DE102015001615A1 - Device for generating kinetic energy, device for compression and method for obtaining electrical energy - Google Patents

Abstract

The invention relates to a device for generating kinetic as well as electrical energy from an influx of gas or fluids or from an exhaust gas flow, wherein the kinetic energy contained in the influx of gas or fluids or in the exhaust gas flow is used to accelerate bodies or their kinetic energy Converting energy into electricity, storing this electrical energy, and retrieving it when needed. Furthermore, the invention relates to the use of the device according to the invention as well as methods for the construction and the production of electrical energy.

Description

Related patents

• AT 000000221318 B ; CH 000000508809 A ; CH 000000266474 A ; CH 000000322020 A ; DE 60 2004 001 691 T2 ; DE 20 2013 001 098 U1 ; DE 00 0069 301 008 T2 ; DE 00 0019 538 769 A1 ; DE 00 0003 014 518 A1 ; DE 00 0003 490 164 T5 ; DE 20 2011 102 001 U1 ; DE 10 2011 007 386 A1 ,

The invention and / or the apparatus or associated apparatuses associated with the invention enables the positive and / or negative acceleration and / or maintenance of a constant speed of a physical object connected to the invention or to the invention. The use of the device according to the invention increases the efficiency of an internal combustion engine and of other working and power machines and other machines which serve to convert kinetic and thermal energy into electrical energy.

The invention and / or the device or associated devices associated with the invention further relates to the recovery of electrical energy from a gas, fluid, incoming to the invention or the device or devices connected thereto, regardless of whether the aforementioned matter is an oxidizer acts. The invention and / or associated with its invention device or associated devices also relates to the recovery of electrical energy from an exhaust stream of an internal combustion engine as well as on this device building combustion engines. This invention and / or the device or devices associated with the invention further relates to methods for obtaining electrical energy.

By use of the invention and / or the device or devices associated with the invention, devices connected to the device or the device of the invention itself, which are mobile, are accelerated and / or speed maintained. The device according to the invention relates to working and power machines or their combination, as well as their underlying principles and methods. The device according to the invention, which is immobile, allows the production of electrical energy.

The use of the electrical energy harvesting apparatus of the present invention increases the efficiency of converting kinetic energy into electrical energy because the kinetic energy of a moving gas, fluid, not previously used to generate electrical energy is now positive Contribution to the energy balance in the conversion of kinetic energy into electrical energy in dedicated devices such as jet engines, jet engines and Aeroderivaten this, wind or water or fusion power plants or in internal combustion engines as well as building on this device or connected to her devices makes. By using the device according to the invention, the efficiency of these internal combustion engines or devices increases, since the kinetic energy of the exhaust gas flow, which is not previously used for the production of electrical energy, now makes a positive contribution to the energy balance of combustion in the internal combustion engine. But also the kinetic energy of the moving gases, fluids is converted with higher efficiency into electrical energy.

It is known that the efficiency of internal combustion engines is about 30%. The efficiency for the purposes of this invention is the quotient of the useful energy that is available to an engine after combustion, and the energy that is supplied to an engine in the form of a fuel. Beneficial energy is also the kinetic or thermal energy of a gas, fluid resulting from an actual velocity or actual velocity relative to the device of the invention. The ratio may take values between 0 and 1, with larger values indicating good utilization of the fuel energy supplied and smaller values indicating low utilization.

The aim of research and industrial development is to increase the efficiency of internal combustion engines in particular. But the goal of research and industrial development is also to use any actual form of energy, especially in electrical energy, but also to convert existing energy. In particular, the conversion of energy that does not result from combustion processes is constantly being researched and developed. And, always a great potential in an improved utilization of the energy contained in the exhaust stream is seen.

Exhaust gases are produced during the combustion of an air-fuel mixture in the combustion chamber of an engine and are discharged via exhaust pipes to the outside air or to the environment. The exhaust gases leave the combustion chamber under high pressure, high speed and high temperatures and are discharged through one or more exhaust pipes. The exhaust stream thus contains both thermal and kinetic energy, and these properties are considered as the starting point for considerations of how to increase the efficiency of an internal combustion engine.

The conversion of energy that was previously unusable or not maximally used efficiently is a further relevant approach for the devices according to the invention. In particular, the development of kinetic energy of gases by so-called wind power plants or fluids by hydroelectric power plants or electrical energy-generating transformation of the states of matter of these elements are in a power hungry society research and development. The efficiency increase in terms of increasing the efficiency but also the diversification of possible conversion devices by the present invention should be another starting point.

In the prior art, for example, devices are described which use the kinetic energy of an exhaust gas flow to increase the performance of an internal combustion engine. For this purpose, outside air is compressed and this compressed outside air provided to the internal combustion engine. Such devices are referred to in the literature as turbojet, turbocharger, turbo exhaust fan or turbocharger. Such devices are also referred to as fans, compressors or propellers, depending on their use and application. In addition to the aviation and shipping industry, this inherent in the exhaust flow energy is also used in the automotive or power generation / energy conversion industry to increase performance or increase in efficiency.

In this case, such a turbine, as far as positioned in the exhaust gas flow, converts the kinetic energy of the exhaust gas constituents which flow out of the combustion chamber after combustion into a rotational movement. This rotational movement is transmitted via a shaft axially or coaxially to a second turbine, which is also attached to the shaft axially or coaxially fixed. This turbocharger compressor turbine sucks outside air and compresses this outside air, which is then fed to the engine. The combustion of compressed air in the combustion chamber leads to an increase in the power of the internal combustion engine in terms of torque, power output or thrust or traction. Turbines are therefore used to utilize the kinetic energy of the exhaust gas flow to compress outside air and thus increase the efficiency of an engine. Again, aviation, shipping, automotive and power generation / energy conversion industries use this.

Such a turbine as referred to above, as far as positioned in or positioned in a gas flow or fluid accelerating towards the turbine or moving toward the gas or fluid with the device connected thereto, and the gas or fluid is not exhaust gas converts the kinetic energy of the gas or fluid into a rotational motion.

The aforementioned turbines may further convert the rotary motion to electrical energy by means of correspondingly incorporated devices.

In addition to people's changing mobility needs, resources-saving drives for people's mobility are particularly demanded, and as more and more technical devices are introduced into vehicles for mobility that are not necessarily able to serve but also serve more electrical energy is required for their operation to provide the fuels used for the conversion of thermal and kinetic energy, or to convert energy present in gases and fluids into electrical energy and to provide corresponding equipment.

The kinetic energy of the exhaust gas streams in internal combustion engines, but also energy inherent in the states of matter (gases, fluids) or in their kinetic energy, are convertible into electrical energy and usable for devices that can set a physical Gegegnstände in motion. Since, in general, according to the principle of energy conservation, energy is not lost, only converted is covered by it, in principle the above can put a turbine in a rotary motion.

Prior art turbines in the above-mentioned are in the exhaust stream or influx of gas or fluid-based profiles mounted on a movable axial / coaxial shaft and due to their Positioning on the shaft are adapted to convert the kinetic energy of the accelerated exhaust gas flow and / or the gas, the fluid in a rotational movement of the axial / coaxial shaft about its longitudinal axis.

A turbine in the sense of the prior art is a paddle wheel, a turbine wheel, an axial turbine, steam turbine, gas turbine, radial turbine, spiral turbine, propeller turbine or a turbine, which is located in the exhaust pipe of an internal combustion engine and a propeller. Turbine in the context of the invention is also the compressor, the fan and paddle wheels, turbine wheels in jet engines or in such stationary devices. In the context of the prior art, it is another device for converting kinetic energy and kinetic energy or electric energy propellers for air and water vehicles are covered by the invention.

The exhaust pipe connects the combustion chamber of the internal combustion engine with the outside air. The resulting in the combustion of an air-fuel mixture in the combustion chamber of the internal combustion engine exhaust gases are discharged from there to the environment. This occurs due to the pressure and temperature conditions in the combustion chamber of the engine with a high velocity of the exhaust stream and at high temperatures.

In the process, the exhaust components collide with the turbine blades of the (exhaust) turbine and set them in motion by transferring their kinetic energy to the exhaust gas turbine. This creates a rotational movement of the exhaust gas turbine.

In the process, fluids and gases impinge on the turbine blades of the (exhaust) turbine and set them in motion by transmitting their kinetic energy to the (exhaust) turbine, thus producing a rotational movement of the exhaust gas turbine.

The rotational movement of the axial / coaxial shaft is thus generated by the fact that the outgoing of the kinetic energy of the exhaust gases or the fluid pressure offset the profiles on the shaft in a rotational movement of the axially and / or coaxially mounted shaft.

The invention encompasses several types and fields of use of devices, so that the state of the art in relation to the relevance for the invention is shown in brief:
A jet engine, also called turbine air jet engine, jet engine, or jet turbine (hereinafter referred to as jet engine), is a gas turbine, which is mainly used as an aviation engine and operates on the principle of the recoil drive. The sucked air is compressed, mixed with a gaseous or liquid fuel, then ignited and burned. As a mixture of combustion products and air creates a hot gas, which emerges as a drive jet again, with thrust as a reaction force on the recoil arises (so-called turbojet engines), where in turbofan engines (turbofan engines, English: turbofan) the accelerated air of the sheath flow the main part of Engine power or the thrust generated. The jet engine removes the necessary oxidizer of the ambient air.

The jet engine is of high importance for aviation nowadays. By far the largest part of aviation transport services is provided today by jet engines: in supersonic aircraft, turbofan engines are used less frequently, but predominantly turbofan engines, which dominate commercial air traffic in particular, are used instead. The turbofan engines are designed according to the state of the art as a two-stream turbine jet engine and so called.

The gas turbine as a jet engine consists of inlet, compressor, combustion chamber, turbine and exhaust nozzle. The compressor and the turbine are mechanically connected to each other via at least one shaft. But for freewheel turbines, some of which are used in turboprops, the turbine stages driving the propeller are mechanically separated from the other components.

In turbofan engines, a fan is used upstream of the first compressor stage for the core flow. The fan ensures the generation of the sheath current, which is guided around between the actual gas turbine and the outer engine cowling and blown out to the rear. The fan (sometimes blower, fan, fan called) has, especially at a high bypass ratio of the engine, a much larger cross-section than the compressor stages. If the speed was too high, its blades would develop high centrifugal forces, which increases the mechanical load. The incoming air would also reach the blade tips supersonic speed, which reduces the efficiency. The state of the art today is that the fan usually runs on its own shaft, which is driven by the low-pressure turbine, at a significantly lower speed than the compressor. This constitutes a jet engine with more than one shaft where three waves are now known to those skilled in jet engine. Between the fan and the shaft driving it can also be arranged a reduction gear.

As a result, the blades of the fan in the multi-shaft jet engine run in an optimal speed range, which improves the efficiency of the engine, since the secondary air flow can be further slowed down, the consumption of fuel and noise emissions reduced. The lower speed reduces centrifugal forces and makes fan blading easier. The inner fan area, d. H. Regarding the air flow in the compressor section of the jet engine, which makes no contribution to the compression, separate assembly is considered. If he makes a contribution to the compression, he is regarded as the first compressor stage. The outer fan area accelerates the bypass flow and also serves the compression, the ratio for these areas depends on the constructive and constructed parameters concerning the acceleration of the sheath flow and / or the compression in the inner jet engine. The fan is usually located in front of the compressor. He may also be located behind the inner jet engine. The fan of a turbofan engine has the task to suck in and accelerate large air masses.

Behind the fan, the air flow is divided into an inner air flow (called primary flow), which enters the inner jet engine (compressor, combustion chamber, turbine, exhaust nozzle), and an outer air flow (called secondary or secondary flow), the outside of the inner Jet engine is passed.

The fan produces about 80% of the propulsion in modern commercial engines. Characteristic of a fan in the twin-stream turbine air jet engine is the bypass ratio, which is the ratio of the air flow rate of the side stream to the air flow passing through the gas turbine. Civil aircraft have a bypass ratio of 4 (80% bypass, 20% core flow) to 9 (90% bypass, 10% core flow). Secondary and primary current together cause the total thrust. In combat aircraft, the side stream share in favor of a maximum final speed is low to very low.

The air intake is followed by the compressor. Modern so-called compressors have several compressor stages, each of which may consist of several wheels with compressor blades. The purpose of the compressor is to supply kinetic energy to the incoming air mass and to convert it into pressure energy. This happens in the expanding spaces of the compressor blades. According to the law of Bernoulli, in a channel increasing in cross-sectional area, the static pressure increases while the flow rate decreases. The now lost kinetic energy is compensated in a rotor stage again. A complete compressor stage of an axially compressing compressor thus consists of a so-called rotor stage, in which both pressure and temperature as well as the speed increase, and a so-called stator stage in which the pressure increases to the detriment of the speed. The rotor stages are arranged one behind the other on a common drum, in modern engines also on up to three drums. The stator stages are permanently installed on the inside of the compressor housing. The stator blades partly also as connecting struts in the compressor or the turbine.

A turbofan engine hides the inner core flow, which carries out the thermodynamic cycle of the gas turbine. The thrust of the core engine is low in relation to the sheath flow and the core engine essentially serves as a motor for fan and sheath flow. The sheath flow also causes a reduction in the jet velocity of the expelled air-exhaust jet with the result of lower fuel consumption and lower noise emissions compared to a single jet engine of equal thrust.

Air is sucked in at the inlet of the turbofan engine. The fan accelerates in the outdoor area (sidestream) this air. In the interior (core flow) of the first large airfoil wheel, the air is compressed and thereby braked slightly. The core airflow is directed to the interior of the turbine, where the thermodynamic cycle generates the drive energy. For this purpose, the fan is first followed by a compressor, which further compresses the core stream. After the compressor comes the combustion chamber. Here fuel is injected into the compressed air and burned, which provides the energy for the drive. The increase in temperature and pressure due to combustion leads to a strong acceleration of the core flow. The core stream is passed through the exhaust gas turbine after the combustion chamber. This converts a part of the energy supplied in the combustion chamber into mechanical power, so that compressor and fan are driven (by means of a shaft leading to the front). The remaining energy (pressure, flow velocity) in the core stream is converted into thrust via the thrust nozzle located at the end of the engine.

In order to prevent the blade tips of the fan from reaching too high a speed, reduction gears or at least one, usually two to three, shafts are used in order to be able to operate the core engine and the fan at different rotational speeds. The multi-shaft system is designed by a coaxial shaft assembly, ie an outer hollow primary shaft through which the thinner secondary shaft passes.

The blading of the turbine is costly cooled from the inside or outside and consist of resistant alloys to use optimal properties of the material used for a turbine.

Behind the turbine, the exhaust nozzle is attached, through which the gas is accelerated to high speed and thus generates the thrust. The pressure difference between the turbine outlet pressure and the ambient pressure at the turbine outlet is completely converted into speed. As long as the pressure ratio of turbine outlet pressure to ambient pressure is less than a so-called critical value of about two, the pressure at the nozzle end is equal to the pressure in the environment. Engines with afterburner lead to the gas flow even before the nozzle further fuel whose combustion reduces the gas density because of the increased temperature. The exit velocity of the free jet is then greater at the same nozzle pressure ratio and thus also the thrust. Engines with afterburner need an adjustable nozzle, since the narrowest nozzle cross-section must be increased in Nachbrennerbetrieb.

Fan, compressor and turbine require a solid housing, which will withstand the centrifugal force of the demolished part in the event of a break in the blading and this does not injure the airframe or nearby persons. So that a penetration of the engine housing is prevented, it is usually with mats from z. B. aramid reinforced, which are also used for bullet-proof vests, hard hats or vehicle armor. The high temperatures in the turbine area prevent the use of aramid there.

The twin-jet jet engine (turbofan, bypass, bypass engine) is the predominant form of jet engine. It offers over a jet engine the better efficiency.

Disadvantages with respect to jet engines according to the prior art are summarized:
The high speed of the blades leaves high centrifugal forces arise, which means a high mechanical load on the blades and reach at the blade tips this supersonic speed, which reduces the efficiency of the engine. Multi-shaft designs that increase weight and complexity are necessary. The blades in the turbine and their anchoring must be consuming cooled from inside or outside and have to consist of resistant alloys. The exit velocity of the exhaust jet at the afterburner requires an adjustable nozzle, because the narrowest nozzle cross-section must be increased during afterburner operation.

The work of the rocket engine is based on the recoil principle. The difference with the jet engine is that it takes the necessary for the combustion oxidizer or the carrier of oxygen in the ambient air. The Raktentriebwerk must carry the so-called oxidizer with it. Incidentally, similar to the jet engine, an exhaust gas jet accelerated by the combustion of a combustion agent with the aid of an oxidizer accelerates a mass.

A disadvantage of the prior art engine is, in particular, that the oxidizer must be carried by the engine, which results in a high takeoff weight, for which a large part of the combustion energy must be used. Another disadvantage is that once started combustion process can not be stopped. It is also a disadvantage that an extension of the Raktetenantriebs to the utilization of the ambient air or other gas until now severely limits its applications.

A propeller is a drive by wings, which are usually positioned radially about an axial shaft. Especially in ships today is spoken by propellers, because of propellers, which is also made here. Airplanes, helicopters, ships, wind turbines and other derivatives in the field of power plant technology work on the same principle. It is variable whether the air flow power is withdrawn by the propeller or whether the air flow is to be driven. Propellers absorb the mechanical work and return this mechanical work as flow energy to the surrounding medium. The blades of a propeller are designed and positioned so that they are flowed around in rotation about an axial shaft from the surrounding aggregate, ie air, fluids so that the wings of the Among other dynamic propeller experience, which results in a rotational movement of the axial shaft, which generates thrust. A propeller can be designed as a so-called push or pull propeller.

The disadvantage of the propeller is that the tangential component of the buoyancy causes flow resistance, which requires a high torque, which the drive must deliver via the axial / coaxial shaft, and which sets the rotor radiation in rotation. Fast rotating propellers also lead to so-called cavitation on the propeller, which mechanically damages the propeller. Also, in the air and in water, vortices form on the wing tips of a propeller. These vortices are part of the performance that the propeller can not use for its intended purpose, which reduces efficiency.

Jet engines are rarely used outside aviation. Corresponding non-aviation derivatives are the gas turbine that has been redesigned to power a power generator or other work machine. The use is stationary or mobile, d. H. in power plants for power generation or on ships. Instead of a thrust nozzle, a low-pressure turbine is connected downstream, in which the exhaust gas expands and is relaxed and thus delivers the useful power via an axial shaft to the generator or the working machine. In turbofan engines, the fan is replaced by a low-pressure compressor.

A turbocharger consists of two turbines, exhaust and compressor turbines. In this case, an exhaust gas turbine in the exhaust gas flow converts the kinetic energy of the exhaust gas components which flow out of the combustion chamber after combustion into a rotational movement. This rotational movement is transmitted via a shaft axially to a second turbine, which is also attached to the axial shaft. This turbocharger compressor turbine, hereinafter referred to, sucks in outside air and compresses this outside air, which is then supplied to the internal combustion engine. The combustion of compressed air in the combustion chamber leads to an increase in the power of the internal combustion engine. However, this increase in performance usually occurs only at high engine speeds, if a sufficiently strong exhaust gas flow is present. Furthermore, the construction of the turbocharger with two turbines in a limited space requires space that could be used elsewhere. This is all the more so as the state of the art corresponding variability of the turbine geometry in the exhaust stream or other gas or fluid flow also requires space.

Starting from the prior art, it is an object of the present invention or one or more associated with it device or devices first, the above disadvantages of the prior art to alleviate, reduce or prevent or to increase the efficiency of the prior art.

The object of the present invention is, in particular, to utilize and utilize the energy present as kinetic or thermal energy in the exhaust gas flow, in the fluid, oxidizer, gas stream (which is not an exhaust gas stream) for the acceleration of a body and / or as electrical energy for further purposes To harness and use it or to make it usable and to use it for immobile devices for the production of electrical energy. It is in particular the object of the present invention or devices connected to this invention to provide a device which converts the kinetic energy of an exhaust gas stream, or of a fluid or a gas stream, in particular of an oxidizer, into electrical energy and thus increases the efficiency of an internal combustion engine and / or to provide a device that harnesses the energy inherent in the gases and fluids by converting them to electrical energy or can be used to accelerate a body.

A turbine according to the invention is a paddle wheel, a turbine wheel, a steam turbine, gas turbine, radial turbine, spiral turbine, propeller turbine or a turbine, which is located in the exhaust pipe of an internal combustion engine and propeller. Turbine in the context of the invention is also the compressor, the fan and paddle wheels, turbine wheels in jet engines, ramjet engines, combined jet and ramjet engines, rocket engines or in such stationary devices. For the purposes of the invention, it is further device for converting kinetic energy and kinetic energy into electrical energy.

The exhaust pipe connects the combustion chamber of the internal combustion engine with the outside air. The resulting in the combustion of an air-fuel mixture in the combustion chamber of the internal combustion engine exhaust gases are discharged from there to the environment. This occurs due to the pressure and temperature conditions in the combustion chamber of the engine with a high velocity of the exhaust stream and at high temperatures.

According to the invention, the exhaust gas components impinge on the turbine blades of the exhaust gas turbine and set them in motion by transmitting their kinetic energy to the exhaust gas turbine. This creates a rotational movement of the exhaust gas turbine.

According to the invention, fluids and non-exhaust gases impinge on the turbine blades of the turbine or on the propellers and set them in motion by transmitting their kinetic energy to the exhaust gas turbine / propeller, thus producing a rotational movement of the exhaust gas turbine or propeller ,

The rotational movement of the turbine blade is thus generated by the fact that the individual blades of the turbine of the kinetic energy of the exhaust / the fluid / of the outgoing pressure pushes their respective position and the individual blades on the turbine set the turbine in a rotary motion.

This object is further achieved by the features of the claims below.

It is surprising that the turbine according to the invention does not require a shaft located axially or coaxially in its center. The turbine according to the invention surprises with a concentric eccentric bearing, which is configured without transmitting a shaft positioned in its center for transmitting the rotational movement and is positioned axially relative to the exhaust gas flow. This means that the turbine produces a rotational movement in that the turbine blades, which are also eccentrically mounted in the outer edge of the turbine, the kinetic and thermal energy of the exhaust jet due to the high pressure and the high speed of the turbine eccentrically mounted in a rotating movement offset. It is surprising that the rotational movement of the eccentrically mounted turbine can be effectively enabled in the engagement body. That is, surprisingly, the exhaust pipe acts as part of this as a receiving device for the turbine.

It is surprising that the eccentrically mounted turbine, which is positioned axially relative to the exhaust gas flow, can be connected as an exhaust gas turbine with at least one turbine, which is a fan and / or with at least one turbine, which is a compressor. It is absolutely surprising to equip a jet engine solely with eccentrically mounted turbines positioned axially to the exhaust gas flow. It is also surprising that the turbine used as a fan and / or compressors are effectively stored in the engaging body so that both the rotational movement of these turbines and the effectiveness of the turbine resulting device not only maintained, but also increased can. It is also surprising that a turbine according to the invention, which is positioned fixed eccentrically in the engagement body, that is not rotatable, effectively take over or extend the tasks of a stator which is mounted axially in the prior art.

It is furthermore surprising that an axially concentric eccentrically mounted fan according to the invention positioned concentrically with the inflowing oxidizer or gas, in particular air, can be constructed with the center of the circular, ie radially oriented turbine blades and / or that such a turbofan according to the invention can be carried away from the center of the turbine Circular removal and also radially oriented turbine blades can be constructed.

It is surprising with respect to this turbofan according to the invention that a turbofan constructed with the center of the circular, ie radially aligned turbine blades can be connected to at least one further turbofan by suitable over or reduction gears or by rigid connection, such that on one outside the outer edge of the turbine first fans according to the invention concentrically at least one further fan according to the invention, which is constructed with its edge and the fictitious center of the turbine radially removing turbine blades, can be connected.

It is also surprising with respect to this turbofan according to the invention that it can be connected to at least one compressor which is axially aligned with the inflow of the incoming oxidizer or gas and concentrically eccentrically mounted. It is surprising that in one embodiment of the turbine according to the invention the compressor can also be constructed with turbine blades aligned radially to the center and / or with turbine blades radially remote from the center. Again, it is surprising that the fan according to the invention as well as the compressor according to the invention can be effectively stored in the engaging body and / or by gears that are positioned on the outer edge of this fan and compressor or by waves that are positioned on the outer edge of this fan and compressor , get connected.

It is surprising that an exhaust gas turbine according to the invention, a fan according to the invention or a compressor according to the invention in combination with a stator mounted axially to the inflowing oxidizer or gas and concentrically eccentric or centered according to the invention, wherein the marked stator between several or before or after at least one inventive compressor can be positioned.

Surprisingly, in particular, that the aforementioned embodiments of the turbine, which is aligned axially to the exhaust flow, not only eccentrically constructed and stored at its outer edge in the two-dimensional basic shape of a concentric circular can be performed, but also eccentrically constructed and stored in the basic form of a concentric ellipse or a corresponding eccentrically constructed and stored arbitrary oval or a correspondingly eccentrically constructed and mounted convex connecting link can be performed. Because of this, it is surprising that an embodiment of the turbine with turbine blades aligned radially to the center of the turbine can also perform the aforementioned basic shapes in their construction. Therefore, it is also surprising that a further embodiment of the turbine also with the turbine blades radially removing from the center of the turbine also the aforementioned basic shapes can be executed respecting their construction. The design of the bearing of the turbine and turbine blades according to the invention required for this purpose is surprising.

It is surprising that the turbine blades oriented toward the center are positioned in an exhaust stream, gas stream or fluid stream flowing through a pipe, the turbine blades outwardly away from the center separate from the exhaust, gas or water stream of the interior Pipe can be suspended. As a result, the outer turbine part can convert or redirect thermal or kinetic energy of the exhaust gas, gas or fluid flow flowing in the inner tube and thus surprisingly increase the efficiency of the devices connected to it.

It is surprising that at least one of the named embodiments of the turbine and the associated embodiments of the turbine blades according to the invention in a further advantageous embodiment with at least one axially or coaxially mounted exhaust gas turbine, at least one axially or coaxially mounted turbofan, with at least one of an axial or Coaxially mounted compressor, with no or at least one of an axially or coaxially mounted stator and at least one exhaust pipe combined can be constructed. This initially makes it possible to significantly increase the thrust of a device which is additionally constructed with the turbines according to the invention, and thus to significantly increase the efficiency of such a device or not only to slightly reduce the consumption of combustion materials. Here, depending on the intended use of a device constructed like a dartig, there is an increase in the transport capacity and a more specialized construction of this device.

Also, a rocket engine emits a high pressure, high velocity exhaust stream in response to the principle of recoil to provide thrust to achieve the escape velocity necessary for leaving Earth or orbit planet orbit. It is surprising that at least one inventive fan, directly or by means of an over / under substitution connected to an exhaust gas turbine according to the invention, which is positioned in the exhaust gas jet of the rocket drive, further thrust is able to produce. A fan designed in accordance with the invention with turbine blades that radially separate from the center can also be connected to a rocket engine in a further embodiment. As a result, the structural disadvantage inherent in rocket propulsion can be mitigated or the unused kinetic and thermal energy of the exhaust jet of the rocket engine can be used to provide thrust. In this context, it is surprising that here too the turbines used according to the invention are not bound to the basic shape of a circular circumference, but here too the basic shape can be an ellipse or an arbitrary oval or a convex connecting path.

A combination of the previously described embodiments of the turbines, insofar as they are contained in particular in a jet and / or ramjet engine based thereon, with a rocket engine can be surprisingly implemented by the invention.

A propeller, which according to its principle also generates a rotational movement due to a gas or fluid flowing in or accelerated by it, can surprisingly be constructed according to the same principle of the turbine according to the invention. In particular, it is surprising for a propeller according to the invention that at least one airfoil, which is positioned axially to the influx of gas or fluid, surprisingly either in its basic form concentrically on a circular or ellipse or any oval or a convex connecting link build up and Accordingly, according to the invention can be mounted eccentrically. It is furthermore surprising that an embodiment of the exhaust gas turbine according to the invention can be connected to a propeller, in accordance with the invention or in a classical design. In particular, given in non-inventive propellers disadvantages of cavitation or vortex formation at the wing tips can be reduced or prevented by the embodiments of the invention or the efficiency of propellers in gases or fluids can be increased.

It is surprising that in a further advantageous embodiment of the turbines according to the invention, an exhaust gas turbocharger is constructible, the exhaust and compressor turbine follows the structural design of the turbine according to the invention, so this takes over. Surprisingly, furthermore, in the context of the fact that this further embodiment of the turbine according to the invention can be connected with axially mounted exhaust gas and / or compressor turbines can be connected. In particular, it is surprising that also for this embodiment of the eccentrically mounted turbine (s) according to the invention, these can be designed concentrically on a circular or concentric on an ellipse or concentrically on another convex connecting path.

For the aforementioned embodiments of the invention, it is preferred that the claimed device be operated in the internal combustion engine of a consumer, wherein as a consumer cars, trucks, buses, agricultural tractors, hybrid vehicles, fuel cell vehicles, ships, submarines, aircraft, helicopters, Escape speed vehicles, in particular missiles , Power plants, wind power plants, wind turbines or water jet drives come into consideration. There are also consumers as all vehicle and machine types in question, which have a high-velocity exhaust gas flow, the energy remains unused and therefore discharged as waste heat and kinetic energy of the exhaust stream to the environment and so the consumer is no longer available , There are also consumers as all vehicle or machine types in question, which have an influx of oxidizers, gases or high speed and as waste heat and kinetic energy but the influx of oxidizers, gases or give to the environment or on the invention respectively. It was completely surprising that the device according to the invention can serve to improve the efficiency in all these consumers.

The above object is further achieved by the features of the claims below and the following claims:
Electrical energy is usually converted by the connection of an axial or coaxial exhaust gas turbine, which can generate electrical current through a rotatable first shaft with a dynamo, from the kinetic energy of the exhaust gas flow.

The efficiency of a kinetic energy to electrical energy conversion device is between 0 to 1, with larger values representing a greater measure of converted energy and smaller ones to a lesser extent. This object is further achieved by the features of the claims below.

This object is further achieved by the features of the claims below.

According to the invention a device for recovering electrical energy from an exhaust gas stream of an internal combustion engine is proposed, comprising at least one exhaust pipe, an eccentrically mounted exhaust gas turbine, a rotatable first shaft and a dynamo and is characterized in that the exhaust gas turbine is present in the exhaust stream, the exhaust gas flow through at least one exhaust pipe is discharged from a combustion chamber of the internal combustion engine to the outside air or the environment and the exhaust gas turbine, whose blades in the eccentric bearing, d. H. are fixed on a concentric, elliptical or convex connecting path, and at this connecting section by a shaft, a transmission is connected to the dynamo. Rotary movements and torques, ie forces, are thus transferred from the exhaust gas turbine to the dynamo. The junction between each of a turbine and a shaft is referred to as the end face of the eccentrically mounted exhaust gas turbine. At this junction between turbine and shaft, the motion and associated kinetic energy is transferred between the components. In addition, the exhaust gas turbine and the dynamo, inter alia, at this junction, so the front of the exhaust gas turbine, stored.

A dynamo within the meaning of the invention is a device with which kinetic energy, in this case the rotational movement, is converted into electrical energy by means of the principle of electromagnetic induction. Due to the rotational movement of the exhaust gas turbine, the rotatable first shaft or the transmission is set in motion and transmits the rotational movement to the dynamo. Preferably, this is outside the exhaust stream.

Unlike an exhaust gas turbine known in the prior art, the invention or device according to the invention does not consist of axially or coaxially mounted turbines, exhaust and compressor turbine, but of eccentrically mounted exhaust gas turbines, which identify a circular, elliptical or otherwise convex connecting path in its two-dimensional basic form and the dynamo.

Thus, it can not come to the problem described in the prior art when using the device that at low pressure engine oil is sucked from the camp of the compressor turbine and enters the combustion chamber of the engine. In particular, the efficiency of the combustion material used increases by the addition of combustion additional and subsequent conversion into electrical energy.

In a further embodiment of the invention, it may also be preferred that the vehicle has more than one exhaust pipe or the at least one exhaust pipe is provided with a bypass line to pass over parts of the current to the device according to the invention and with further A bypass line of an exhaust pipe is in the context of this invention, a pipe which is guided along a defined portion of the exhaust pipe parallel to this and is connected to the exhaust pipe, that a portion of the exhaust gas flow through the bypass Line can be redirected. The bypass line starts and ends in the exhaust pipe.

The eccentrically mounted exhaust gas turbine present at least once in the exhaust gas flow is thereby positioned axially relative to the exhaust gas flow in at least one exhaust gas pipe or selected or all exhaust gas pipes. It was completely surprising that although this results in a minimal braking effect on the exhaust gas flow, but the eccentrically mounted exhaust gas turbine can avoid a backflow of the exhaust gas flow. Moreover, it was completely surprising that it is possible to remove rotatable first and further axial or coaxial shafts from the exhaust gas flow and thus to greatly increase the efficiency of the exhaust gas turbine and associated devices as well as devices based thereon. Thus, the invention can be surprisingly completely flexible adapted to the structural conditions within an internal combustion engine or a mobile or immobile object. It may also be preferred that a device according to the invention is arranged in the bypass line, which further increases the versatility of the device according to the invention.

It is preferred in a further embodiment of the invention that the claimed device is operated in the internal combustion engine of a consumer, as consumer cars, trucks, buses, agricultural tractors, hybrid vehicles, fuel cell vehicles, ships, submarines, aircraft, helicopters, Escape speed vehicles in particular Rockets, power plants, wind power plants, wind turbines or water jet drives are conceivable. There are also consumers as all vehicle and machine types in question, which have a high-velocity exhaust gas flow, the energy remains unused and therefore discharged as waste heat and kinetic energy of the exhaust stream to the environment and so the consumer is no longer available , There are also consumers as all vehicle or machine types in question, which have an influx of oxidizers, gases or high speed and as waste heat and kinetic energy but the influx of oxidizers, gases or give to the environment or on the invention respectively. It was completely surprising that the device according to the invention can serve to improve the efficiency in all these consumers.

A consumer according to the invention has, in a preferred embodiment, an electrical power supply system and / or an electric motor and / or in a preferred embodiment of the invention also a battery via which most vehicles have energy storage and buffers to compensate for different voltages. It was completely surprising that the device according to the invention can be used in all consumers, the technology-related, in addition to a combustion and an electric motor, have an accumulator for storing electrical energy. It was completely surprising that the device according to the invention can also be used in all consumers who technologically have an electric motor and / or dynamo and / or an accumulator for storing electrical energy and the device that drives the electric motor / dynamo from on the invention inflowing oxidizers, gases is set in a rotary motion.

It may also be preferred that the consumer comprises an electric motor in addition to an electrical energy supply system. An electric motor converts electrical energy into a movement, ie kinetic energy. He thus represents an ideal customer for the electrical energy generated by the device according to the invention. It was completely surprising that the electric motor in his energy Case of using a device according to the invention not only from the accumulator can, but also partially from the electrical energy, which is obtained by means of the claimed device from the exhaust stream of the engine or the influx of the oxidizer, gases.

If a consumer, in which the claimed device is operated, has no accumulator due to the technology, a further preferred embodiment of the invention consists in that the device according to the invention itself comprises an accumulator. This can advantageously be used to store excess electrical energy and to return it at a later date and when needed. The use of a rechargeable battery ensures a continuous supply of electrical energy. It was completely surprising that the accumulator can also act as a buffer in conjunction with other components relating to the energy supply of the consumer.

The accumulator is connected via means for power line to the dynamo of the device according to the invention and can receive the generated electrical energy of the dynamo. However, it may also be preferred that the dynamo deliver the electrical energy directly to the consumer, or his energy supply system and / or an optionally existing electric motor. Thus, surprisingly, an optimization of the supply of the consumer with electrical energy can be achieved.

The accumulator is also connected via means for power line to the power supply system and / or an electric motor of the consumer and can feed electrical energy into the energy supply system and / or provide an electric motor of the consumer with electrical energy. It was completely surprising that the use of the electrical energy generated by the dynamo of the device according to the invention depends on how much electrical energy is available to the consumer and how great his current need is.

Since the electrical energy provided by the device according to the invention represents an additional possibility for generating energy in a consumer, the disadvantage of an axially or coaxially mounted exhaust gas turbine, which develops its effect only at sufficiently high rotational speeds, is known to the device according to the invention Not relevant.

Unlike in the case of the introduction of compressed air into the combustion chamber of the internal combustion engine by means of an axially or coaxially mounted exhaust gas turbine, the strict continuity of the process in generating the additional electrical energy is not absolutely necessary in one or more embodiments of the invention, since surprisingly the interaction of the alternator , local generators and device according to the invention ensures the supply of all electrical equipment in the consumer.

In a further preferred embodiment, the invention includes a transmission to reduce the number of rotations per unit time in transmitting the rotational motion from the first shaft to the dynamo. Exhaust gas turbines in an exhaust gas flow can reach speeds of up to 300,000 revolutions per minute. This can also apply with appropriate design for the present invention. Since these are transferred to the rotatable first shaft and then on to the dynamo and dynamos usually work in smaller speed ranges between 50 and 3000 revolutions per minute, it may be preferable between the exhaust gas turbine according to the invention and / or on the first rotatable shaft on the outer edge of the exhaust gas turbine and the dynamo to provide a transmission which translates the higher speeds of the exhaust gas turbine so that the dynamo can operate in the optimum speed range. The use of a transmission thus surprisingly increases the range of action of the usable rotational speeds of the exhaust gas turbine according to the invention and the performance of the dynamo according to the invention and its service life.

The device according to the invention is advantageously operated in an internal combustion engine in which there is an accelerated exhaust gas flow. In this case, the device according to the invention can surprisingly be used in a large variety of engines. For example, it may be a gasoline engine, a diesel engine, a Wankel engine, an HCCi engine, a turboprop engine, a hybrid engine, or a Stirling engine. In a further preferred embodiment, the inventive device and the internal combustion engine in a jet engine, a single or twin jet engine, a ramjet, a Ramjet jet engine, a Scramjet jet engine, clock engine, a combination of a jet and ramjet, a jet engine or used a gas and / or coal power plant.

The effect of an exhaust gas turbine as a turbocharger described in the prior art consists in an increase in the power of the internal combustion engine. This is disadvantageously associated with high thermal and mechanical loads on the entire motor material. The effect of the device according to the invention, however, lies in the increase of the efficiency of the internal combustion engine. Surprisingly, complicated material adjustments and the use of additional cooling devices could be avoided.

Particularly preferred is the use of the device according to the invention in hybrid vehicles. Hybrid vehicles, according to a UN definition, include at least two energy converters and two energy storage systems. In this case, diesel, petrol or electric motor energy converters and accumulators, gas or fuel tanks energy storage systems. Surprisingly, the performance of hybrid engines in particular has been improved by the better utilization of the chemical energy stored in a fuel through the use of the device according to the invention.

In a further preferred embodiment, the device according to the invention comprises an electric motor, which converts the electrical energy that is generated by the dynamo according to the invention again into kinetic energy and can drive different waves with this kinetic energy. In a preferred embodiment, the electric motor thereby drives a shaft which is connected to a compressor according to the invention of a jet engine, a single-jet or two-jet engine, a ramjet engine, a combined jet and ramjet engine. According to the invention, a compressor is here, which is surprisingly characterized in that it is mounted eccentrically and not axially or coaxial and centered. It was completely surprising that the electric motor in this way can support the drive of a compressor according to the prior art but also the compressor according to the invention. Surprisingly, by the use of the electric motor, the performance of the internal combustion engine can be increased by means of the drive of the compressor.

In a preferred embodiment, the electric motor thereby drives a shaft which is connected to a propeller according to the invention. An inventive propeller surprises by its eccentric bearing, which is the opposite of the axial or coaxial and centered bearing. It was completely surprising that the electric motor can support the drive of the propeller according to the prior art or the propeller according to the invention in this way. Surprisingly, the efficiency of the propeller can be increased by the use of the electric motor.

It may also be preferred that the electric motor drives a shaft which is connected to a fan according to the invention. For the purposes of this invention, a fan is a gas turbine having a larger cross-section than a compressor. According to the invention, a fan which is surprisingly mounted eccentrically and in particular is not mounted axially or coaxially.

The blades according to the invention of an exhaust gas turbine, a compressor or a fan develop due to the large cross-section of the turbine large centrifugal forces. The tips of the blades of the exhaust turbine, the compressor or the fan can sometimes reach supersonic speed.

The blades according to the invention of an exhaust gas turbine, a compressor or a fan are fixed in a preferred embodiment of the device according to the invention on the outer edge of the / each eccentrically mounted exhaust gas turbine, compressor or fan. They are not fixed axially or coaxially on a central shaft in the embodiment according to the invention. As a result, the exhaust gas turbine, the compressor or the fan is on its own, relatively slowly rotating rotational movement. The fan according to the invention can be operated at a different speed, as well as the compressor according to the invention. The speed of the fan according to the invention is preferably lower than the speed of the compressor according to the invention.

It may be mounted in a further preferred embodiment, a transmission between the invention fan and the shaft driving it. It was completely surprising that this allows the operation of the fan in an optimal speed range can be guaranteed. This improves the efficiency of the fan according to the invention. This reduces fuel consumption of the internal combustion engine and reduces noise emissions of the device according to the invention.

Surprisingly, the operation of the fan or compressor according to the invention and the exhaust gas turbine according to the invention, the radial forces acting on the fan blades are reduced by the lower rotational speed.

Surprisingly, it is therefore possible to make the blades according to the invention of the fan or compressor according to the invention and the exhaust gas turbine according to the invention more compact or more stable and / or lighter. Thus, it may also be preferred to manufacture the blades of the fan according to the invention from a lighter and / or more economically effective material and thus to reduce the weight of the vehicle or the device in which it is used and the production costs. This also affects the energy consumption.

It may also be preferred that both the shaft, which is connected to the compressor according to the invention, and the shaft, which is connected to the fan according to the invention, jointly driven by the electric motor. It was completely surprising that thereby the thrust of the combustion engine according to the invention and the compressor according to the invention can be increased. This increase in thrust, in particular travel times can be shortened when the device according to the invention is used in an aircraft. In addition, the use of the device according to the invention surprisingly increases the power yield of the fuel with the same consumption or reduces the consumption of fuel.

The invention further relates to the use of the device according to the invention and its preferred embodiments. Moreover, the invention relates to a method for obtaining electrical energy from the exhaust gas stream of an internal combustion engine. In this case, this method preferably comprises the removal of kinetic energy from an exhaust gas flow through an exhaust gas turbine according to the invention, the conversion of this kinetic energy into a rotational movement through the exhaust gas turbine according to the invention and the transmission of the rotational movement of the inventive exhaust gas turbine on a rotatable first shaft. Specifically, this happens because the components of the exhaust gas stream impinge at high speed on the eccentrically mounted turbine blades or blades of the exhaust gas turbine according to the invention and set them in motion. Surprisingly, a rotational movement of the exhaust gas turbine can be generated from the straight-line movement of the exhaust gas flow within the exhaust pipe in this way, which can then be used to obtain electrical energy by the dynamo according to the invention. Surprisingly, an inventive fan connected to the exhaust gas turbine according to the invention accelerates gas, which in turn drives an eccentrically mounted turbine, which generates the method of obtaining electrical energy from the gas flow of the fan. This saves resources and lowers production costs.

In a further preferred method, an inventive eccentrically mounted turbocharger present in the consumer is used for the preferred method steps. It was completely surprising to use a turbocharger according to the invention for the inventive method. This saves resources and lowers production costs.

In a further preferred method, the rotational movement of the first shaft bearing against the exhaust gas turbine according to the invention or the fan according to the invention is transmitted to a dynamo. It may be preferred that between the rotatable first shaft and the dynamo, a transmission is interposed. The task of the transmission is to translate the high speeds, the exhaust gas turbines, due to the high speeds in the exhaust stream, often, translate into an acceptable range for the dynamo. By means of the dynamo, the rotational movement, which is transmitted via the rotatable first shaft and possibly by means of the transmission to him, converted into electrical energy. In this case, the dynamo applies the principle of electromagnetic induction, in which a current-carrying conductor moves in a magnetic field and in which a voltage is induced by the Lorentz force.

The invention further relates to a method in which the electrical energy generated is passed on directly to an existing consumer power supply system. It may also be preferred that an electric motor or another device operated with electrical energy is operated in the vehicle with the electrical energy. Furthermore, it may be preferable for the electrical energy generated in the dynamo to be stored in an accumulator and only later to be passed on to the energy supply system or electric motor. It was completely surprising that this preferred embodiment of the method allows a high deployment flexibility of the method according to the invention, since it can be responded to the circumstances in the vehicle and the current energy needs of the consumer.

Further advantageous measures are described in the remaining subclaims. The invention will be described in more detail with reference to embodiments and the following figures. LIST OF REFERENCE NUMBERS 1 Second casing pipe 2 (Storage of the turbines) between 3 Influx of gas or fluid 4 from the center (removing) 5 to the center (aligned) 6 radial 7 concentric storage 8th eccentric storage 9 positioned axially 10 exhaust turbine 11 fan 12 compressor 13 stator 14 dynamo 15 exhaust gas flow 16 exhaust pipe 17 rotatable, first shaft 19 internal combustion engine 20 combustion chamber 21 circle round 22 turbine blade 23 ellipse 24 any oval 25 convex link 26 (Exhaust) turbine on axial or coaxial rotatable shaft 27 Fan on axial or coaxial rotatable shaft 28 Compressor on axial or coaxial rotatable shaft 29 compressor pipe 30 first jacket pipe 31 rigid connection 32 airfoil 33 (Compressor) turbine 34 propeller 35 Influx of oxidizers, gas, fluids 36 Device around longitudinal axis rotatable turbine blade 37 rotatable, second and / or each other wave 38 ducted 39 exhaust nozzle 40 intake 41 turbine 42 gas flow

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• AT 000000221318 B [0001]
• CH 000000508809 A [0001]
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• CH 000000322020 A [0001]
• DE 602004001691 T2 [0001]
• DE 202013001098 U1 [0001]
• DE 000069301008 T2 [0001]
• DE 000019538769 A1 [0001]
• DE 000003014518 A1 [0001]
• DE 000003490164 T5 [0001]
• DE 202011102001 [0001]
• DE 102011007386 A1 [0001]

Claims (37)

Device for generating kinetic as well as electrical energy from a gas stream consisting of at least one compressor tube and / or at least one exhaust pipe, consisting of at least one concentrically eccentric axially positioned and mounted in the gas turbine turbine, characterized in that at least one concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) positioned and mounted turbine ( 41 ) axially ( 9 ) in the gas stream ( 42 ) and the gas stream ( 42 ) by at least one exhaust pipe ( 16 ) and / or compressor tube ( 29 ) is characterized in that the axial ( 9 ) in the gas stream ( 42 ) positioned and mounted turbine ( 41 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of a circle round ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) of the turbine ( 41 ) and characterized in that at least one axial ( 9 ) in the gas stream ( 42 ) positioned and mounted turbine ( 41 ) with radial ( 6 ) to the center ( 5 ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the turbine ( 41 ) is connected by a rotatable, first shaft ( 17 ) or second or further rotatable shaft ( 37 ) or a transfer or reduction device or a rigid ( 31 ) Compound characterized in that these turbines ( 41 ) by a rotatable first shaft ( 17 ) or by a second or further rotatable shaft ( 37 ) or by transfer or reduction device or rigid ( 31 ) Connection with at least one further aforementioned turbine ( 41 ), characterized in that one, several or all turbines ( 41 ) between ( 2 ) Exhaust pipe ( 16 ) and compressor tube ( 29 ) are stored. Apparatus according to claim 1, comprising a compressor tube, an exhaust pipe, at least one jacket tube, at least one concentrically eccentrically mounted exhaust gas turbine, at least one concentrically eccentrically mounted fan, at least one concentrically eccentrically mounted compressor, a stator and at least one combustion chamber, an internal combustion engine and at least a thrust nozzle, characterized in that at least one concentric ( 7 ) eccentric ( 8th ) positioned and mounted exhaust gas turbine ( 10 ) axially ( 9 ) in the exhaust stream ( 15 ) and the exhaust gas flow ( 15 ) through an exhaust pipe ( 16 ) from at least one combustion chamber ( 20 ) together with exhaust nozzle ( 39 ) of the internal combustion engine ( 19 ) is discharged to the outside air, characterized in that the axial ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) in circular ( 21 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the exhaust gas turbine ( 10 ) in circular ( 21 ) and / or characterized in that at least one axial ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the exhaust gas turbine ( 15 ) are connected by a rotatable, first shaft ( 17 ) or transfer or reduction device or rigid connection ( 31 ) with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of the circular ( 21 ) is connected to remotely oriented turbine blades and / or characterized in that the axial ( 9 ) in the influx ( 35 ) positioned and stored fan ( 11 ) is connected to at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored fan ( 11 ) on a circular ( 21 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ) and / or characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) rigidly ( 31 ) is connected to at least one in the concentric ( 7 ) Circular ( 21 ) eccentric ( 8th ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the fan ( 11 ) in circular ( 21 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the fan ( 11 ) are connected by a rotatable, first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of the circular ( 21 ) is associated with remotely oriented turbine blades and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) and / or at least one axial ( 9 ) in the exhaust stream ( 15 ) positioned exhaust gas turbine ( 10 ) with at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) mounted compressor ( 12 ) is characterized in that the fan ( 11 ) and / or the compressor ( 12 ) and / or the exhaust gas turbine ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) is characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored compressors ( 12 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) in circular ( 21 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the compressor ( 12 ) in circular ( 21 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored compressor ( 12 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ), the rigid ( 31 ) on the compressor ( 12 ) are supported by a rotatable first shaft ( 17 ) or transfer or reduction device or rigid connection ( 31 ) with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of the circular ( 21 ) is associated with remotely oriented turbine blades and / or characterized in that at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) Stored stator ( 13 ) behind, between or in front of the compressor ( 12 ) is positioned and stored or a stator ( 13 ) characterized in that one, several or all fans ( 11 ) and / or the one, several or all exhaust gas turbines ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) are stored. Device according to at least one above-mentioned claim, characterized in that the device consists of a compressor tube, an exhaust pipe, at least one jacket tube, at least one concentrically eccentrically mounted exhaust gas turbine, at least one concentrically eccentrically mounted fan, from at least one concentrically eccentrically mounted compressor, from a stator and at least one combustion chamber and at least one exhaust nozzle, characterized in that at least one concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted exhaust gas turbine ( 10 ) axially ( 9 ) in the exhaust stream ( 15 ) and the exhaust gas flow ( 15 ) by at least one exhaust pipe ( 16 ) from at least one combustion chamber ( 20 ) together with exhaust nozzle ( 39 ) of the internal combustion engine ( 19 ) is discharged to the outside air, characterized in that the axial ( 9 ) in the exhaust gas flow ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) of the exhaust gas turbine ( 10 ) and / or characterized in that at least one axial ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) with radial ( 6 ) to the center ( 5 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the exhaust gas turbine ( 11 ) is connected by a rotatable, first shaft ( 17 ) or a transfer or reduction device or a rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) with at least one of the centers ( 4 ) remotely oriented turbine blade ( 22 ) and / or characterized in that the axial ( 9 ) axially ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) is connected to at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) and on a concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) axially ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ) and / or characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the fan ( 11 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with at least one radial ( 6 ) to the center ( 5 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blade ( 22 ), the rigid ( 31 ) with the fan ( 11 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) remotely oriented turbine blades ( 22 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) and / or at least one axial ( 9 ) to the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) with at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) positioned and stored compressors ( 12 ) concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) and / or the axial ( 9 ) to the influx ( 35 ) positioned and stored compressors ( 12 ) and / or the axial ( 9 ) in the exhaust stream ( 15 ) positioned and decelerated exhaust gas turbine ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) is characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored compressors ( 12 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the compressor ( 12 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored compressor ( 12 ) with radial ( 6 ) to the center ( 5 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the compressor ( 12 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored compressor ( 12 ) with the center ( 4 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is associated with remotely oriented turbine blades and / or characterized in that at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) positioned and supported stator ( 13 ) behind, between or in front of the compressor ( 12 ) is positioned and stored or a stator ( 13 ) characterized in that one, several or all fans ( 11 ) and / or the one, several or all exhaust gas turbines ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) are stored. Device according to at least one above-mentioned claim, characterized in that the device consists of at least one axially or coaxially on a rotatable first shaft ( 17 ) mounted exhaust gas turbine in the exhaust stream and / or at least one axially or coaxially on a rotatable first shaft ( 17 ) mounted fan, at least one axially or coaxially on a rotatable first shaft ( 17 ) mounted compressor, a stator, at least one exhaust pipe and a thrust nozzle connected to at least one eccentrically mounted exhaust gas turbine, at least one eccentrically mounted fan and at least one eccentrically mounted compressor characterized in that the axially or coaxially on a rotatable first shaft ( 17 ) stored exhaust gas turbine ( 26 ) axially ( 9 ) in the exhaust stream ( 15 ) is present characterized in that in front of or behind this turbine ( 26 ) a concentric ( 7 ) eccentric ( 8th ) axially ( 9 ) to the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) and the exhaust gas flow ( 15 ) by at least one Exhaust pipe ( 16 ) from a combustion chamber ( 20 ) together with exhaust nozzle ( 39 ) of the internal combustion engine ( 19 ) is discharged to the outside air, characterized in that the axial ( 9 ) to the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) with the center ( 4 ) of the exhaust gas turbine ( 10 ) of a circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) and / or characterized in that at least one axial ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) with radial ( 6 ) to the center ( 5 ) on a Keisrund ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the exhaust gas turbine ( 10 ) are connected by a rotatable, first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of the circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is connected to removing turbine blades and / or characterized in that the axially or coaxially mounted on a rotatable shaft fan ( 27 ) axially ( 9 ) in the influx ( 35 ) characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) is connected to at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) and on a concentric ( 7 ) Circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) eccentric ( 8th ) axially ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the fan ( 11 ) are connected by a rotatable, first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of the circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) remotely oriented turbine blades ( 22 ) and / or characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) and / or the axial ( 9 ) to the influx ( 35 ) positioned and stored compressors ( 12 ) and / or the axial ( 9 ) to the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) is characterized in that the axially or coaxially on a rotatable first shaft ( 17 ) mounted compressors ( 28 ) axially ( 9 ) in the influx ( 35 ) characterized in that at least one axially ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) and / or at least one axial ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) axially ( 9 ) with at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted compressor ( 12 ) is characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored compressors ( 12 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the compressor ( 12 ) of the circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored compressor ( 12 ) with radial ( 6 ) to the center ( 5 ) on a circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) with the compressor ( 12 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored compressors ( 12 ) with the center ( 4 ) of a circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is associated with remotely oriented turbine blades and / or characterized in that at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) Stored stator ( 13 ) behind, between or in front of the compressor ( 12 ) is positioned and stored. characterized in that one, several or all fans ( 11 ) and / or the one, several or all exhaust gas turbines ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) are stored. Device according to at least one of the preceding claims, characterized in that at least one concentric ( 7 ) eccentric ( 8th ) positioned and mounted exhaust gas turbine ( 10 ) axially ( 9 ) in the exhaust stream ( 15 ) and the exhaust gas flow ( 15 ) through an exhaust pipe ( 16 ) from at least one combustion chamber ( 20 ) together with exhaust nozzle ( 39 ) of the internal combustion engine ( 19 ) is discharged to the outside air, characterized in that at least one in its previously claimed embodiments according to the invention axially ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) behind the combustion chamber ( 20 ) together with exhaust nozzle ( 39 ) of the internal combustion engine ( 19 ) is characterized in that the axial (in accordance with one or more or all or 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Compound is connected to at least one exhaust gas turbine according to the invention which is present in one or more or all or all of the previously illustrated embodiments ( 10 ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is characterized in that the axial ( 9 ) in the exhaust gas flow ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) of the exhaust gas turbine ( 10 ) and / or characterized in that at least one axial ( 9 ) in the exhaust stream ( 15 ) positioned and mounted exhaust gas turbine ( 10 ) with radial ( 6 ) to the center ( 5 ) on a circle or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blades ( 22 ), the rigid ( 31 ) are connected to the exhaust gas turbine, is connected by a rotatable, first shaft ( 17 ) or a transfer or reduction device or a rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) on a circular or ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) with at least one of the centers ( 4 ) remotely oriented turbine blade ( 22 ) and / or characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) is connected to at least one axial ( 9 ) to the incoming oxidizer and / or gas ( 35 ) and on a concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) axially ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blades ( 22 ) and / or characterized in that the axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) rigidly ( 31 ) is connected to at least one concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) away from the center ( 4 ) of the fan ( 11 ) and / or characterized in that at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with at least one radial ( 6 ) to the center ( 5 ) on a circular ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) oriented turbine blade ( 22 ) by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored fan ( 11 ) with the center ( 4 ) of a circle round ( 21 ) or an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) remotely oriented turbine blades ( 22 ) is characterized in that the concentric ( 7 ) eccentric ( 8th ) positioned and stored fan ( 11 ) axially ( 9 ) in the influx ( 35 ) and the influx ( 15 ) by at least one jacket tube ( 30 ) to the fan ( 11 ), characterized in that the one, several or all fans ( 11 ) and / or the one, several or all exhaust gas turbines ( 10 ) between ( 2 ) Exhaust pipe ( 16 ) and jacket tube ( 30 ) are stored. characterized in that it is connected to a rocket engine. Apparatus according to claim 1 for compressing the oxidizer or gas ( 3 ) using the exhaust stream ( 15 ) of an internal combustion engine ( 19 ), comprising an intake pipe ( 40 ), a compressor tube ( 29 ), at least one compressor turbine ( 33 ) according to one or more or all of the previously claimed embodiments of an exhaust gas turbine ( 10 ), an exhaust pipe ( 16 ), which the exhaust gas flow ( 15 ) discharged to the outside air, characterized in that the compressor turbine ( 33 ) axially ( 9 ) to the exhaust stream ( 15 ) and the exhaust gas flow ( 15 ) by at least one exhaust pipe ( 16 ) from a combustion chamber ( 20 ) of the internal combustion engine ( 19 ) is discharged to the outside air, characterized in that the compressor turbine ( 33 ), which according to one or more or all of the previously claimed embodiments of an exhaust gas turbine ( 10 ) is constructed by at least one intake pipe ( 40 ) Draws in ambient air and over the compressor tube ( 29 ) into the combustion chamber ( 20 ) of the internal combustion engine ( 19 ) is characterized in that at least one axial ( 9 ) in the exhaust stream ( 35 ) positioned and stored compressor turbine ( 33 ), constructed as in the aforementioned embodiments claimed exhaust gas turbine ( 10 ), radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) is characterized in that at least one axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) on a circular ( 21 ) is connected to radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) aligned airfoils ( 32 ) and / or characterized in that the axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) on a circular ( 21 ) rigidly ( 31 ) is connected to at least one radial ( 6 ) in concentric ( 7 ) eccentric ( 8th ) Circular ( 21 ) mounted turbine blade ( 22 ), which are radially ( 6 ) from the center ( 4 ) of the compressor turbine ( 34 ) in a circle ( 21 ) and / or characterized in that at least one axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) on a circular ( 21 ) with at least one radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) oriented turbine blade ( 22 ), the rigid ( 31 ) with the compressor turbine ( 34 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) and stored compressor turbine ( 33 ) on a circular ( 21 ) with the center ( 4 ) of the circular ( 21 ) remotely oriented turbine blades ( 22 ), characterized in that the concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) axially ( 9 ) in the exhaust stream ( 15 ) concentric ( 7 ) eccentric ( 8th ) is positioned and stored and the influx ( 35 ) by at least one intake pipe ( 40 ) to the compressor turbine ( 33 ), characterized in that the one, several or all compressor turbines ( 33 ) in at least one exhaust pipe ( 16 ) are stored. Apparatus according to claims 1 and 6 for compressing the oxidizer or gas ( 3 ) using the exhaust stream ( 15 ) of an internal combustion engine ( 19 ), comprising an intake pipe ( 40 ), a compressor tube ( 29 ), at least one compressor turbine ( 33 ) according to one or more or all of the previously claimed embodiments of an exhaust gas turbine ( 10 ), an exhaust pipe ( 16 ), which the exhaust gas flow ( 15 ) discharged to the outside air, characterized in that the compressor turbine ( 33 ) axially ( 9 ) to the exhaust stream ( 15 ) and the exhaust gas flow ( 15 ) by at least one exhaust pipe ( 16 ) from a combustion chamber ( 20 ) of the internal combustion engine ( 19 ) is discharged to the outside air, characterized in that the compressor turbine ( 33 ), which according to one or more or all of the previously claimed embodiments of an exhaust gas turbine ( 10 ) is constructed by at least one intake pipe ( 40 ) Draws in ambient air and over the compressor tube ( 29 ) into the combustion chamber ( 20 ) of the internal combustion engine ( 19 ) is characterized in that at least one axial ( 9 ) in the exhaust stream ( 35 ) positioned and stored compressor turbine ( 33 ), constructed as in the aforementioned embodiments claimed exhaust gas turbine ( 10 ), radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is characterized in that at least one axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is connected to radial ( 6 ) to the center ( 5 ) of the ellipse ( 23 ) or any oval ( 24 ) or the convex link ( 25 ) aligned airfoils ( 32 ) and / or characterized in that the axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) rigidly ( 31 ) is connected to at least one radial ( 6 ) in concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) mounted turbine blade ( 22 ), which are radially ( 6 ) from the center ( 4 ) of the compressor turbine ( 33 ) in on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) and / or characterized in that at least one axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) with at least one radial ( 6 ) to the center ( 5 ) of the ellipse ( 23 ) or any oval ( 24 ) or the convex link ( 25 ) oriented turbine blade ( 22 ), the rigid ( 31 ) with the compressor turbine ( 34 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) in the exhaust stream ( 35 ) concentric ( 7 ) eccentric ( 8th ) and stored compressor turbine ( 33 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) with the center ( 4 ) of the ellipse ( 23 ) or any oval ( 24 ) or the convex link ( 25 ) remotely oriented turbine blades ( 22 ), characterized in that the concentric ( 7 ) eccentric ( 8th ) positioned and stored compressor turbine ( 33 ) axially ( 9 ) in the exhaust stream ( 15 ) concentric ( 7 ) eccentric ( 8th ) is positioned and stored and the influx ( 35 ) by at least one intake pipe ( 40 ) to the compressor turbine ( 33 ), characterized in that the one, several or all compressor turbines ( 33 ) in at least one exhaust pipe ( 16 ) are stored. Device according to at least one of the preceding claims, characterized in that the turbine blades ( 22 ) of the compressor turbine ( 33 ) are variably rotatable about their longitudinal axes ( 36 ) are. Device according to at least one above-mentioned claim, characterized in that at least one axially or coaxially mounted exhaust gas turbine ( 26 ) in the exhaust stream ( 15 ) and at least one axially or coaxially mounted compressor turbine ( 28 ) which is combined with any or all of claims 10 through 13 inclusive. Apparatus according to claim 1, characterized in that at least one axial ( 9 ) in the influx ( 35 ) positioned and stored propellers ( 34 ), constructed as in the aforementioned embodiments claimed exhaust gas turbine ( 10 ), radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) is characterized in that at least one axially ( 9 ) Influx of gas and / or fluids ( 3 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored propeller ( 34 ) on a circular ( 21 ) is connected to radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) aligned airfoils ( 32 ) and / or characterized in that the axial ( 9 ) to the influx of gas and / or fluids ( 3 ) positioned and stored propellers ( 34 ) rigidly ( 31 ) is connected to at least one radial ( 6 ) in concentric ( 7 ) eccentric ( 8th ) Circular ( 21 ) stored Airfoil ( 32 ), which is radially ( 6 ) from the center ( 4 ) of the propeller ( 34 ) in a circle ( 21 ) and / or characterized in that at least one axial ( 9 ) to the influx of gas and / or fluids ( 3 ) positioned and stored propeller ( 34 ) with at least one radial ( 6 ) to the center ( 5 ) of the circular ( 21 ) aligned airfoil ( 32 ) that is rigid ( 31 ) with the propeller ( 34 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx of gas and / or fluids ( 3 ) positioned and stored propellers ( 34 ) with the center ( 4 ) of the circular ( 21 ) is connected to the removal-oriented blades, characterized in that the concentric ( 7 ) eccentric ( 8th ) positioned and stored propellers ( 34 ) axially ( 9 ) in the influx of gas and / or fluids ( 3 ) and the influx ( 15 ) by at least one jacket tube ( 30 ) to the propeller ( 34 ), characterized in that the one, several or all propellers ( 34 ) in at least one jacket tube ( 30 ) and / or second jacket tube ( 1 ) are stored. characterized in that the propeller ( 34 ) in an influx of gas and / or fluids ( 3 ) is used. Device according to claim 1 and 10, characterized in that at least one axial ( 9 ) in the influx of gas and / or fluids ( 3 ) positioned and stored propellers ( 34 ), constructed as in the aforementioned embodiments claimed exhaust gas turbine ( 10 ), radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is characterized in that at least one axially ( 9 ) to the influx of gas and / or fluids ( 3 ) concentric ( 7 ) eccentric ( 8th ) positioned and stored propeller ( 34 ) on an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) is connected to radial ( 6 ) to the center ( 5 ) of the ellipse ( 23 ) or any oval ( 24 ) or the convex link ( 25 ) aligned airfoils ( 32 ) and / or characterized in that the axial ( 9 ) to the influx of gas and / or fluids ( 3 ) positioned and stored propellers ( 34 ) rigidly ( 31 ) is connected to at least one radial ( 6 ) in concentric ( 7 ) eccentric ( 8th ) in an ellipse ( 23 ) or in any oval ( 24 ) or in a convex link ( 25 ) stored airfoil ( 32 ), which is radially ( 6 ) from the center ( 4 ) of the propeller ( 34 ) in an ellipse ( 23 ) or in any oval ( 24 ) or in a convex link ( 25 ) and / or characterized in that at least one axial ( 9 ) to the influx of gas and / or fluids ( 3 ) positioned and stored propeller ( 34 ) with at least one radial ( 6 ) to the center ( 5 ) of the ellipse ( 23 ) or any oval ( 24 ) or the convex link ( 25 ) aligned airfoil ( 32 ) that is rigid ( 31 ) with the propeller ( 34 ) is connected by a rotatable first shaft ( 17 ) or over or under reduction device or rigid ( 31 ) Connection with at least one axial ( 9 ) to the influx ( 35 ) positioned and stored propellers ( 34 ) with the center ( 4 ) of an ellipse ( 23 ) or any oval ( 24 ) or a convex link ( 25 ) remotely oriented airfoils ( 32 ), characterized in that the concentric ( 7 ) eccentric ( 8th ) positioned and stored propellers ( 34 ) axially ( 9 ) in the influx of gas and / or fluids ( 3 ) and the influx of gas and / or fluids ( 3 ) by at least one jacket tube ( 30 ) to the propeller ( 34 ), characterized in that the one, several or all propellers ( 34 ) in at least one jacket tube ( 30 ) are stored. characterized in that the propeller ( 34 ) in an influx of gas and / or fluids ( 3 ) is used. Device according to at least one of the preceding claims, characterized in that an airfoil ( 32 ), several or all airfoils ( 32 ) of the propeller ( 34 ) or a turbine blade ( 22 ), several or all turbine blades ( 22 ) a turbine ( 41 ) or an exhaust gas turbine ( 10 ) or a fan ( 11 ) or a compressor ( 12 ) or a compressor turbine ( 33 ) are variably rotatable about their longitudinal axes ( 36 ) are. Device according to at least one above-mentioned claim, characterized in that at least one second jacket blank ( 1 ), characterized in that the first, second or all fan ( 11 ) and / or the first, second or all compressors ( 12 ) and / or the first, second or all exhaust gas turbines ( 10 ) and / or the first, second or all turbines ( 41 ) between ( 2 ) first jacket pipe ( 30 ) and second jacket tube ( 1 ), characterized in that the first, second or all fan ( 11 ) and / or the first, second or all compressors ( 12 ) and / or the first, second or all exhaust gas turbines ( 10 ) and / or the first, second or all turbines ( 41 ), each with at least one to the center ( 5 ) and / or from the center ( 4 ) removing turbine blades ( 22 ) are connected by a rotatable, second or further wave ( 37 ) or transfer or reduction device or rigid connection ( 31 ) are connected. Device according to one or more of the preceding claims, characterized in that a device according to one or more previously mentioned embodiments according to one or more of the aforementioned claims for obtaining electrical energy from an exhaust gas stream ( 15 ) of an internal combustion engine, comprising at least one exhaust pipe ( 16 ), an exhaust gas turbine ( 10 ) or compressor turbine ( 33 ) or comprising at least one compressor tube and a turbine ( 41 ) according to one or more of the above-mentioned embodiments in one or more of the preceding claims and a dynamo ( 14 ), characterized in that the exhaust gas turbine ( 10 ) or compressor turbine ( 33 ) the kinetic energy of the exhaust gas stream ( 15 ) converts into a rotational movement, characterized in that the exhaust gas turbine ( 10 ) or compressor turbine ( 33 ) at the concentric ( 7 ) eccentric ( 8th ) Storage in the intermediate space ( 2 ) in the exhaust pipe ( 16 ) is connected to the dynamo ( 14 ) about the rotational movement of the exhaust gas turbine ( 10 ) or compressor turbine ( 33 ) to be able to record. Apparatus according to claims 1 to 14 inclusive, characterized in that a device according to one or more of the aforementioned embodiments according to one or more of the aforementioned claims for obtaining electrical energy from an influx ( 35 ) and / or a gas or fluid ( 3 ) or a gas stream ( 42 ) comprising at least one fan ( 11 ) or at least one turbine ( 41 ) at least one propeller ( 34 ), at least one jacket tube ( 30 ) or compressor tube ( 29 ) and a dynamo ( 14 ), characterized in that the fan ( 11 ) or the propeller ( 34 ) or the turbine ( 41 ) the kinetic energy of the influx ( 35 ) and / or the gas or fluid ( 3 ) in a rotational movement, characterized in that the fan ( 11 ) or the propeller ( 34 ) or the turbine ( 41 ) at the radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) Storage is connected to the dynamo ( 14 ) about the rotational movement of the exhaust gas turbine ( 10 ) or the compressor turbine ( 33 ) to be able to record. Apparatus according to claim 14, characterized in that the exhaust gas turbine ( 10 ) or compressor turbine ( 33 ) or the turbine ( 41 ) axially ( 9 ) to the exhaust stream ( 15 ) in at least one exhaust pipe ( 16 ) or compressor tube ( 29 ) or selected or all exhaust pipes ( 16 ) is positioned. Apparatus according to claim 15, characterized in that the fan ( 11 ) or the propeller ( 34 ) or the turbine ( 41 ) axially ( 9 ) to the influx ( 35 ) of the oxidizer or gas or fluid ( 3 ) in at least one jacket tube ( 30 ) or selected or further jacket pipes ( 1 ) or compressor tube ( 29 ) is positioned. Apparatus according to claim 1 to 14 inclusive, characterized in that the internal combustion engine ( 19 ) is operated in a consumer selected from the group of passenger cars, hybrid vehicles, fuel cell vehicles, trucks, buses, agricultural tractors, ships, submarines, aircraft, helicopters, escape-speed vehicles, in particular rockets, gas and / or coal power plants. Apparatus according to claim 1 to 14 inclusive, characterized in that the turbine ( 41 ), the exhaust gas turbine ( 30 ), the compressor turbine ( 33 ), the fan ( 11 ) or the turbine ( 41 ) or the propeller ( 34 ) in a consumer selected from the group of passenger cars, hybrid vehicles, fuel cell vehicles, trucks, buses, agricultural tractors, ships, submarines, aircraft, helicopters, escape-speed vehicles, in particular rockets, gas and / or coal power station, wind power plants, wind turbines or water jet drive is operated. Device according to one or more of the preceding claims, characterized in that the consumer comprises an electric power supply system and / or an electric motor. Device according to at least one claim, characterized in that the device comprises an accumulator. Device according to at least one claim, characterized in that the accumulator is connected to the dynamo ( 14 ) and is connected to the energy supply system and / or the electric motor of the consumer and stored in it energy stored in the power supply system and / or the electric motor ( 14 ) can feed. Device according to at least one claim, characterized in that the device comprises a gearbox for determining the number of rotations per unit of time during the transmission of the rotational movement from the shaft ( 17 ) on the dynamo ( 14 ) to reduce. Device according to one or more of the preceding claims, characterized in that the device comprises means for sound damping. Device according to one or more of the preceding claims, characterized in that the internal combustion engine ( 19 ) is an Otto engine, a Diesel engine, a Wankel engine, an HCCi engine, a turboprop engine, a jet engine, a ramjet engine, a combined jet / ramjet engine, a hybrid engine or a Stirling engine, or that the internal combustion engine is in a gas and / or coal power plant or in a jet engine, a single-jet or twin-jet engine, a ramjet engine, a ramjet jet engine, a scramjet jet engine, a jet engine or a rocket engine is operated. Device according to one or more of the preceding claims, characterized in that the turbine ( 41 ), the exhaust gas turbine ( 10 ), the fan ( 11 ), the compressor ( 12 ), the propeller ( 34 ) or the compressor turbine ( 33 in a turboprop engine, a jet engine, a ramjet engine, a combined jet / ramjet engine, a Stirling engine, a gas and / or coal power plant or in a jet engine, a single jet or twin jet engine, a ramjet engine, a ramjet jet engine , a Scramjet jet engine, a jet engine or a rocket engine or in wind power plants or in wind turbines is operated. Apparatus according to claim 20, characterized in that the electric motor comprises a rotatable second shaft ( 37 ), between exhaust pipe ( 16 ) or compressor tube ( 29 ) and jacket tube ( 30 ) positioned and stored with a compressor ( 12 ) of a jet engine, a single-jet or two-jet engine, a ramjet engine, a combined jet / ramjet engine or turbocharger according to the at least one preceding claim and / or a rotatable third shaft ( 37 ), between exhaust pipe ( 16 ) or compressor tube ( 29 ) and jacket tube ( 30 ) positioned and stored with a fan ( 11 ) of a jet engine, a single jet or two jet engine of a ramjet engine, a combined jet / ramjet engine, a rocket engine or a rotatable third shaft ( 37 ), between exhaust pipe ( 16 ) or compressor tube ( 29 ) and jacket tube ( 30 ) and / or jacket tube ( 30 ) and second jacket tube ( 1 ) positioned and stored with a fan ( 11 ) of a jet engine, a single-jet or two-jet engine of a ramjet engine, a combined jet / ramjet engine, a rocket engine or with a propeller ( 34 ) of a turboprop engine, of a jet engine or of a marine propulsion engine or of a compressor turbine ( 33 ) is connected to a turbocharger or turbocharger according to the invention, and / or at least one further, fourth shaft drives, characterized in that the compressor ( 12 ) and / or the fan ( 11 ) or the compressor turbine ( 33 ) or the propeller ( 34 ) driving shaft (s) and / or the at least one further driven shaft at the concentric ( 7 ) eccentric ( 8th ) Storage between ( 2 ) Exhaust pipe ( 16 ) or compressor tube ( 29 ) and jacket tube ( 30 ) and / or jacket tube ( 30 ) and second jacket tube ( 1 ) and transmits the rotary motion. Apparatus according to claim 20 and 25, characterized in that the electric motor is a shaft which is connected to a turbine ( 41 ), a fan ( 11 ), the compressor ( 12 ) or with a propeller ( 34 ) is connected to a device according to one or more of the preceding claims, and / or drives at least one further shaft, characterized in that the turbine ( 41 ), the fan ( 11 ), Compressors ( 12 ), Propellers ( 34 ) driving shaft and / or the at least one further driven shaft at the concentric ( 7 ) eccentric ( 8th ) Storage of the turbine ( 41 ), the fan ( 11 ), Compressors ( 12 ), Propellers ( 34 ) as described in the preceding claims, which transmits rotary motion. Use of the device according to at least one above-mentioned claim for obtaining electrical energy from an exhaust gas stream ( 15 ) of an internal combustion engine. Use of the device according to the at least one preceding claim for obtaining electrical energy from an influx ( 35 ) and / or from a gas or fluid ( 3 ) or a gas stream ( 42 ). Method for obtaining electrical energy from an exhaust gas stream ( 15 ) of an internal combustion engine, comprising the steps a. Removal of kinetic energy from an exhaust gas flow ( 15 ) using a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) stored exhaust gas turbine ( 10 ) and / or a fan ( 11 ) and / or a compressor ( 12 ) or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and stored compressor turbine ( 33 ) or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and mounted turbine ( 41 ), which as a basic form is circular ( 21 ) and / or an ellipse ( 23 ) and / or any oval ( 24 ) and / or a convex link ( 25 ), b. Conversion of the kinetic energy of the devices of claim 31. a. in a rotary motion, c. Transmission of the rotational movement of the devices of claim 31. a. and b. on a rotatable first shaft ( 17 ) and / or second ( 37 ) and / or further wave ( 37 ). Process for obtaining electrical energy from an influx ( 35 ) and / or from a gas or fluid ( 3 ) or gas stream ( 42 ) comprising the steps a. Taking kinetic energy from an influx ( 35 ) and / or from a gas or fluid ( 3 ), which is directed to a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and mounted exhaust gas turbine ( 10 ) and / or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and stored fan ( 11 ) and / or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and stored compressors ( 12 ) or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and stored compressor turbine ( 33 ) or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and mounted turbine ( 41 ) or a concentric ( 7 ) eccentric ( 8th ) radially ( 6 ) positioned and stored propellers ( 34 ), which as a basic form is circular ( 21 ) and / or an ellipse ( 23 ) and / or any oval ( 24 ) and / or a convex link ( 25 ), b. Conversion of the kinetic energy of the devices of claim 32. a. in a rotary motion c. Transmission of the rotary motion of the devices of claim 32. a. and b. on a rotatable first shaft ( 17 ) and / or second ( 37 ) and / or further wave ( 37 ). A method for obtaining electrical energy according to claim 31 and 32, wherein for the steps 31. a., B. and c. an exhaust gas turbine present in the consumer ( 10 ) or compressor turbine ( 33 ) and / or a fan ( 11 ) or a compressor ( 12 ) or a turbine ( 41 ) a propeller ( 34 ) is being used. Process according to claims 22 to 27 inclusive comprising the steps a. Transmission of the rotational movement of the rotatable first shaft ( 17 ) or further wave ( 37 ) on a dynamo ( 14 b. Conversion of the rotational movement by the dynamo ( 11 ) into electrical energy. The method of claims 20 to 25 inclusive, comprising the steps a. Feeding the generated electrical energy into a power supply system and / or an electric motor of a consumer or b. Storage of the generated electrical energy in an accumulator. Method according to the preceding claims, comprising the steps a. radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) on a circular ( 21 ) or elliptical ( 23 ) or oval ( 24 ) or concave link ( 25 ) mounted turbine ( 41 b. Construction of the turbine ( 41 ) on a concentric ( 7 ) eccentric ( 8th ) circular ( 21 ) or elliptical ( 23 ) or oval ( 24 ) or concave link ( 25 c. Storage of the turbine ( 41 ) between ( 2 ) Exhaust pipe ( 16 ) and / or compressor tube ( 29 ) and / or jacket tube ( 30 ) and / or between jacket pipe ( 30 ) or compressor tube ( 29 ) and second jacket tube ( 1 ) while maintaining the rotational capability of the turbine or in rigid connection, d. Turbine ( 41 ) consisting of at least one radial ( 6 ) from the center ( 4 ) and / or a radial to ( 5 ) Center of the turbine ( 41 ) oriented turbine blade ( 22 ) and / or rotatable ( 36 ) Turbine blades ( 22 ) and / or rotatable ( 36 ) Turbine blade ( 22 ); Propeller ( 34 ) consisting of at least one radial ( 6 ) from the center ( 4 ) and / or a radial to ( 5 ) Center of the propeller-oriented airfoil ( 32 ) and / or rotatable ( 36 ) Blade ( 32 e. the turbines ( 41 ) or propeller ( 34 ) after 35. d. rotate in the same direction of rotation or in opposite directions. Method according to the preceding claims, comprising the steps a. The turbines ( 41 ) are at least one rotatable first wave ( 17 ) or a rotatable second shaft ( 37 ) or all rotatable shafts ( 37 b. rigid ( 31 ) and / or by a transmission and / or by an electric motor ( 14 ), c. and the turbines ( 41 ) are in terms of their respective structure as radial ( 6 ) concentric ( 7 ) eccentric ( 8th ) positioned and mounted turbine ( 41 ) in circular ( 21 ) or in elliptical ( 23 ) or in oval ( 24 ) or concave link ( 25 ), d. the individual turbine forms in 37. c. can be combined.

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