阅读说明：本技术 脉冲驱动装置 (Pulse driving device ) 是由 H.鲁格 T.皮特汉斯 M.苏特 于 2018-11-05 设计创作，主要内容包括：一种用于重复产生爆炸、特别用于驱动飞行器的装置。其包括：燃烧室(21)；至少一个供给管线,用于将可流动爆炸性材料或在混合时形成爆炸性材料的组分供给到燃烧室(21)；用于定向排出通过点燃所述燃烧室(21)中的爆炸性材料而产生的气体压力的排出装置；用于部分或完全关闭排出装置的可移动喷嘴调节元件(26)；致动元件(25),其构造成在排出装置打开之后并且在爆炸气体通过排出装置流出期间进一步打开排出装置。在此,所述排出装置具有用于排出气体压力的多个部分喷嘴(40),并且所述部分喷嘴(40)的位置可以通过所述致动元件(25)来设置。(A device for the repeated generation of explosions, in particular for driving an aircraft. It includes: a combustion chamber (21); at least one supply line for supplying flowable explosive material or components which form explosive material when mixed to the combustion chamber (21); -discharge means for the directed discharge of the gas pressure generated by the ignition of the explosive material in the combustion chamber (21); a movable nozzle adjustment element (26) for partially or fully closing the discharge means; an actuating element (25) configured to further open the evacuation device after it is opened and during the outflow of the explosive gas through the evacuation device. The discharge device has a plurality of partial nozzles (40) for discharging the gas pressure, and the position of the partial nozzles (40) can be set by means of the actuating element (25).)

1. Device for repeatedly generating an explosion and for converting chemical energy into kinetic energy of an outgoing exhaust gas of said explosion, in particular for generating thrust for propelling an aircraft, comprising:

a combustion chamber (21) for receiving a combustion gas,

at least one supply conduit for supplying flowable explosive material or components which form explosive material when mixed to the combustion chamber (21);

-exhaust means for the directed exhaust of the gas pressure generated in the combustion chamber (21) by the ignition of the explosive material,

a movable nozzle adjustment element (26) for partially or completely closing the discharge means;

an actuating element (25) which is designed to open the discharge device further after it has been opened and during the outflow of the explosion gas through the discharge device,

characterized in that the discharge means comprise a plurality of partial nozzles (40) for discharging the gas pressure, and the position of the partial nozzles (40) is adjustable by the actuating element (25).

2. The device according to claim 1, wherein each of the partial nozzles (40) comprises a partial valve seat (41) and a partial valve body (42), and a partial nozzle inlet region (43) is determined by the position of the partial valve body (42) relative to the partial valve seat (41), and wherein the nozzle adjusting element (26) determines the position of the partial valve body (42) relative to the partial valve seat (41).

3. The device according to claim 1 or 2, wherein the openings of the partial nozzles (40) comprise annular openings arranged concentrically to each other.

4. The device according to any one of claims 1 to 3, wherein the combustion chamber (21) has a variable volume.

5. The device according to claim 4, comprising a displaceably arranged partition wall (28) which delimits the combustion chamber (21).

6. The device according to claim 5, wherein the partition wall (28) forms a delimitation of the combustion chamber (21) opposite the exhaust means, and in particular the actuating element (25) is guided through the partition wall (28).

7. The device according to any one of claims 1 to 6, comprising compression means (1, 2) for compressing the flowable explosive material or at least one of the components of the explosive material.

8. The device according to claim 7, wherein the compression device is a continuously operated compressor (2), in particular a rotary compressor, such as a turbo compressor.

9. An arrangement according to claim 8, wherein the compressor (2) is driven by a turbine (4) and the turbine (4) is arranged to be driven by an exhaust jet (5) from a turbine combustion chamber (6), wherein the turbine combustion chamber (6) is different from the combustion chamber (21).

10. An arrangement according to claim 8, wherein the compressor (2) is driven by a turbine (4) and the turbine (4) is arranged to be driven by the exhaust gas (17) of the combustion chamber (21).

11. The device according to claim 10, comprising an output for delivering mechanical work to a mechanical consumer, in particular to at least one of:

fluid machine, in particular a propeller, for propelling a vehicle, in particular an aircraft,

a generator for conversion into electrical energy.

12. Apparatus according to any one of claims 7 to 11, comprising compression means in the form of an air inlet (1) for compressing incoming air at a supersonic speed of the apparatus relative to ambient air.

13. A method for repeatedly producing an explosion and for converting chemical energy into kinetic energy of an outgoing exhaust gas of the explosion, in particular for producing thrust for propelling an aircraft, repeatedly performing the following steps:

feeding flowable explosive material or components which form the explosive material when mixed into a combustion chamber (21), wherein a discharge device of the combustion chamber (21) is at least partially closed by a movable nozzle adjusting element (26); and generating an overpressure in the combustion chamber (21) with respect to the ambient pressure;

opening the discharge device;

igniting the explosive material in the combustion chamber (21);

leading out the explosive gas through the discharge device;

-at least partially closing the discharge means by means of the movable nozzle-adjusting element (26);

it is characterized in that the preparation method is characterized in that,

in order to open the discharge device and discharge the explosion gas, a plurality of partial nozzles (40) are opened synchronously with one another;

in order to at least partially close the discharge device, a plurality of partial nozzles (40) are closed at least partially in synchronism with one another.

14. The method according to claim 13, wherein the partial steps of opening the discharge device, igniting the explosive material in the combustion chamber, and conducting out explosive gas through the discharge device by means of the movable nozzle adjustment element are performed in a temporally overlapping manner.

15. Method according to claim 13 or 14, wherein the partial nozzles (40) each comprise a partial valve seat (41) and a partial valve body (42), and the partial valve bodies (42) are moved synchronously with each other relative to the partial valve seat (41) by means of the nozzle adjusting element (26).

Technical Field

The invention relates to a device and a method for the repeated generation of explosions for energy conversion, for example for the generation of thrust, in particular in an aircraft.

Background

Propulsion engines, so-called Pulse Detonation Engines (PDEs), are known, with which the temperature and pressure increase of the isovolumetric combustion (i.e. by explosion) at constant volume is exploited, instead of continuous combustion at constant pressure. Unlike internal combustion engines in which the pressure generated drives the piston in a direct manner, it is desirable to maximize the kinetic energy of the exiting combustion gases. Thus, the combustion gases produced by the explosion will accelerate to a maximum velocity for maximum thrust generation and will be used for propulsion purposes. Holzwarth turbines for power generation and pulse jet engines that generate thrust at high frequencies by explosion are known.

A method for generating pressure pulses by explosion is described in european patent application EP 2319036a2 (and likewise US 2011/180020a 1). In this case, the mixture of oxidizing agent and combustible substance is ignited in a container closed by a valve and an explosion is produced. Shortly before ignition the valve is opened and the pressure wave of the explosion can be directed to its designated location via the outlet opening. This device, also known as an Explosion Generator (EG), is nowadays used for cleaning contaminated steam boilers.

In european patent application EP3146270a1 (and also in US 2017/082069a 1) a pulse detonation drive is disclosed, which comprises an actuating device which, in the event of an explosion gas flowing out through an outlet nozzle, adjusts the area ratio between the nozzle inlet area and the nozzle outlet area, which ratio at least approximately follows a desired area ratio for generating a maximum outlet velocity of the explosion gas as a function of the pressure in the explosion space.

Disclosure of Invention

A possible object of the invention is to provide a device and a method of the initially mentioned type which achieve an improved conversion of the released energy into kinetic energy of the combustion gases in the event of an explosion.

This object is achieved by means of a device and a method having the features of the respective independent patent claims.

The device is used for repeatedly generating explosions and for converting chemical energy into kinetic energy of the outgoing exhaust gases of said explosions, in particular for generating thrust for propelling an aircraft. It includes:

a combustion chamber as an explosion space,

at least one supply conduit for supplying flowable explosive material or components which form explosive material when mixed to the combustion chamber;

-means for the directed discharge of the gas pressure generated in the combustion chamber by the ignition of the explosive material,

a movable nozzle adjustment element as a closing element for partially or completely closing the discharge device;

an actuating element designed to further (continuously) open the evacuation device after the opening of the evacuation device and during the outflow of the explosive gas through the evacuation device.

The discharge device comprises a plurality of partial nozzles for discharging the gas pressure, and the position of the partial nozzles can be adjusted by means of an actuating element.

The partial nozzles each correspond to a separate opening of the discharge device. In principle, the individual openings are individually closable, but in an embodiment the individual openings can be activated and closed jointly.

With the same stroke of the actuating element, a larger cross-sectional area can be released when using a plurality of individual small partial nozzles than when using only one nozzle with only one nozzle opening. This means that in the case of only one large nozzle, in order to release the same cross-sectional area, it is necessary to open the actuating element significantly further. This means that the speed of the actuating element must be higher in order to achieve the same increase in cross-sectional area per unit time. In practice, the maximum speed of the actuating element is a critical, limiting variable. It is therefore advantageous if the necessary speed of the actuating element is kept as small as possible and the area released here is kept as large as possible.

In an embodiment, therefore, the nozzle, in particular the convergent-divergent nozzle, is realized by the sum of the partial nozzles and ensures that the optimum ideal area ratio between the nozzle end (nozzle outlet area) and the nozzle neck (nozzle inlet area) is always adjusted at least approximately during the entire outflow time. Thereby, the outflow velocity of the exhaust gas (burned gas) of the device or its kinetic energy can be ideally maximized at least approximately. The outflow velocity preferably exceeds the speed of sound. If the device or vehicle is directly driven/propelled by the exhaust, a thrust is generated that affects the propulsion, depending on the outflow speed. Here, the pushing force can be maximized according to the internal pressure by the corresponding opening width of the discharge device. If the turbine is driven by the exhaust gas, only a portion of the kinetic energy of the exhaust gas is used for this drive. Depending on the design and setup/regulation of the turbine, the remaining part of the kinetic energy at the outlet of the turbine can be used directly to drive/propel the device or vehicle.

Overall, a high efficiency of conversion of chemical energy into mechanical energy or work can be achieved by the device. Chemical energy is defined as the form of energy that is stored in an energy carrier in the form of a compound and can be released in the case of a chemical reaction.

In contrast to the known pulse detonation drive of european patent application EP3146270a1 (or US 2017/082069a 1), the rate at which the overall cross-sectional area of all nozzles changes can be increased.

In an embodiment, each partial nozzle comprises a partial valve seat and a partial valve body, and the partial nozzle inlet area is determined by the position of the partial valve body relative to the partial valve seat. The nozzle adjusting element determines the position of the partial valve body relative to the partial valve seat.

In this case, the partial nozzle can be closed by a movement of the respective partial valve body toward the respective partial valve seat. The sum of the partial nozzle inlet areas forms the total nozzle inlet area and the sum of the partial nozzle outlet areas forms the total nozzle outlet area.

In an embodiment, a partial valve body is each part of the valve body. Thus, the movement of the valve bodies causes a movement of the partial valve bodies relative to one another, in particular a movement of the partial valve bodies towards or away from the partial valve seats. In an embodiment, the partial valve seats are each formed on a common valve seat body.

In an embodiment, the openings of the partial nozzles comprise annular openings arranged concentrically to each other.

In an embodiment, the openings of the partial valves each comprise a separate circular opening. The openings may all be the same size or the same diameter, or may be of different diameters. In an embodiment, the openings of the partial valves each comprise a separate linear opening.

In an embodiment, the partial nozzles each comprise a partial valve body in the form of a regulating valve needle, and the partial nozzle inlet area of the partial nozzle is determined by the position of the regulating valve needle relative to the partial valve seat.

In an embodiment, the regulating valve needles each have an outer contour, in particular an at least approximately conical outer contour, which tapers towards the valve tip.

In an embodiment, part of the valve seat and part of the valve body form respective convergent-divergent parts of part of the nozzle.

A flowable explosive substance or a flowable explosive mixture is introduced into the combustion chamber, said flowable explosive substance or flowable explosive mixture being formed by mixing components which are preferably non-explosive per se. The flowable substance and/or substance mixture is, for example, gaseous, fluid, powdered, dusty or powdery or a mixture of these component substances. Typically, one component is a combustible and the other component is an oxidant. For example, the mixture consists of two pressurized gases. All variants and possible combinations of substances and mixtures are referred to herein and hereinafter simply as "flowable explosive materials" and should not be understood as being limiting to a single substance or to a particular mixture.

In the case of constant volume combustion, a higher combustion temperature is achieved than in the case of combustion at constant pressure. In the case of explosive combustion, a large pressure increase is additionally achieved. For example, in the case of stoichiometric combustion of air and natural gas at constant volume, a pressure increase of 7.5 times can be achieved, i.e. in the case of an initial pressure of the mixture of 10 bar, the peak pressure in the explosion space is about 75 bar. In such applications with isochoric combustion, the aim is to produce a gas jet that leaves the explosion space at maximum velocity.

In an embodiment, the device is provided for use with an initial pressure provided between ambient pressure and twenty times ambient pressure, for example between six and twelve times ambient pressure.

In an embodiment, the combustion chamber has a variable volume.

Thereby, the volume of the combustion chamber can be reduced with respect to the maximum volume. In the case of a reduction in the volume of the combustion chamber, the burnt mixture flows out more quickly than the maximum volume. The shortened outflow duration results in thrust being present for a shorter duration. Thus, the average thrust of the device over several pulses is reduced. The reduced volume simultaneously results in a smaller amount of explosive mixture per pulse and also on time average.

In an embodiment, the device comprises a displaceably arranged partition wall which delimits the combustion chamber.

Thereby, the change of the combustion chamber volume can be achieved in a mechanically simple manner.

In an embodiment, the partition wall forms a delimitation of the combustion chamber opposite the exhaust means. In particular, the actuating element can be guided through the partition wall.

Thereby, a change of the volume of the combustion chamber can be achieved in a space-saving manner, and the rotationally symmetrical shape of the combustion chamber can be maintained independently of the position of the partition wall.

In an embodiment, the actuating element comprises a drive device for driving the opening movement of the discharge device, in particular by means of a drive device realized by means of an auxiliary explosion device in which an auxiliary explosion generates a force which contributes to the opening movement.

Details regarding the actuation of such an auxiliary explosive device are described in the initially mentioned EP 2319036a 2. In particular, according to an embodiment, the explosion in the auxiliary explosion device may be synchronized with the explosion in the explosion space by a pipe, also called delay pipe.

By reacting the escaping explosion gas against the actuating element, a further force or force component can be generated which contributes to the opening movement.

In an embodiment, the actuating element is configured to temporarily completely close the discharge device. Thus, the pressure in the explosion space can be increased above ambient pressure before ignition.

In an embodiment, the device comprises a compression device for compressing at least one of the components of the explosive material or the flowable explosive material.

Thus, prior to ignition, the pressure of the explosive material may increase relative to ambient pressure. The pressure generated by the explosion is a function of this pressure before ignition and therefore also increases accordingly. Therefore, the thrust force generated by the device can also be increased.

In an embodiment, the compression device is a continuously operating compressor, in particular a rotary compressor, for example a turbo compressor.

The compressor may be a rotary compressor, in particular a turbo compressor.

In an embodiment, the compressor is driven by a turbine and the turbine is arranged to be driven by an exhaust gas jet from a turbine combustion chamber, wherein the turbine combustion chamber is different from the combustion chamber.

In other words, the compressor, the turbine and the turbine combustor are here components of a gas turbine. A gas turbine is used in order to operate the compressor. The turbine or turbine combustor may operate with the same combustibles as the combustor. Thus, the explosive material may be the same mixture as in the combustion chamber, but with a different mixing ratio.

In an embodiment, the compressor is driven by a turbine, and the turbine is arranged to be driven by the exhaust gas of the combustion chamber.

Thus, in contrast to a topology with a separate gas turbine, the exhaust gas flow of PE is used here for the drive of the compressor. This simplifies the plant and increases the overall efficiency of the plant due to the generally better efficiency of PE compared to conventional gas turbines.

In an embodiment, the device comprises an output for delivering mechanical work to a mechanical consumer.

In an embodiment, the device comprises an output for conveying mechanical work to a fluid machine. This may be a propeller for propelling a vehicle, in particular an aircraft.

In an embodiment, the apparatus comprises an output for delivering mechanical work to the generator. Thus, the mechanical work is converted into electrical energy.

In an embodiment, the device comprises a compression device in the form of an air inlet for compressing the incoming air at a supersonic velocity of the device relative to the ambient air.

Such a compression device may alternatively or additionally be present in the compressor. Thus, in particular in the case of aircraft, the compression in the compressor may be replaced by compression in the air inlet when supersonic speeds are reached.

In an embodiment, the discharger is configured to adjust an area ratio between a total nozzle inlet area and a total nozzle outlet area of the discharger in case the explosive gas flows out through the discharger, said ratio at least approximately following a desired area ratio to generate a maximum outlet velocity of the explosive gas depending on the pressure in the combustion chamber.

This may be achieved by a nozzle adjustment element arranged to vary the total nozzle inlet area, which is the sum of the partial nozzle inlet areas. Here, the actuating element may be configured to control the movement of the nozzle adjusting element for adjusting the total nozzle inlet area at least approximately according to the mentioned ideal area ratio.

In an embodiment, the actuating device comprises a drive device for driving the opening movement of the nozzle adjusting element, in particular by means of a drive device realized by means of an auxiliary explosion device with an auxiliary combustion chamber, in which auxiliary explosion generates a force that contributes to the opening movement.

In an embodiment, the actuating device comprises a braking device for delaying the opening movement of the regulating valve, in particular by a braking device realized by a gas compression spring or a camshaft or a combination of a gas compression spring and a camshaft.

In an embodiment, the nozzle adjustment element is configured to temporarily completely close the discharge opening.

The method for repeatedly generating an explosion and for converting chemical energy into kinetic energy of the outflowing exhaust gas of the explosion, in particular for generating thrust for propelling an aircraft, comprises repeatedly performing the following steps:

feeding flowable explosive material or components which form explosive material when mixed into a combustion chamber, wherein the discharge means of the combustion chamber is closed at least partially by a movable nozzle adjustment element; and generating an overpressure in the combustion chamber with respect to the ambient pressure;

opening the discharge device;

igniting the explosive material in the combustion chamber;

-leading out the explosive gas through an exhaust:

at least partially closing the discharge means by means of a movable nozzle-adjusting element.

In this case, the amount of the solvent to be used,

for opening the discharge device and discharging the explosion gas, the partial nozzles are opened synchronously with one another.

In order to at least partially close the discharge device, the partial nozzles are closed at least partially synchronously with one another.

In an embodiment, the partial steps "opening the discharge device", "igniting the explosive material in the combustion chamber" and "conducting the explosive gas through the discharge device by means of the movable nozzle adjusting element" are performed in a temporally overlapping manner.

In an embodiment, the partial nozzles each comprise a partial valve seat and a partial valve body, and the partial valve bodies are moved synchronously with each other relative to the partial valve seats by means of the nozzle adjusting element.

Further preferred embodiments will emerge from the dependent patent claims. The features of the method claims may be combined with the apparatus claims and vice versa, where appropriate.

Drawings

The subject matter of the invention is explained in more detail below by means of preferred embodiment examples presented in the figures. Schematically showing:

FIG. 1 shows a pulse driver or Pulse Engine (PE);

FIG. 2 illustrates the operating mode of PE, wherein the volume of the combustion chamber of the PE is variable;

FIG. 3 illustrates an operating mode with variable frequency;

FIG. 4 illustrates increasing the opening speed by using a plurality of partial nozzles with individual nozzle openings;

FIG. 5 illustrates different nozzle bodies each having a plurality of nozzle openings;

FIG. 6 shows a PE supercharged by a single gas turbine;

FIG. 7 shows a PE supercharged by a turbine driven by the PE's exhaust;

FIG. 8 shows a PE with a propeller driven by a turbine; and

fig. 9 shows a PE with a generator driven by a turbine.

Basically, in the figures, identical or equivalently functioning components are provided with the same reference numerals.

Detailed Description

Fig. 1 shows an apparatus for repeatedly generating an explosion, hereinafter also referred to as pulse motor or PE 15. The combustion chamber 21 or the explosion space can be filled with a flowable explosive material, for example an explosive gas mixture, via a filling device. To this end, the filling means comprise a combustion chamber air inlet 12 for supplying an oxidant, such as air, and a combustion chamber combustible inlet 14 for supplying a combustible or fuel, such as hydrogen. The flowable explosive material thus formed can be ignited by an ignition device (e.g., by spark plug 23) and initiate an explosion.

The outlet of the combustion chamber 21 for the exhaust gas 17 passes through the nozzle opening 27. The nozzle opening 27 is closable by the nozzle adjustment element 26 of the actuating element 24. In the neutral position, the nozzle opening 27 is closed by the actuating element 25, the actuating element 25 being held in this position by the air spring 24.

During filling of the combustion chamber 21, the nozzle adjustment element 26 seals the combustion chamber 21 towards the nozzle opening 27. In this way, an initial pressure with an overpressure can be generated, with which in turn a greater explosion pressure can be generated.

The auxiliary combustion chamber 22 may likewise be filled with explosive material via another filling device having an auxiliary combustion chamber air inlet 11 and having an auxiliary combustion chamber combustible inlet 13. The actuating element 25 can be moved by means of an explosion in the auxiliary combustion chamber 22 against the pressure of the air spring 24 and the nozzle opening 27 can be opened thereby.

In operation of the PE 15, the auxiliary combustion chamber 22 and the combustion chamber 21 may both be filled with the same explosive material. In principle, different materials or different mixtures can also be applied in the two combustion chambers. First, the explosive material is ignited in the auxiliary combustion chamber 22 by the assigned spark plug 23. Thereby, the pressure in the auxiliary combustion chamber 22 rises and the actuating element 25 starts to move and thus starts to release the nozzle opening 27 of the combustion chamber 21. The explosive material is then ignited in the combustion chamber 21, for example by means of a further spark plug 23.

Therefore, the ignition plugs 23 of the auxiliary combustion chamber 22 and the combustion chamber 21 are ignited shortly after each other. The delay between the two ignition moments can be chosen such that the discharge speed of the exhaust gases 17 or the total energy converted into kinetic energy of the exhaust gases 17 is maximized.

In another embodiment, the material in the combustion chamber 21 is ignited by an explosion from the auxiliary combustion chamber 22 and directed through the delay tube via a tube or delay tube which is also filled with an explosive material.

The filling of the combustion chambers (combustion chamber 21 and auxiliary combustion chamber 22) may be done in stages and in the following order, first with oxidant through combustion chamber air inlet 12 or auxiliary combustion chamber air inlet 11 and then with combustible through combustion chamber combustible inlet 14 or auxiliary combustion chamber combustible inlet 3. Thus, the corresponding combustion chamber wall can be cooled with the oxidant during filling, while the mixture cannot ignite on the combustion chamber wall. The resulting cooling possibility allows the cycle frequency to be maximized. Thus, the power density, and therefore the maximum thrust per combustion chamber volume, may be maximized.

With regard to other elements of the design and method aspects for the operation of the device, reference is made to the initially mentioned EP3146270a1, the content of which is hereby incorporated into the present application.

The combustion chamber 21 comprises a partition wall 28 which forms part of the entire wall of the combustion chamber 21. The volume of the combustion chamber 21 can be changed by displacing the partition wall 28. The partition wall 28 can be displaced by a schematically illustrated adjusting device 281 and the volume can be changed thereby. In fig. 1, the partition wall 28 is movable, for example, in the same direction as the direction in which the actuating element 25 reciprocates.

Fig. 2 shows the operating modes of the PE 15 with variable volume in its combustion chamber, each with the time course of the thrust force F generated by the PE 15: in the upper process there is a larger combustion chamber volume and in the lower process there is a smaller combustion chamber volume but with a constant pulse period tc. In the case of a reduction in the volume of the combustion chamber, the burnt mixture flows out more rapidly than with a larger volume. The shortened outflow duration results in the thrust being dominant for a shorter duration. The average thrust of PE 15 therefore decreases with time. Due to the lower volume, the consumption of combustibles and oxidants per pulse and the time average thereof also decreases.

FIG. 3 shows the mode of operation of a PE 15 with a variable frequency, with a larger operating frequency (or smaller pulse period tc 1) in the upper process and a smaller operating frequency (or larger pulse period tc 2) in the lower process. Here, only the number of thrust pulses per unit time is reduced, while the pulses themselves remain the same, i.e. have the same amount. Thereby, the thrust and the consumption in time averaging are also reduced.

In operation, the volume as well as the frequency of operation may vary. Thereby, the same average thrust can be achieved with different combined volumes and operating frequencies, and operation optimized. For example, the stoichiometry of the mixture may vary therewith. For example, a fast load change can be achieved by adjusting the operating frequency, and then, in case of a constant load, by slowly adjusting the volume while compensating by the operating frequency. In the case of optimization, consideration may be given to the fact that the individual pulses may all be of a certain optimized time course or pulse type in the case of thrust regulation by the operating frequency. Regarding heat loss, a large volume is more advantageous than a small volume in terms of surface to volume ratio. In the case of driving an exhaust turbine, there is an additional degree of freedom in selecting the operating state: depending on how the efficiency of the exhaust gas turbine behaves as a function of PE frequency and PE volume, it may be advantageous if the PE volume can be reduced in the partial load region.

Fig. 4 shows that the opening speed is increased by using a plurality of partial nozzles with individual nozzle openings. On the left side a nozzle with a single nozzle opening 27 is shown, and on the right side a nozzle with a plurality of partial nozzles 40 is shown. Each partial nozzle 40 comprises a partial valve seat 41 and a partial valve body 42. Part of the valve body 42 can bear on part of the valve seat 41 and thus close said part of the nozzle 40 and can be moved away from part of the valve seat 41 for opening part of the nozzle 40. The partial valve bodies 42 can be moved jointly, i.e. synchronously, by the actuating element 25, for example by forming the partial valve bodies 42 on the same body, or all fastened to each other in a rigid manner on the actuating element 25 or on a common actuating device. When moving part of the valve body 42 away from part of the valve seat 41, a larger cross-sectional area is released with the same stroke of the valve body or actuating element 25 than when using only one nozzle. Thus, the temporal variation of the total cross-sectional area of all the partial nozzles 40 is greater than when only one single nozzle is used. Thus, by including a plurality of individual partial nozzle openings 27, the speed of opening the nozzle openings 27 and releasing a larger cross-sectional area can be increased without having to move the actuating element 25 faster.

The plurality of partial nozzles 40 or nozzle openings 27 may be shaped differently. Fig. 5 shows different nozzle bodies 30, each having a plurality of nozzle openings 27 arranged in concentric rings, radial linear jets and circular openings with different diameters. In other embodiments, the circular openings all have the same diameter (not shown).

Fig. 6 shows a PE 15 that is supercharged (charging) by a separate gas turbine. Here, fuel or combustible is delivered from the combustible tank 7 via the fuel delivery means 18 and via the fuel inlet valves (auxiliary combustion chamber combustible inlet 13 and combustion chamber combustible inlet 14) to the combustion chamber 21 and auxiliary combustion chamber 22 of the PE 15. Another fuel delivery device 18b delivers fuel to the turbine combustor 6 operating in a continuous (i.e. non-pulsating) manner via the turbine combustor feed valve 10 and drives the compressor 2 via the turbine 4 and the shaft 3. The compressor 2 is supplied with air from the air inlet 1, compresses said air and leads it via air inlet valves (auxiliary combustion chamber air inlet 11 and combustion chamber air inlet 12) into the combustion chambers 21, 22.

The compressor 2 may be a radial compressor or an axial compressor, and may be one-stage or multi-stage. The turbine 4 and the further turbine 4b may be one or more stages.

The air may already be pre-compressed in the air inlet 1 by ram pressure compression. The higher the mach number of the incoming air 16, the greater this (pre) compression. Since, at sufficiently high mach numbers, the air is already sufficiently compressed in the air inlet 1, the compressor 2 becomes redundant at these mach numbers. At the mach number at which the compressor 2 is required, the bypass valve 8 is closed and the compressor inlet valve 9 is opened. If the compressor is no longer in use due to the high velocity of the incoming air 16, the compressor inlet valve 9 is closed and the bypass valve 8 is opened. Thereby, the compressor 2 is bridged. In this case, the compressor outlet valve 19 is also closed.

The vehicle, in particular an aircraft, can be propelled by the outflowing exhaust gas 17 of the PE 15 or by the thrust generated by it.

Fig. 7 shows a PE 15 supercharged by a further turbine 4b, which turbine 4b is driven by the exhaust 17 of the PE 15 via the common shaft 3. The compressor 2 may also be driven via a turbine 4b driven by the exhaust gas 17 from the PE 15, instead of being driven by a separate gas turbine as an auxiliary component. In this case, the additional fuel supply 18b and the turbine combustion chamber 6 can be dispensed with.

Fig. 8 shows a PE 15, wherein a further turbine 4b, driven by the exhaust gas 17 of the PE 15, drives a propeller or propeller 201, in particular via a retarder 20. The propeller may be of shrouded or unshrouded design. Like turboprops, the propellers are used to propel vehicles, in particular aircraft. The exhaust jet 5 of the other turbine 4b can likewise contribute to the propulsion.

Fig. 9 shows a PE 15, wherein another turbine 4b driven by the exhaust 17 of the PE 15 drives a generator 202. If necessary, a speed reducer 20 may be arranged between the shaft 3 and the generator 202.