a partial amount is released in relation to the total amount, which according to FIG. 6 results in 48.5% of the total amount.

At point B of FIG. 5, the second nozzle valve 37 or 38 of the deflagration chamber opens and, in a work cycle section that extends to point C , discharges a further partial amount of fuel gas, the percentage of which is the total amount of fuel gas generated per deflagration in the same chamber the level of 25% in FIG. 6 can be seen. At point C, at which the second nozzle valve closes, the expansion line ABC reaches the line of the charge air pressure P ₀ , below which the remaining amount of fire gas in the deflagration chamber is. The extent of this residual amount of fuel gas can be seen in FIG. 6 with 26.5% in relation to the total amount. At the point in time C , the charge air inlet and outlet elements open simultaneously for the residual fire gases. Both valves close after a period of time corresponding to the length of a work cycle section at point E. When the organs were still open, the piston of the associated fuel pump had started its delivery stroke at time D , so that fuel was not injected into the charge air that was still moving Formation of an ignitable mixture occurred. The fuel injection is ended before E , so that when the charge air inlet and residual fire gas outlet organs close at time E, the chamber is filled with a completely homogeneous, highly ignitable mixture. If, therefore, an ignition of this mixture takes place at time 15 too, the conditions are chosen so that the full maximum deflagration pressure is reached at time A when a period of time equal to the duration of a work cycle segment between time E and this second time A has expired. In this second point A , a full working cycle with closing, ie without pause or overlap, consecutive working cycle sections AB, BC, CE and EA is carried out, with which the implementation of the inventive concept is shown diagrammatically.

The working process in the other three deflagration chambers takes place in exactly the same way as was shown in FIG. 5 for the chamber under consideration. However, viewed in terms of time, these work cycles are offset by the duration of one work cycle segment compared to the work cycle of the chamber under consideration. Seen in the diagram, this means that when the highest deflagration pressure P ₁ occurs in the chamber under consideration, a second chamber had already started the same working cycle a time period ι · 0.059s seconds earlier, that is, the working cycle of this second chamber hurries

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that of the chamber under consideration by 0.0595 seconds. At the time O so this second chamber had already reached a state of your l'oint B of the diagram train of FIG. 5 even advanced by the time 2 · 0.0595, (1 hr., This chamber had to at the time 0 l'oint C of the diagram of Fig. 5 realized. Fine fourth chamber finally informs the I Magnimm the I ^1- Ig. 1 to the time scale 3 · 0.0595 seconds ahead, d. li., at time O is l> ven the diagram time /; has been reached.

FIGS. X and 9 show a four-chamber oil propellant gas generator which is used to carry out this Method is suitably designed. Its control shaft should make 252 complete revolutions per minute. So 252 work cycles are carried out per minute. This means that one work cycle lasts 0.23s seconds, and each of its four work cycle sections takes 0.0595 seconds.

In FIG. 9 one can initially see the four spray canisters 62, 63, 64 and 65, which are assigned to the common nozzle and blading. If one assumes that the Veras pui'iungskammerr> 5 is shown in longitudinal section in FIG. 8, so that the chamber 64 can be seen in view, then each chamber initially has the charge air inlet valve 66, into which the fuel injector 67 with the supply line 68 is built in, while the charge air supply takes place even at 69. The control of the charge air valve is indicated at 70. The Breniisloffleituiigen 68 lead to a four-piston fuel pump, not shown, of conventional design. The deflagration chamber itself has a venturi-like inlet end at 71, the diffuser 72 being designed with a very slender incline so that the incoming charge air spreads like a piston and is able to expel the residual fire gases without the formation of significant eddies. The outlet valve 73 is provided for releasing these residual fire gases from state C in FIG. 5. In addition to the outlet valve 73, a nozzle valve 74 is arranged, which is used to discharge the fire gases from state A of the I ^1- Ig. 5 is determined. 9 shows the nozzle valves 74, which are assigned to the deflagration chambers 64 and 65, on the right-hand side. The valves 74, which are designed as almost relieved piston valves, then go over to the valve seat "^ in the nozzle antechamber 76, to which the nozzles 77 adjoin. The nozzles 77 are arranged upstream of the blading 78 of the wheel 79 of the first turbine stage, so that the nozzle and blading arrangement yy, 78, 79 of the first turbine stage, fuel gas components from the initial state. / of FIG. 5 processed.

In addition to the nozzle valve 74, each deflagration chamber has a second nozzle valve 80, the design of which basically corresponds to that of the nozzle valve 74. The nozzle valves 80 can be assigned special nozzles, as FIG. 9 illustrates for the nozzle valves 74. The exemplary embodiment shows a different design in that the valve seats of the nozzle valves 80 are followed by line parts 81 which lead to a filling chamber 82 which is arranged between the two turbine stages of the system according to the exemplary embodiment. This filling chamber not only receives fire gases via the nozzle valves 80 and the line parts 81, but also has a collecting nozzle arrangement 83 for the partial amount of fire gas that had already performed work in the first turbine stage 77, 78, 79. At its end opposite to the collecting nozzle arrangement 83, the filling chamber 82 has an outlet nozzle arrangement 84 which is arranged upstream of the blading 85 of the wheel 86 of the second turbine stage as an impinging nozzle. The blading 85 is followed by a second collecting nozzle arrangement 87, which is in open connection via a line part 88 with the mouth cross-section of the exhaust gas extraction line 89. Line parts not recognizable in the drawing open out at the same point and lead the propellant gas extraction line 89 to the residual fire gases which come through the outlet valve 73 for discharge. The turbine stages yj, 78, 79 and 84, 85, 86 transmit their mechanical power via the shaft of the turbine rotor 79, 80 to a work-taking machine 91, which can be designed as a compressor for charge air, possibly also for fuel gases.

The O-F diagram of the system according to FIG. 8 and FIG. 9 does not differ from the Q-F diagram of FIG. 6.

In the exemplary embodiments according to FIGS. 10 and 11, the advantageous possible applications of the basic concept of the invention illustrated in detail in FIGS. 4 to 9 have essentially been retained. 8 and 9. The difference, however, is that the outlet valve 73 of the embodiment according to FIGS. 8 and 9 is followed by a special nozzle and blading arrangement 96, 97, whereby a third hatch is provided 98 a third turbine stage is created. The turbine stages 84, 85, 86 and 96, 97, 98 have a common outflow housing part 99, so that the advantages of the counterpressure curves identified by the lines 36, etc. with reference to FIG and BC are preserved. This is also the case in the exemplary embodiment in FIG. 11, since here the common outflow housing part 99 is replaced by a filling chamber 100 which, due to the confluence of the line part adjoining the outlet valve 73, remains subject to the counterpressure curve defined by the upper boundary line 36 the area III in Fig. 6 is illustrated. As a result, the second door hinge step 84, 85, 86 is subjected to a counterpressure curve which does not differ significantly from that of the exemplary embodiment according to FIGS. 8 and 9, so that the advances derived from FIG. 6 are also retained in the exemplary embodiment according to FIG .

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The runners of the turbines according to FIGS. 8, io and II can also be designed with a single ring in accordance with the exemplary embodiment according to FIG corresponds to a small drop in total enthalpy.
The hatched areas in FIGS. 6 and 7 give, as already mentioned, a measure of the available work that the individual partial quantities of fuel gas are able to deliver in the stages of the system. First of all, the area I _{0 can be recognized} as a measure of the power that the partial amount of fuel gas released via the nozzle valves 74 (FIGS. 8 and 9) from the initial state A can develop in the first nozzle and blading arrangement TJ, 78, 79 of the system. The same partial amount of fuel gas can deliver disposable work in the nozzle and blading arrangement 84, 85, 86, the equivalent of which is represented by the area I _b . On the other hand, the area II corresponds to the available working capacity of the partial amount of fuel gas brought into effect via nozzle valves 80 from the initial state B, again in the nozzle and blading arrangement 84, 85, 86.

While areas I ₀ , I ₀ and II are to be developed in the two stages 7y, 78, 79 and 84, 85, 86 of the actual deflagration turbine, area III represents the available working capacity of the fire gases, which are used as propellants in the Propellant gas extraction line 89 enter. You reach the actual consumer stage via this line, which can be designed in any way, for example as a multi-stage Parson turbine, in order to drive an electrical generator, a pump or other work machines in this way. The propellant gases can also be used and consumed purely thermally, purely chemically, purely pneumatically or in any combination of these possibilities.

The ratio of area III to the sum of areas l _a , I ₆ and II shows that the system operates with a surprisingly high level of economic efficiency if one takes into account the fact that the power of the deflagration turbine available according to the sum of the areas mentioned is sufficient to drive all auxiliary machines, in particular the charge air compressor, without having to rely on having to utilize the waste heat from the system in order to be able to at least partially cover the required compression effort in this way. This results in the possibility, recognized according to the invention, of leaving the state of the fire gases outside the deflagration chambers and the nozzle and blading arrangements completely unchanged. Likewise, the coolants of the system, which are used to cool the chambers, nozzles, blading, wheels, shafts and valves, are removed after the cooling heat has been absorbed without the cooling heat being withdrawn. However, since in most cases special coolants with a high boiling point are used, it would be uneconomical to remove these coolants from the system; In this case, the recooling system is retained, but the recooling medium is released after the recooling heat has been absorbed, this recooling medium consistently consisting of water or air. Likewise, no use is made of the sensible heat of the outflow gases from the last blading. Rather, the outflow gases are released from the system with the sensible heat, without the heat being used for the purposes of the deflagration turbine stage of the system or the auxiliary machine drive. This corresponds to the fact that the flue gas transfer lines within and after the deflagration turbine stage are designed with a full clear cross section. In order to maintain the same gas velocities, despite the installation of heat exchangers, they neither need to be enlarged, nor is their clear cross-section reduced by installing heat exchangers. The fire gas transfer lines lying between the individual pressure stages of the deflagration turbine are all arranged within the turbine housing 41, to which only the propellant gas extraction line 48 (FIG. 4) or 89 (FIGS. 8 and 11) connects in order to supply the generated propellant gases to a consumer be able.

Although the subdivision of those produced in the deflagration chambers, highly stressed and highly heated Fire gases (fresh gases), a particularly noteworthy feature present in partial amounts of gas Invention represents, is readily understood that the possibility of the duration of each Work cycle sections, the number of deflagration chambers or those working in parallel Deflagration chambers in each group and the relocation of the work cycle sections in the individual To determine chambers against each other so that the nozzle and blading arrangements one record a continuous stream of fresh gas with the result that the turbine shaft is constantly on constant torque is exerted, even without this subdivision of the total generated Fire gas amount can be achieved. Because this state is independent of the way in which the fresh gases are discharged during each work cycle, since it only matters that the discharge of fresh gases from a certain chamber is immediately at the end of the Fresh gas discharge from another chamber follows. Nor is it essential that the purging of a deflagration chamber of residual combustion gases coincides with the charge the same chamber coincides with air and fuel. It is easily possible to do this Carry out flushing during a special work cycle section that is only intended for this purpose or to carry out the flushing in a work cycle section that is directly related to the loading of a chamber goes ahead.

From the above it can also be seen that the gases which in FIG. 4 _{leave the first nozzle and blading arrangement 30, 25 a} , 25

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Claims (20)

Sch 11204 I a / 46 f, and those (iase that are released through the nozzle valves 37 or 3S into the Sanimel chambers 39, 40, enter these chambers at the same time, there: '. Ur mixing come under pressure equalization and in this state to Nozzle arrangement 11. The thermodynamic treatment of the same process in Figures 6 and 7, on the other hand, required a separate treatment of both partial gases in order to be able to illustrate the working surfaces in the two diagrams which correspond to the performances in the air conditioning arrangement The diagrams must therefore not be interpreted in such a way that the two partial amounts of gas in the second examination come into effect independently of one another It is of theoretical importance. ICs are furthermore in the essence of the invention that they are only preferred embodiments ien corresponds if all work cycle sections have the same duration. It is only essential that the periods of time in which the partial expansions of the a5 partial gas quantities take place are the same, and that the duration of a work cycle section essentially corresponds to the quotient of the duration of a work cycle and the number of Verpultiingskammern, which are offset against each other in their work cycles, in order to achieve a continuous application. It is also in the essence of the invention that the numerical values given for temperatures, pressures, numbers of work cycles per unit of time, wheel circumferential speeds, etc. are only examples, without being essential characteristics of the exemplary embodiments or even of the invention itself. The control of the inlet and outlet organs described, which have been illustrated in the form of valves, but can also easily be replaced by slides, mine-controlled outlets and inlets or the like, can be carried out in the most varied of ways, for example mechanically, pneumatically, hydraulically, electrically, magnetically, electromagnetically, hydromechanically, hydroelectrically, pneumomechailisch, pneumoelectrically or in any other suitable way. Such controls and devices for regulating the controlled processes are known and are not the subject of the invention. Path ν ta ν s ph Cc. 11 f .: 1. Process for operating fire gases by means of propellant gas generators that produce fertilizers with processing of fire gas gradients in nozzle and blading arrangements and with lowering of the pressure caused in the flow direction of the fire gas behind a blading arrangement (during or almost during the expansion of the fire gases in the nozzle or .Development arrangement, characterized by a determination of the base pressure curve in which the same or practically the same enthalpy changes occur in the nozzle or blading arrangement and in which in particular the line of the back pressure in a QF diagram, the ordinates of which corresponds to the heat content Q of the fire gases in kcal / Nuv ¹ and the abscissa of which corresponds to the percentages V of the volumetric flow of fire gas in the total amount of fire gas generated in each deflagration chamber, occurring as an equidistant to the expansion line or approximately as such. 2. The method according to claim 1, characterized by producing the counterpressure reduction behind a sprinkling arrangement means to expand the fire gases in the nozzle or Blading arrangement of synchronous expansion of the gases generating the back pressure, wherein Fire gases of maximum voltage supplied to at least one nozzle and blading arrangement and when the fire gases are used to the expansion, the expansion generated in the nozzle arrangement synchronously runs. 3. The method according to claim 1 and / or 2. characterized in that fire gases with Maximum generation voltage can only be fed to a nozzle and sprinkling arrangement, during the expansion of the fire gases in the nozzle arrangement synchronous expansion, fire gases are subjected, which from a can be taken from multiple deflagration chambers using the same nozzle and blading arrangement are assigned, the fire gases being one of the nozzle and blading arrangements assigned deflagration chambers are taken at a time, in which an Fcucrgas tension occurs in this chamber, which corresponds to the combustion gas pressure matches that the fire gases have at the end of the expansion in the nozzle arrangement, and wherein generated in the extraction chamber with a voltage above the extraction voltage The nozzle and blading arrangement up to the point in time at which the extraction commences pressurize, behind which the fire gases of the same extraction chamber with smaller, pressures lying below the withdrawal tension to produce one with the elongation can be used in the nozzle and blading arrangement lowered back pressure. 4. The method according to one or more of claims 1 to 3, characterized by a Relocation of the work cycle sequence of several of the same nozzle and blading arrangements associated deflagration chambers, in which during the period of expansion of the Flue gases extracted from a deflagration chamber in the nozzle and bladder assembly Fire gas taken from another deflagration chamber to produce the reduced counter pressure can be used, 578/213 Sch 11204 Ial46 f by supplying the fire gases used to generate the counterpressure further nozzle and blading arrangements assigned to them, behind which in turn during the expansion of the aforementioned fire gases in these nozzle and blading arrangements, reduced fire gas counterpressures similar course can be generated, as well as by repeating this process for ίο any additional turbine stages equal enthalpy changes in these further and additional turbine stages can be generated. 5. The method according to claim 4, characterized in that one during the stretching initially the highest tensioned partial amount of fire gas in a nozzle and blading arrangement a lower-tension partial amount of fire gas in the counterpressure chamber of this nozzle and blading arrangement is relaxed after being in another deflagration chamber with higher Initial tension than the tension prevailing in the counterpressure chamber had been generated, see above that the enthalpy changes in the first-mentioned partial amount of fuel gas in the nozzle and blading arrangement be kept approximately constant. 6. The method according to claim 5, characterized in that a lower-tensioned partial amount of fuel gas is relieved of medium pressure in a second nozzle and blading arrangement, while at the same time in the counterpressure chamber from the second blading arrangement a partial amount of fuel gas withdrawn from a third deflagration chamber at an even lower pressure is relaxed while generating a counterpressure curve in which the enthalpy changes that of the second deflagration chamber initially with the mean pressure withdrawn partial amount of fuel gas are essentially constant, with the generation voltage the partial amount of fuel gas withdrawn from the third deflagration chamber with the lowest pressure is greater than the highest Voltage generated in the counterpressure chamber of the second nozzle and blading arrangement and wherein the lowest-stressed partial amount of fire gas used is fire gases from a deflagration chamber while it is being charged by means of the charge air as residual combustion gases be displaced. 7. The method according to one or more of claims 1 to 6, characterized by Subdivision of the work cycle of each deflagration chamber into one with the number of deflagration chambers Matching number of work cycle sections, with the work cycle sections are preferably strung together without any time breaks between them and without mutual temporal overlaps, so that the work cycle sections are each handled with the same duration can be. 8. The method according to claim 7, characterized by an offset of the work cycle . follow in the chambers of the propellant gas generator under and against each other for the duration of each of a work cycle section. 9. The method according to one or more of claims 1 to 8, characterized in that at the beginning of the work cycle section of the charge including the residual fuel gas displacement Ladelufteinlaß- and Restfeuergasauslaßorgane opened and that at the end of the same Working cycle section both organs are closed, with the supply of fuel expediently during a part of the duration of the work cycle section of the Charge or residual fire gas displacement takes place extending time period. 10. The method according to one or more of claims 1 to 9, characterized in that the fire gases are subjected to expansion during a period of time which is w times the duration of a work cycle section, where η is an integer equal to 1 or greater than ι , with a preferred subdivision of the work cycle of each deflagration chamber into at least η - \ - '2 work cycle sections, with at least one work cycle section for charge including residual fire gas displacement and at least one further work cycle section for ignition and deflagration in addition to the η expansion cycle sections. 11. The method according to one or more of the Claims 1 to 10, characterized in that the fire gas states outside the deflagration chambers and the nozzle and blading arrangements as well as the consumer stage except for inevitable losses be maintained unchanged, for example by discharging coolant with the absorbed Cooling heat or by dissipating the heat transfer medium used to absorb the recooling heat with the absorbed Recooling heat or by releasing the exhaust gases from the deflagration turbine stage the system with the sensible heat that it exits the last blading arrangement, seen in the direction of the fire gas, on- uo point. 12. Device for carrying out the method according to one or more of claims ι to 11, characterized by nozzle and blading arrangements associated with multiple controlled deflagration chambers Discharge for the extraction of fire gases for the purpose of generation during the expansion of the fire gas in the nozzle or blading arrangements, the pressure reduced counterpressures behind these blading arrangements, seen in the direction of flow of the fire gases, in connection with a design of the control during the opening the nozzle valve of a deflagration chamber that releases higher-tension fire gases 509 578/213 Sch 112041 al46 f corresponding nozzle valve of a further Verpiiffungskainmer closed, but at least one of their other, lower-tension fire gases discharging nozzle valve is opened, the opened nozzle valve with a Counter-bending chamber of the nozzle and blading arrangement is connected, which is acted upon by the opened nozzle valve with higher tension fire gases. ίο 13. Apparatus according to claim 12, characterized by training the control during the opening of a nozzle valve one deflagration chamber the corresponding nozzle valve of another deflagration chamber closed, but opened at least one outlet valve of the same for the residual flue gas and with the counter pressure chamber of the Nozzle and blading arrangement is connected via the opened nozzle valve ao is acted upon with flue gases. 14. Apparatus according to claim 12 and / or 13, characterized in that at least a rotor disk with at most one row of blades is busy. 15. The device according to claim 14, characterized in that all carriers that preferably form a common turbine rotor, with at most one row of blades are occupied, the rotor preferably having two or three disks. [6. Device according to one or more of claims 13 to 15, characterized in that the number of deflagration chambers is equal to an integral multiple of the number of working cycle sections of the working cycle of a deflagration chamber, each deflagration chamber having at least η + ι controlled fire gas outlets.
17. Device according to one of claims 13 to 16, characterized in that a Treibgaseiitiiahmek'itung connected to the exhaust valve assemblies of each deflagration chamber for residual combustion gases displaced by charge air is, the same propellant gas sampling line with the blading of the last Turbine stage is in fire gas conducting connection. 18. Device according to one of claims 13 to 16, characterized in that in the way the residual fire gases released through the exhaust valve arrangements of the deflagration chambers there is a nozzle and blading arrangement adapted to the gradient of the same, ' wherein the fire gas receiving spaces of the residual combustion gases processing nozzle and Blading arrangement and that acted upon by the next higher-tensioned partial amount of fire gas Nozzle and blading arrangement together to form a common discharge housing space are united. 19. Device according to one of claims 13 to 16, characterized in that the residual fire gases Line piece leading to nozzle and blading arrangements to a filling chamber arrangement is connected, the fire gases from the nozzle and Beschaufclungsanordnung picks up from a next higher-tensioned Feuergasteilmengc is applied. 20. Device according to one or more of claims 13 to 19, characterized by Assignment of four deflagration chambers to two nozzle and blading arrangements, each deflagration chamber in addition to two nozzle valves for at least one exhaust valve Residual combustion gases and at least one operating medium inlet element, in particular a charge air valve, comprising, the exhaust valves having a third nozzle and blading arrangement can be assigned. Referred publications: German patents No. 614 561, 606883, 537, 558785, 555560. For this purpose 2 sheets of drawings © 509 578/213 10.55