WO2014191637A2

WO2014191637A2 - Aerobic and / or anaerobic propulsion device with combined and simultaneous steady-state operation and propelled systems and assemblies including such a device

Info

Publication number: WO2014191637A2
Application number: PCT/FR2014/000117
Authority: WO
Inventors: Pierre François Yannick AGOSTINI
Original assignee: Agostini Pierre François Yannick
Priority date: 2013-05-31
Filing date: 2014-05-26
Publication date: 2014-12-04
Also published as: WO2014191637A3; FR3006381B1; FR3006380B1; FR3006380A1; WO2014191637A4; FR3006381A1

Abstract

The invention relates to an aerobic and / or anaerobic propulsion device with combined and simultaneous steady-state operation and propelled systems and assemblies including such a device. The invention relates to a propulsion device making it possible to obtain a significant increase in the mass flow and thrust. It is made up of an aerobic and / or anaerobic propulsion device (101) equipped with at least one turbopump (1), a system for converting heat energy into kinetic energy made up of a bypass device and a dense rare gas fluid injection system. The device according to the invention is in particular intended for the propulsion of systems and assemblies.

Description

AEROBIC AND / OR ANAEROBIC TYPE PROPULSION DEVICE HAVING PERMANENT COMBINED AND SIMULTANEOUS TYPE OPERATION AND SYSTEMS AND PROPELLED ASSEMBLIES HAVING SUCH A DEVICE

DESCRIPTION

The subject of the present invention is an aerobic and / or anaerobic propulsion device with steady-state operation of combined and simultaneous type and propulsion systems and assemblies comprising such a device.

The subject of the present invention is an aerobic and / or anaerobic propulsion device with steady-state operation of combined and simultaneous type, and propulsion systems and assemblies comprising such a device and characterized in that the device has a combined type of permanent operation. and simultaneous and in that the speech "presents a continuous operation of combined and simultaneous type" defines an additional characteristic defining the device itself and not the manner in which the device is operated.

Moreover, no aerobic and / or anaerobic propulsion device operating in steady state of combined and simultaneous type and systems and propulsion systems comprising such a device have been realized to date.

The current state of the art in terms of heavy launcher lunar or Martian capacity is represented by the industrial realization of the rocket Saturn V dating from 1969 and the Apollo program, some studies were conducted and then abandoned because of technological barriers incompatible with an economically profitable space program.

The object of the present invention is to be able to manufacture industrially, with the aid of the propulsion device of the invention, a range of launchers ranging from the Vega, Dragon, Falcon 9 or Soyuz rocket market to the large launchers. Ariane 5 and the very large Saturn V or Ares launchers and well beyond these performances with heavy and heavy launchers, the latter to consider the Martian exploration with the return of the crews, as well as the return of the man on the moon and the industrial exploitation of the geological resources of the lunar regolith on the basis of the book "Return to the Moon" writes by Harrison H. Schmitt, and in particular the lunar helium 3 resources that can be used as fuel in clean and environmentally friendly thermonuclear fusion reactors in order to produce abundant energy and to provide energy independence for hundreds of thousands of years. years while being economically viable, depreciable and profitable by making the energy transition.

The object of the present invention is to overcome the aforementioned drawbacks and to provide an aerobic and / or anaerobic propulsion device characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic propulsion motor, and / or or anaerobic, has a greater thrust than is currently allowed by the state of the art and that said engines with aerobic propulsion and / or anaerobic are equipped on the one hand with "by-pass" systems Also known as "by-pass" and / or in that the aerobic and / or anaerobic propulsion engines are equipped with turbopumps with improved characteristics resulting in an increase in injection pressures and mass flow, resulting in a significant increase in the thrust for liquid propellant engines and / or in that the feed parameters (pressure and mass flow) of said engines are adapted to the conditions and the flight path by the use of at least one propellant with at least one liquid or cryogenic fluid of the "rare" gas type, also called "noble" type gases or "inert" gases, allowing and to continuously vary the thrust by controlling the speed of rotation of the turbopump and the mass flow rates injected into said engine and thus to adapt the thrust to the conditions and the duration of flight of the system or systems propelled comprising a such device.

Furthermore, no aerobic and / or anaerobic propulsion device and powered assemblies comprising such a device having the advantage of a significant increase in the thrust and the mass flow rate beyond the possibilities of the current state of the art. has not been realized to date, this invention constituting a major breakthrough and a break in the current technological barriers in the field of aeronautical and space propulsion in the field of heavy launchers of greater capacity than the Ariane 5 ME rocket.

All aerobic and / or anaerobic propulsion engine devices to date all use at least one aerobic static or dynamic compression stage, an aerobic and / or anaerobic combustion chamber and at least one exhaust nozzle, the existence of at least one aerobic stage static or dynamic compression being unavoidable and all have the disadvantage of reduced thrust compared to the possibilities of the invention.

The aerobic and / or anaerobic type engines comprising at least one combustion chamber and at least one expansion nozzle also known as a jet engine or a thermo-propulsion nozzle, used in the field of aerospace and / or aeronautics operate using solid or liquid propellants, and at least one propellant supply turbopump of at least one combustion chamber in the case where they are liquid.

The principle lies in the violent expansion of fluids or solids which, most of the time, passes through a phase change from the liquid state to the gaseous state, or from the solid state to the gaseous state, then to be relaxed in at least one expansion nozzle. The propulsive force or thrust force of the aerobic and / or anaerobic engine, also called a rocket engine or a thermo-propulsion nozzle, is thus generated on the one hand by a specific energy transfer of the propellants or monergols into the kinetic energy of the gases in the presence and on the other hand by an initial kinetic energy transfer of the fluids in the presence of final kinetic energy transferred to the system and propelled assembly comprising such a propulsion system, and in the case of liquid propellants or monergols the phenomenon converting the The specific energy of said liquid propellants or monergols in kinetic energy is self-maintained by feeding said liquid propellants or monergols of at least one combustion chamber, also called the propulsion chamber, by at least one feed turbopump.

Currently, aerobic and / or anaerobic type motors and more particularly anaerobic motors have the disadvantages a limited lifetime, due to oxidation and corrosion of the walls, or even the destruction of said walls in the presence of propellant combustion or monergols, and a low temperature of said walls in the absence of external cooling system.

No current aerobic and / or anaerobic propulsion engine has internal confinement of combustion by injection of a fluid at the walls of said anaerobic engine in order to preserve the materials constituting the attacks and chemical degradations due to the combustion of the propellants, whether they are solid or liquid.

No current aerobic and / or anaerobic propulsion engine has internal confinement of combustion by injection of a fluid at the walls just upstream of the neck of the nozzle of said aerobic and / or anaerobic propulsion engine in order to modify the lines. flow current ejected at said neck and vary the ratio of the sections between the neck section of the nozzle and the section of the free outlet of said nozzle of the aerobic and / or anaerobic propulsion engine and in that said injection of a fluid makes it possible to adapt to the different flight phases the thrust force of said aerobically and / or anaerobically propelled engine by varying the injection pressure as well as the flow rate of said injected fluid and in that said injection of a fluid it makes it possible to modify the intrinsic characteristics of the fluid ejected at the free outlet of the nozzle of said aerobic and / or anaerobic propulsion engine, such as for example enter the density and the speed of sound of the fluid medium.

No current aerobic and / or anaerobic propulsion engine has an internal mirror to the nozzle of the aerobically and / or anaerobically propelled engine in order to maximize the heat exchange by radiation between the various fluids, for example the hot combustion gases and the fluid. injected, and to minimize the absorption of thermal radiation by the wall of the nozzle.

A turbopump is in aeronautics and / or astronautics a propellant pump or liquid or cryogenic fluids generally driven by a turbine rotating at several thousand revolutions per minute, which pressurises at least one liquid propellant and / or at least one fluid before being injected into at least one propulsion chamber of an aerobic and / or anaerobic propulsion device also an aerobically and / or anaerobically propelled motor, with propellants and / or liquid fluids. This element of said engine plays an essential role in the performance of said engine because the thrust thereof depends on the pressure of the propellants arriving in at least one propulsion chamber still called combustion chamber. The turbine driving the turbopump can be moved by the gases produced by a gas generator. The energy to be supplied to turn the turbines is then very important. The pressure, rotation speed, flow rate and / or extreme temperatures of the cryogenic propellants make the turbopump the most complex part to design in an aerobic and / or anaerobic propulsion engine, for example in a type of motor. rocket engine and generally has a duration of life and reliability l imitated and has the disadvantage of not operating at variable speed.

All turbopumps generally have a single gas propulsion turbine coupled on the same rotational shaft common to one or two pumps and whose advantage is to present speeds of critical speed, power and maximum speed of use. a limited pump outlet pressure having the disadvantage of a limited thrust of the aerobic, aerobic and / or anaerobic propulsion motor, anaerobic impeded by said turbopump, and in that the assemblies thus constituted by the "pump" function and by the turbine function are not balanced due to the existence of axial forces in the rotation shaft of said turbopump.

The present invention aims at remedying the aforementioned drawbacks and at producing an aerobic and / or anaerobic propulsion device with steady-state operation of combined and simultaneous type and propulsion systems and assemblies comprising such a device and characterized in that said device has a combined and simultaneous continuous type operation and that the "present a combined and simultaneous type of continuous operation" defines an additional characteristic defining the device itself and not the manner in which the device is operated and in that said device makes it possible to increase the thrust with respect to what is permitted by the state of the art and that said aerobic and / or anaerobic propulsion device, also called an engine. aerobic and / or anaerobic propulsion is equipped on the one hand with "bypass" systems also "by-pass" and / or in that the aerobic and / or anaerobic propulsion engine is equipped with turbopumps with improved characteristics resulting in an increase in mass flow and thrust for liquid propellant engines and / or that the mass flow rate of said engines is adapted to the conditions and the flight path by the use of at least one propellant with at least one cryogenic liquid fluid of the rare gas type, thus making it possible to vary the thrust in a continuous manner by controlling the speed of rotation of the turbopump and the mass flow rates injected into said engine and thus to adapt the thrust to the conditions and the flight duration of the system or systems propelled comprising such a device and in that said balanced turbopumps having a resultant zero or almost zero axial forces can generate propellant supply flow and / or fluid flow torques using the propulsion device allowing pressures in the combustion chamber of from 20 to 100 mega pascals and more and in that the rare gas injection systems used to increase thrust (111), (114) and (115) be used in addition to the bypass in the ground or Mars take-off phase, then be used to compensate for the drop in the bypass system due to the altitude gain and the consequent drop in air density or the atmosphere whether terrestrial or Martian or used to obtain an aerobic propulsion device and / or anaerobic variable thrust in the absence of atmosphere in the "vacuum" as for example in the phases of moon landing or take-off, or in conjunction with the by-pass system in the case of a "marshalling" or take-off on Mars, and in that the bypass system associated with the injection of rare gas constitutes a convertible thermal energy in kinetic energy resulting in the increase of the total thrust, and in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is characterized by a very significant increase in the thrust and in that said engine does not include an "aerobic" compression stage located at the inlet of the bypass device and disposed upstream of the dilution zone (104), supersonic or hypersonic supersonic or hypersonic conditions, knowing that a dilution consists of the addition of a first fluid composed of the aerobic fluid stream of the bypass to a second fluid composed of hot combustion gases to reduce the concentration of the second fluid consisting of said hot combustion gases and in that said aerobic propulsion device and / or anaerobic, also called aerobic and / or anaerobic propulsion engine, comprises in the central part an aerobic and / or anaerobic propulsion device (101) using at least one solid or liquid propellant and / or a rare gas type liquid fluid and said at least one liquid propellant and / or rare-type liquid fluid is injected upstream of the neck of the nozzle (103) into at least one combustion chamber (102) and / or downstream of the neck of the nozzle ( 103) using at least one feed system composed of at least one feed turbopump, which is part of the invention and in that the propulsion device has at least one combustion chamber. aerobic and / or anaerobic (102) generating hot combustion gases fed upstream of an exhaust nozzle (103) of the combustion chamber, the ejection of hot combustion gases in supersonic or hypersonic mode is in the downstream part (105) of the outlet nozzle of the combustion chamber situated downstream of the throat of the nozzle of the aerobic and / or anaerobic propulsion device, and in that the aerobic and / or anaerobic propulsion device , also called aerobic and / or anaerobic propulsion engine comprises a bypass system consisting of an outer casing (107) defining an aerobic fluid vein (106) flowing between the outer casing (107) and the central body of the device. aerobic and / or anaerobic propulsion (101) and in that the ejection of hot combustion gases in the supersonic or hypersonic mode occurring in the downstream portion (105) of the exhaust nozzle of the combustion chamber generates a depressurization n at the inlet of the bypass (109) it operates as a static vacuum cleaner by fluid drive, the bypass from the front of the system and / or the propelled assembly to the rear of it by creating a general outlet nozzle (108) so that the outlet nozzle (103) of the combustion chamber of the aerobic and / or anaerobic central propulsion device is located inside the nozzle the output device (108), and in that said "aerobic and / or anaerobic" type propulsion device, also called an "aerobic and / or anaerobic "includes a general outlet nozzle (108) which receives the hot combustion gases from the outlet nozzle (103) of the combustion chamber of the aerobically and / or anaerobically propelled engine and which provides the supersonic or hypersonic dilution. said hot combustion gases, the thermal exchange expansion and the supersonic or hypersonic expansion of the aerobic fluid vein (106) from the bypass and at the outlet thereof in the supersonic or hypersonic dilution zone (104) operating at supersonic or hypersonic conditions, located in the downstream portion of the outlet nozzle (103) of the combustion chamber which generates a pressure difference between the bypass vacuum inlet (109) and its outlet operating in the supersonic or hypersonic, all resulting in a significant increase in the mass flow ejected at the outlet of the general outlet nozzle (108), the thrust and the speed ejection outlet at the outlet of the general outlet nozzle (108), and in that the vacuum force generated at the inlet (109) of the bypass contributes to improving the aerodynamic performance of the systems and assemblies propelled by adding to the thrust force from the general outlet nozzle (108) and in that said "aerobic and / or anaerobic" type propulsion device, one of the essential characteristics of which is to operate using the capacity of a fluid stream to when it is subjected to a force resulting from the driving ability of a moving layer on the other adjacent layers knowing that the movement of the aerobic fluid vein (106) in the by-pass can be considered as resulting from the sliding of the fluid layers on each other and in that the aerobic fluid stream (106) is subjected to a pressure difference between the bypass inlet and the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, resulting in entrainment of the aerobic fluid vein (106) in the bypass and that another essential feature is that the fluid entrainment is performed from a supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, creating a permanent fluid drive from supersonic or hypersonic conditions of the supersonic dilution zone (104) or hypersonic operating conditions supersonic or hypersonic, and not from subsonic conditions and that one of the other essential features is that the bypass feeds a supersonic or hypersonic dilution zone generated by the dilution of the hot combustion gases from a nozzle of Laval (103) creating a supersonic or hypersonic fluid vein mixing with the aerobic fluid vein (106) of the bypass, also in supersonic or hypersonic mode thus performing a supersonic or hypersonic dilution in a dilution zone and whose essential characteristic is that this dilution zone opens downstream of the outlet of the nozzle (103) of Laval from which are produced the hot combustion gases in a general outlet nozzle (108), and whose profile is in the extension of the nozzle (103) of upstream Laval and characterized in that the section of the beginning of the divergent of the general outlet nozzle (108) has an equal or superior section at the outlet section of the nozzle (103) thereby allowing a particular operation in that the nozzle (103) is nested in the nozzle (108) precisely and so that the hot combustion gases at the outlet of the nozzle (103) have a supersonic or hypersonic velocity which they maintain at the beginning section of the divergent of the general exhaust nozzle (108) and which are then accelerated a second time by the dilution in the diverging part of the nozzle (108), thus enabling the generation of a continuous and continuous supersonic or hypersonic flow characterized in that the by-pass system of the invention provides a significant thrust gain of a coefficient greater than one and up to to three and more and in that the nozzle (103) and the aerobic fluid vein (106) does not supply another combustion chamber or a subsonic dilution zone which would be located for example upstream of the collar of a Laval nozzle in subsonic or sonic mode and in that said supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions dilutes and exalt the hot combustion gases from the nozzle ( 103) and the aerobic fluid vein resulting from the bypass by dilation and acceleration of the fluid stream from the bypass and in that this expansion is carried out simply by thermal exchanges by conduction, by convection and by thermal radiation and by what the aerobic fluid vein proceeds to exalt the hot gases of combustion whose kinetic energy released from the absorption of a portion of the thermal energy of the hot combustion gases, on the one hand generates said fluid entrainment of the aerobic fluid stream (106) flowing in the bypass; pass and generates on the other hand the increased thrust of the propulsion device, steady state and continuous type combined and simultaneous and that the device of the invention does not proceed from the principles of operation of the ramjets that have a compression stage static at the level of the air intake whose fluid stream feeds a combustion chamber in subsonic mode to then be expanded and accelerate in a Laval nozzle and in that to date no industrial device using the principles of the invention allowing to obtain for example with a motor with aerobic propulsion (by-pass) and anaerobic (engine-rocket) on take-off a thrust equal to at least three times and more the push ee of the same engine in the vacuum, has been realized and in that the device of the invention relates to systems and propulsion systems comprising such a device.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic engine, comprises a bypass. consisting of an outer casing (107) disposed over the entire length of the system and the propelled assembly thereof being provided with a general outlet nozzle (108), and in that the propulsion device also called a motor. aerobic and / or anaerobic comprises at least one supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the general outlet nozzle (108), followed by one or a plurality of general exhaust nozzles output (108).

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least one aerobic and / or anaerobic propulsion device. or a plurality of combustion chambers (102) located upstream of at least one or a plurality of outlet nozzles (103) of at least one or a plurality of combustion chambers.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic motor provided with at least one nozzle device outlet (103) of the combustion chamber and in that said nozzle is, downstream of the neck of the nozzle (103), provided with devices for improving the dilution and cooling of the outlet nozzle device (103) of the combustion chamber, such as in that said devices for improving the dilution and cooling consist of recesses in the wall of said nozzle (103), the aerobic propulsion device and / or anaerobic, also called engine to aerobic and / or anaerobic propulsion.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises a device for aerobic and / or anaerobic propulsion. aerobic and / or anaerobic propulsion, also called aerobic and / or anaerobic motor provided with at least one outlet nozzle device (103) of the combustion chamber and in that said nozzle is downstream of the neck of the nozzle ( 103), provided with devices for improving the dilution and cooling of the outlet nozzle device (103), of the combustion chamber such as, for example, that said devices for improving dilution and cooling consist of recesses. axial, longitudinal or parallel to the axis of the nozzle (103) and located in the wall of said nozzle (103) after the neck in the non-cylindrical divergent portion of the device aerobic and / or anaerobic propulsion system, also called an aerobic and / or anaerobic propulsion engine, and in that the presence of the devices for improving the dilution and the cooling makes it possible to amplify the phenomenon of fluid entrainment in supersonic or hypersonic mode of the aerobic fluid vein (106) resulting in an increased vacuum force at the inlet of the bypass system (109).

The present invention also aims at providing an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic type motor, characterized in that said aerobic and / or anaerobic propulsion device comprises the presence of an aerobic and / or anaerobic type of propulsion device. consecutive and successive ovoid recesses in the diverging nozzle (103) which allows the exaltation of the kinetic energy of the hot combustion gases from the aerobic fluid vein (106) which by successive exaltations, the recesses being one upstream of the others, allows to exalt the total resultant kinetic energy of the total output fluid stream, by the process of having a fluid vein exalted by a first ring of recesses which heats and expands said injected fluid allowing a conversion of thermal energy into kinetic energy so that that the kinetic energy of the hot combustion gases is higher at the second recess and in that the process is repeated cascading step by step and recesses recesses to the extent that the recesses are calibrated according to the convertible thermal energy available, which has the consequence of having a fluid entrainment phenomenon of the aerobic fluid vein (106) much higher compared the same system without recesses, knowing that the fluid entrainment of the aerobic fluid vein (106) in the bypass is more important in the case of a hollow nozzle, the vacuum force at the input of the by- pass is increased which makes it possible to increase the mass flow rate at the outlet of the general nozzle (108) and consequently to increase the total thrust force which is the sum of the thrust force at the outlet of the nozzle ( 108) and the tensile and suction force of the aerobic fluid stream (106) at the inlet of the bypass (109) and in that the use of hollow nozzles in the diverging portion constitutes a converter of thermal energy into kinetic energy.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic type motor, characterized in that the outlet nozzle devices (103) of the combustion chamber, the aerobic and / or anaerobic central propulsion device (101), also called an aerobic and / or anaerobic motor, and a general exhaust nozzle (108) of the aerobic and / or anaerobic propulsion device, also called a motor of the type aerobic and / or anaerobic, are of the "Laval nozzle" type and in that the general outlet nozzle (108) of Laval nozzle type has a profile which is in the extension of the nozzle (103), too, of the Laval nozzle type located upstream of the nozzle (108) and characterized in that the neck of the general outlet nozzle (108) has a cross section greater than or equal to the outlet section of the nozzle (103) and in the outlet section of the nozzle (103) corresponds to the exit section of the neck of the outlet nozzle (108) allowing a particular operation in that the nozzle (103) is nested in the nozzle (108) in a manner that very precise and such that the hot combustion gases from the nozzle (103) can under no circumstances be influenced by the convergent portion of the nozzle (108) and even less that the influence of the neck of the nozzle nozzle (108) so that in this particular case the hot combustion gases of the nozzle (103) have a supersonic or hypersonic velocity that they maintain at the inlet of the diverging nozzle (108) and are then accelerated a second once in supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, by exaltation of hot combustion gases by means of the aerobic fluid vein (106) thus allowing the generation of a supersonic flow o u hypersonic whose physical phenomenon is permanent and continuous and characterized in that the by-pass system object of the invention provides a significant thrust gain of a coefficient greater than one up to three and more.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic type motor, characterized in that the propulsion device comprises at least one or a plurality of bypass systems. .

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises a system for aerobic and / or anaerobic propulsion. aerobic bypass consisting of an outer casing (107) having at least one inlet of the bypass (109) of the aerobic fluid vein (106) circulating in the bypass and provided with a single nozzle or several nozzles general output (108).

The present invention also aims at producing an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as technical characteristics additional one or a plurality of modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid stream (106) circulating in the outer casing (107) of the bypass for modulating the mass flow of the aerobic fluid stream (106) by creating an asymmetric flow in the general outlet nozzle (108).

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as a technical feature additional one or a plurality of modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid vein (106) circulating in the housing (107) of the bypass serving for guiding the system and the whole powered.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as a technical feature additional that the use of the modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid stream (106) circulating in the housing (107) of the bypass, is adapted to the flight conditions and the route traveled.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises a system for aerobic and / or anaerobic propulsion. by-pass generally consisting of one or more elements thus defining one or a plurality of orifices at the level of the fluid inlet at the inlet of the bypass (109), this or these elements joining together then to form a supersonic or hypersonic dilution zone (104) operating at supersonic or hypersonic conditions, common to a nozzle or a plurality of general exit nozzles (108).

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least four ports defining at least four aerobic fluid veins (106) uniformly distributed over the circumference of the propulsion (101) which then join to form a supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, common to a nozzle or a plurality of general exit nozzles (108).

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises a plurality of jet nozzles. Laval arranged in the aerobic fluid vein (s) (106) circulating in the bypass casing (107) and located upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the nozzle general output (108).

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is intended to be used to propel a torpedo or a boat into water or water, and in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is intended to be used to propel into the atmosphere a missile, rocket, boosters, aircraft, spacecraft or space vehicle, space shuttle or intercontinental strategic ballistic missile, propulsion systems and assemblies, aerobic propulsion device and / or or anaerobic, also called aerobic and / or anaerobic propulsion engine with a very strong thrust in the launch phase at takeoff or in the ascension phase in the atmosphere, which makes it possible to obtain a significant increase in the acceleration and the rate of climb, the radius of action, the range and / or the payload, and that in the case the propulsion of an intercontinental strategic ballistic missile to allow it then to pass instantaneously, by the dropping of the first stage and the by-pass, the mode of aerobic and / or anaerobic propulsion to the mode of "anaerobic" propulsion by the fire of the second stage then of the third floor thus ensuring a continuity of the thrust in the atmosphere and the exit of the dense layers of the atmosphere. The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, can be assembled alone. or in series thus constituting at least two or a plurality of stages with aerobic and / or anaerobic propulsion for propelling a system and / or an assembly comprising such a device.

The present invention also aims to provide an aerobic and / or anaerobic propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, can be assembled alone. or in parallel and in that the assemblies thus formed can be assembled, for example, to form at least one cluster assembly, to propel a system and / or an assembly comprising such a device.

The present invention also aims to provide an aerobic and / or anaerobic type propulsion device, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, constituting assemblies of aerobic and / or anaerobic type. series which can in turn be assembled in parallel and in that the assemblies thus formed can be assembled, for example, to form a cluster assembly, to propel a system and / or an assembly comprising such a device.

The present invention also aims at providing an aerobic and / or anaerobic propulsion device, characterized in that the said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is intended to provide an aerobic and / or anaerobic propulsion device. significantly increase the thrust and eliminate all the above disadvantages and achieve an aerobic and / or anaerobic propulsion engine having remarkable characteristics of having a significant thrust that can be modulated far beyond the state of the art current and in that the kinetic energy of the ejected gases is significant resulting in a very large thrust force, very high sound velocities at the neck of at least one nozzle and which depend on the intrinsic properties of the fluid, very high pressure and mass flow rates in at least one combustion chamber, also known as a propulsion chamber, and in that said aerobic and / or anaerobic propulsion engine has high flame temperature levels, and increased resistance of the materials constituting the walls of at least one combustion chamber also called propulsion chamber and materials constituting the walls of at least one thrust nozzle of the propulsion gases.

The present invention aims to provide a motor with aerobic and / or anaerobic propulsion characterized in that said aerobic and / or anaerobic propulsion motor (101) is composed of at least one combustion chamber (102), fed with solid propellants. or liquids, also known as the propulsion or propulsion chamber of said aerobic and / or anaerobic propulsion engine (101), delimited by the walls of at least one nozzle (103), and in that at the periphery of at least one chamber (102) are provided fluid injection systems (111), allowing the confinement of the seat of the combustion of the propellants so that the injection of the rare gas fluid surrounding the flame is between said flame and the wall of said combustion chamber so that the walls are cooled and protected from oxidation and corrosion phenomena, noble or noble gases being chemically inert, and that the injected fluid melanates downstream of at least one combustion chamber in a dilution zone (113) located upstream of the neck of at least one nozzle (103), and in that the gas mixture, consisting of exalted hot combustion gases by the rare gas fluid injected by the injection system (111), having intrinsic characteristics improved with respect to the intrinsic characteristics of the burned gases alone, or being relaxed in the downstream part (105) of at least one outlet nozzle ( 103) of the combustion chamber, accelerating said gas mixture to the free outlet of said at least one outlet nozzle (103) of the combustion chamber and that the fluid injected in the presence of the seat of the combustion changes of physical state by passing from the liquid state to the gaseous state making it possible to significantly increase the thrust according to three processes, knowing that the space propulsion as it is practiced today only converts a very small part from thermal energy to kinetic energy of thrust, consists in acting as a thermal energy converter in kinetic energy increasing the thrust and in that the first process consists of transferring part of the thermal energy of the combustion to the injected fluid, the second process consists in improving the intrinsic qualities of the fluid medium thus constituted, namely, the increase in its density and the increase in its velocity. its level at the neck of the nozzle Laval (103) and in that the third process consists in relaxing the fluid medium passing through the throat of the nozzle (103) allowing the acceleration of said fluid in the divergent portion of the nozzle ( 103) and thus convert a larger portion of the thermal energy of the fluid stream into kinetic energy, with higher energy efficiency compared to the simple use of propellants, resulting in an increase in speed and thrust, because the mass flow is increased, which now makes it possible to operate the combustion chambers close to the stoichiometric mixture of the propellants avoiding to force the gas amber combustion of oxygen to increase the mass flow which has the effect of amplifying the phenomena of oxidation and corrosion.

The present invention also aims to provide an aerobic and / or anaerobic propulsion engine characterized in that said aerobic and / or anaerobic propulsion motor (101) is composed of a plurality of inclined fluid injection systems (114). in relation to and towards the axis (112) of the nozzle (103) and arranged on at least one ring at the walls of at least one outlet nozzle (103) of the combustion chamber preceding the neck of the nozzle ( 103), and in that the injected fluid varies, by modulating its injection pressure and its flow rate, the neck section of at least one nozzle (103) by modifying the flow lines of the fluid resulting from at least one combustion chamber (102) of said anaerobic motor (101), and in that the modulation of the nozzle neck section (103) varies the ratio of the neck section of said nozzle to the section output of the divergent portion of the nozzle (103) Laval type and in c e that the smaller the ratio, the greater the ejection velocity of the gases in the outlet section is important, considering that the fluid is not over expanded at the outlet of the nozzle (103), and that the thermal transfer of the gas makes it possible to exalt the kinetic energy of the fluid medium ejected downstream of the nozzle (103), resulting in an increase in the mass flow rate and an increase in the total thrust, and in that the injection of the inert fluid allows to cool and protect the walls of the nozzle (103) oxidation and corrosion phenomena, rare or noble gases being chemically inert.

The present invention also aims to provide an aerobic and / or anaerobic propulsion engine characterized in that said aerobic and / or anaerobic propulsion engine (101) is composed of a plurality of fluid injection systems (115) arranged on at least one ring at the walls downstream of the neck of at least one nozzle (103), and in that the injected fluid serves to exalt the fluid coming from the neck of at least one nozzle (103), by modulation its injection pressure and its flow, resulting in a modulation of the mass flow ejected and accelerated at the outlet of said at least one nozzle (103), all operating and used to adapt the thrust of the anaerobic motor (101) at the different phases of flight, and in that the injected fluid is intended to maximize the thrust by directing the flow of gas ejected along the longitudinal axis (112) of at least one nozzle (103), and in that the injection of the inert fluid allows to refr oidir and protect the walls of the nozzle (103) oxidation and corrosion phenomena, rare or noble gases being chemically inert.

The present invention also aims to provide an aerobic propulsion engine characterized in that said aerobic propulsion device also called an aerobic propulsion engine has the additional feature that the fluid injection device (115) based on rare gas dense as for example the krypton, allows to increase the thrust by being associated or not with a system of post combustion and / or by-pass having as consequences and advantages an increase of autonomy, the radius of action, and of the maximum speed of the system and powered assembly comprising such a device such as for example a fighter jet, a drone, a reconnaissance aircraft, a space shuttle.

The present invention also aims at producing an aerobically and / or anaerobically propelled engine having the additional characteristic of having a wall that behaves like a mirror reflecting the thermal radiation in order to maximize the heat exchange by radiation between the different fluids, for example the hot gases of combustion and the injected fluid, and to minimize the absorption of thermal radiation by the wall of the nozzle.

The present invention also aims at producing an aerobically and / or anaerobically propelled engine (101) presenting as an additional characteristic the injection of dense "rare" gases, for example argon, krypton or xenon, also called "noble" gases. Dense or dense "inert" gases, for the exaltation of the hot combustion gases in order to modify the intrinsic characteristics of the fluid medium by increasing the density and the speed of sound of said fluid medium and in that the increase in said characteristics of the medium are derived from the intrinsic characteristics of the exaltation fluid knowing that the mid-sound velocity will also be increased by the temperature rises and that the characteristics can be greatly increased by a factor of two or more and that the present This invention makes it possible to achieve high velocity velocities at the neck of the nozzle (103) of Laval, with, for example, krypton, allowing acceptable combustion temperatures by the materials composing the walls of the combustion chamber (102) and the nozzle (103) thus allowing very high thrust engines pushing the current technological barriers.

The present invention also aims at producing an aerobically and / or anaerobically propelled engine (101) presenting as an additional characteristic the injection of "rare" gases, for example helium, also called "noble" gases or "inert" gases. , for the exaltation of hot combustion gases in order to modify their intrinsic characteristics by increasing the density and the sound velocity of the fluid medium.

The present invention also aims at producing an aerobically and / or anaerobically propelled engine (101) having the additional characteristic of having a combustion chamber (102) composed of at least one liquid propellant injector system having at least one axial and / or radial swirl to create a "swirl" movement, also called "swirl" movement, in the downstream flow of at least one injection system to promote the mixing of said liquid propellants. The present invention also aims to provide an aerobic and / or anaerobic propulsion motor (101) having the additional characteristic of having fluid injector systems (111, 114, 115) having at least one axial and / or radial swirler. to create a "swirl" movement, also called "swirl" movement, in the downstream flow of at least one injector system to promote the mixing of the different fluids in the presence.

The present invention aims to provide a feed turbopump according to the invention whose object is to increase the thrust of the aerobic propulsion device and / or anaerobic also called aerobic and / or anaerobic propulsion engine and characterized in that said turbopump or a turbopump supply, balanced variable speed, the aerobic propulsion device and / or anaerobic also called aerobic and / or anaerobic propulsion engines and systems and propulsion systems comprising said turbopump.

The present invention aims to provide a feed turbopump according to the invention whose object is to increase the thrust of the aerobic propulsion device and / or anaerobic also called aerobic and / or anaerobic propulsion engine and characterized in that said turbopump either a variable speed balanced feed turbopump, an aerobic and / or anaerobic propulsion device also called aerobic and / or anaerobic propulsion engines and propulsion systems and assemblies comprising said turbopump and that said turbopump is balanced and that it has high service life, reliability, flow rate and / or pressure characteristics as well as mechanical drive power enabling the reliable operation of said turbopump at constant high speed or at variable speed and in that said turbopump comprises at least one or two pumps, or a plurality of pumps, with liquid fluid, composed e (s) of at least one stage or a plurality of stages associated in the latter case in series and / or in parallel, at least one or two turbines, or a plurality of turbines, gas or liquid fluid , composed (s) of at least one stage or a plurality of stages associated in the latter case in series and / or in parallel, a single common rotation shaft connected to said pumps and said turbines and characterized in that the resultant axial forces, caused by all the stages of the "turbine" function and the stages of the "pump" function, in the common rotation shaft is zero or almost zero and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero and in that that said turbopump comprises sufficient number of bearings and necessary for the proper functioning of said turbopump, and whatever the type of bearing used, and sealing means sufficient and necessary for the proper functioning of said turbopump and whatever the the type of sealing means used and in that said turbopump comprises turbines, of gas type or fluid type, whose inputs or admissions and the outputs or discharges on the body of the turbopump can be either of the radial type and / or of the axial type and / or of the tangential type and / or of the oblique type, in that the said turbopump possesses a number of pumps whose inlet or inlet and whose or turbulence on the body of the turbopump may be either of the radial type and / or of the axial type and / or of the tangential type and / or of the oblique type.

The present invention aims to provide a turbopump characterized in that said turbopump has the additional technical characteristic of being a turbopump supply, aerobic propulsion device and / or anaerobic also called aerobic propulsion motor and / or anaerobic at least one propellant, and / or at least one liquefied gas, and / or at least one liquid fluid and / or at least one cryogenic fluid, and that said turbopump is a feed turbopump. at least one combustion chamber also called propulsion chamber.

The present invention aims at producing a turbopump characterized in that said turbopump includes sufficient numbers of pulleys necessary for the proper operation of said turbopump and in that at least one of the paliers is a magnetic pallet.

The present invention aims to provide a turbopump characterized in that said turbopump comprises a plurality of turbines whose resultant forces is mainly of the tangential type in order to maximize the torque in the rotary shaft common to the pumps and turbines.

The present invention aims at producing a turbopump characterized in that said turbopump comprises a plurality of axial screw feed pumps with helical screws with constant or variable geometric thread and / or cylindrical geometry and / or conical geometry and / or frustoconical geometry.

The present invention aims to provide a turbopump characterized in that said turbopump comprises a plurality of liquid fluid pumps and a plurality of turbines having the same rotation shaft in common, and in that said turbopump can simultaneously pump two liquid fluids and / or two propellants of different chemical nature, such as for example dioxygen and dihydrogen or alternatively dioxygen and kerosene, irrespective of the type of kerosene, thus ensuring the stability of the ratio of the mixture of the two propellants in at least one chamber of propulsion, each plurality of pumps being for example separated and disposed on either side of one or a plurality of turbines grouped in this case near the central axis of symmetry of said turbopump.

The present invention aims to provide a turbopump characterized in that said turbopump comprises at least one or two turbines, or a plurality of gas turbines fed in parallel from a single gas generator or a plurality of gas generators having the same characteristics and whose pressure losses in each pipe of the function "input or admission turbine" are strictly distributed and identical, these being located between the gas generator (s) and the inlet of each turbine, a part of the pipes that can be common to a plurality of gas turbines, the same principle being applied for the circuits of the function "exhaust or turbine exhaust" of said turbines so that there is no imbalance of operation due to the different head losses and in that these principles also apply in the case of, for example, the oxygen turbopump of oxygen pumps and comprising liquid dihydrogen turbines fed from the very high pressure liquid dihydrogen taken at the outlet of the "pump" function of the hydrogen turbopump or generally in the case of at least two liquid fluids of different chemical nature.

The present invention aims at producing a turbopump and characterized in that said turbopump comprises a "pump" function. whose pressure losses in each pipe of the function "entry or admission", are strictly distributed and identical, and whose pressure losses in each pipe of the function "output or exhaust" are strictly distributed and identical so that there is no operating imbalance between the stages of the "pump" function of said turbopump due to the different head losses.

The present invention aims at producing a turbopump and characterized in that said turbopump comprises a "turbine" function, the pressure losses in each pipe of the function "inlet or intake", are strictly distributed and identical, and whose losses loads in each pipe of the function "output or exhaust" are strictly distributed and identical so that there is no operating imbalance between the stages of the "turbine" function of said turbopump due to different losses loads.

The present invention aims at producing a turbopump (1) and characterized in that said turbopump comprises, according to a possible industrial embodiment of FIG. 6, a pair of pumps (8) and (9), or a plurality of pumps, composed of stages (10) and (11) or of a plurality of stages, arranged near the axis of symmetry (24) of the turbopump, and whose inlet or inlet of radial type (23) and and / or tangential and / or oblique common pumps (8) and (9) terminating in a chamber (13) common intake to the two pumps (8) and (9), supplying the inputs (19) and (20) of pumps (8) and (9), which are of the axial type, and which are filled with a plurality of axial screw feed pumps with constant or variable geometric screw thread and / or with a cylindrical geometry and / or with a conical geometry and / or frustoconical geometry (12) and whose outlets or discharges (21) and (22) pumps (8) and (9) are of radial type and / or tangential and / or oblique and in that said turbopump comprises a pair of turbines (2) and (3) or a plurality of turbines composed of stages (4) and (5) or a plurality of stages and whose inlets (15) and (17) are of radial and / or tangential and / or oblique type and whose outlets or exhausts (16) and (18) of the turbines are of axial type respectively in an outlet chamber ( 25) and (26) and in that said turbopump comprises a single shaft (14) of rotation common to the pumps and turbines and characterized in that the resultant axial forces, caused by all turbines of the function "turbine" and all the pumps of the function "Pump", in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed , and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper functioning of said turbopump, and whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper functioning of said turbopump and this whatever the type of sealing means used.

The present invention aims at producing a turbopump (1) and characterized in that said turbopump comprises, according to another possible industrial embodiment of FIG. 7, a pair of turbines (2) and (3) or a plurality of compound turbines stages (4) and (5) or a plurality of stages arranged near the axis of symmetry (24) of the turbopump, and whose inputs or admissions (15) and (17) turbines are of type radial and / or tangential and / or oblique and in that the outlets or exhausts (16) and (18) of the turbines are of axial type and are performed respectively by an outlet chamber (25) and (26) opening into a common outlet chamber (27) opening onto one or more radial and / or tangential and / or oblique outlet manifolds (28) and that said turbopump comprises a pair of pumps (8) and (9) or a plurality pumps consisting of stages (10) and (11) or a plurality of stages and whose axial inlet or inlet of each pump (13) opens into an axial screw feeding pump with helical screws with a constant or variable geometric screw pitch and / or with a cylindrical geometry and / or with a conical geometry and / or with a frustoconical geometry (12) which feeds the inlet or axial inlet (19) and (20) of each pump respectively (8) and (9) and having stages (10) and (11), or a plurality of stages and in that the ups and downs or outlets (21) and (22) of the pumps (8) and (9) are of the radial and / or tangential and / or oblique type and in that said turbopump comprises a single common rotation shaft (14) connected to said pumps ( 8) and (9) and said turbines (2) and (3) and characterized in that the resultant axial forces, caused by all turbines of the "turbine" function and by all the pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper operation of the turbopump and this whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper operation of the turbopump and whatever the type of sealing means used.

The present invention aims to provide a turbopump characterized in that said turbopump has the additional feature of using composite materials.

The present invention aims to provide a turbopump characterized in that said turbopump has the additional feature of using thermo-structural materials.

The present invention aims to provide a turbopump characterized in that said turbopump has the additional feature of using ceramic materials.

The present invention aims to provide a turbopump characterized in that said turbopump is driven by at least one gas turbine and in that said gas is water vapor.

The present invention aims to provide a turbopump characterized in that said turbopump is driven by at least one electric motor in place of the drive by gas turbine or steam turbine.

The present invention aims to provide a turbopump power device characterized in that said turbopump relative to the field of turbopumps supply and in particular turbopumps supply aerobic and / or anaerobic propulsion device also called aerobic propulsion engines and / or anaerobic in rare gas type liquid fluid such as helium, neon, argon, krypton or xenon.

The present invention aims at producing a turbopump characterized in that said turbopump has the additional characteristic of being able to operate at a constant speed or at a speed variable by varying in the one or more gas turbines of said turbopump the mechanical power of driving gases produced by one or a plurality of gas generators.

The present invention aims at producing a turbopump (1) characterized in that said turbopump (1) has the characteristic of being able to operate at a constant speed and at variable speed and in that said turbopump (1), comprising a single rotation shaft ( 14) connected to the pumps (8) and (9) and to the turbines (2) and (3), has the additional feature of being able to vary the pressure, the speed of rotation and the flow rate of the said pumps (8) and ( 9) of said turbopump (1).

The present invention aims to provide a plurality of turbopumps characterized in that said set of plurality of turbopumps has the additional feature of being assembled so that the "pump" function of the plurality of turbopumps is mounted in series. to increase the pressure.

The present invention aims to provide a set of plurality of turbopumps and characterized in that said set of plurality of turbopumps has as an additional feature to be assembled so that the "pump" function of the p ururality of turbo pumps is paralleling to increase the flow.

The present invention aims to provide a set of plurality of turbopumps characterized in that said set of plurality of turbopumps has the additional features of being assembled so that the "pump" function of a plurality of turbopumps is in series to increase the pressure and in that the "pump" function of a plurality of turbopumps is mounted in parallel to increase the flow rate.

The object of the present invention is to provide a plurality of turbopumps and characterized in that the entire set of turbopumps is assembled in such a way that the respective turbines of each turbopump are connected in parallel and fed from a single pump. same gas generator or a plurality of gas generators having the same characteristics and in that said gas is produced from liquefied gas or liquid propellant or sol ide and / or liquid fluid. The present invention aims at producing aerobic and / or anaerobic propulsion engines characterized in that said engines comprise at least one combustion chamber also called propulsion chamber and at least one turbopump for supplying at least one liquid fluid. and / or at least one liquid propellant of said at least one combustion chamber also called propulsion chamber.

The present invention aims to provide systems and propelled assemblies characterized in that said systems and propulsion systems comprise at least one combustion chamber also called propulsion chamber and at least one turbopump, for the supply of a fluid to the fluid. liquid and at least one liquid propellant of the adite at least one combustion chamber also called propulsion chamber in that said systems and all the propulsion are rocket type, miss i le, aircraft, rocket plane, supersonic aircraft and / or hypersonic, drone, orbital plane or spacecraft, airplane or spaceship, intercontinental reconnaissance aircraft, intercontinental strategic bomber, and other systems and prop ul uls.

The present invention also aims to provide a turbopump supply in that said turbopump, although previously described and hereafter with reference to the diagrams of Figures 6 to 9 representing four industrial embodiments and possible architectures of the invention among all the other industrial embodiments and other possible architectures, and in that according to the invention, various modifications and changes can be made, in particular on the architectures described, without departing from the general scope of the invention such that defined in the description and in the claims, the drawings of Figures 6 to 9 to be considered in an illustrative rather than restrictive sense. The invention will be better understood on reading the nonlimiting industrial embodiments of the appended drawings which illustrate embodiments of the invention according to FIGS. 1 to 9.

The accompanying drawings illustrate the invention

Figure 1 shows one of the devices of the invention.

The object of the present invention is to provide, according to an industrial embodiment that is the subject of FIG. 1, an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion motor, which does not comprise an aerobic compression stage located at the inlet of the bypass device and disposed upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, and in that said propulsion device of the type aerobic and / or anaerobic, also called an aerobic and / or anaerobic propulsion engine comprises in the central part an aerobic and / or anaerobic propulsion device (101) with solid propellants or propellants having an aerobic and / or anaerobic combustion chamber (102) supplying upstream of an outlet nozzle (103) of the combustion chamber, the ejection of hot combustion gases in the supersonic or hypersonic mode is done in the downstream portion (105) of the outlet nozzle of the combustion chamber located downstream of the throat of the nozzle of the aerobic propulsion device and / or anaerobic, and that the aerobic and / or anaerobic propulsion device, called also aerobic and / or anaerobic propulsion engine comprises a bypass system consisting of an outer casing (107) defining an aerobic fluid vein (106) flowing between the outer casing (107) and the central body (101) of the engine aerobically and / or anaerobically propelled, and in that the ejection of hot combustion gases in supersonic or hypersonic mode occurring in the downstream portion (105) of the combustion chamber outlet nozzle generates a negative pressure at by-pass input (109), which then operates as a static vacuum cleaner by fluid drive, the bypass from the front of the systems and sets propelled to the rear thereof by creating a general outlet nozzle (108) such that the outlet nozzle (103) of the combustion chamber of the aerobic-type central propulsion device and / or anaerobically located inside the general outlet nozzle (108), and in that said aerobic and / or anaerobic propulsion motor comprises a general outlet nozzle (108) which receives the hot combustion gases from the outlet nozzle (103) of the combustion chamber of the aerobically and / or anaerobically propelled engine and which ensures the supersonic or hypersonic dilution of said hot combustion gases, the thermal exchange expansion and the supersonic or hypersonic expansion of the fluid stream aerobic (106) derived from the bypass and at the exit thereof in the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the downstream of the outlet nozzle (103) of the combustion chamber which generates a pressure difference between the inlet (109) in the bypass depression and its output operating in supersonic or hypersonic mode, all resulting in an increase in significant mass flow ejected at the outlet of the general outlet nozzle (108), the thrust and the ejection speed at the outlet of the general outlet nozzle (108), and in that the depression force generated at the inlet (109) of the bypass contributes to improving the aerodynamic performance of the propelled systems and assemblies by adding to the thrust force from the general exhaust nozzle (108), and in that the propulsion device, called also aerobic and / or anaerobic propulsion engine comprises a bypass (107) disposed over the entire length of the system and the propelled assembly thereof being provided with a general outlet nozzle (108), and in that the avail propellant, also called an aerobic and / or anaerobic propulsion engine, comprises at least one supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the general exhaust nozzle (108), followed by a or a plurality of general exit nozzles (108), and in that the aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises an anaerobic and / or aerobic motor provided with one or a plurality of combustion chambers (102) located upstream of at least one or a plurality of outlet nozzles (103) of at least one or a plurality of combustion chambers, and in that the outlet nozzle device (103) of the combustion chamber is provided, downstream of the neck of said nozzle (103), with devices for improving the dilution and the cooling of the outlet nozzle device (103) of the combustion chamber, such as, for example, that said devices for improving dilution and cooling consist of recesses in the wall of said nozzle (103), the device aerobic and / or anaerobic propulsion engine, also called an aerobic and / or anaerobic propulsion engine, and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises the outlet nozzle devices (103) of the combustion chamber of the central propulsion device (101) of the aerobic and / or anaerobic type, also called aerobic and / or anaerobic propulsion engine and of the general exhaust nozzle (108) of the propulsion device central (101) aerobic and / or anaerobic type, also called aerobic and / or anaerobic propulsion engine, are of the "Laval nozzle" type, and in that the propulsion device, also called aerobic propulsion engine and / or anaerobic comprises an aerobic bypass system composed of an outer casing (107) comprising at least one inlet of the bypass (109) of the aerobic fluid vein (106) circulating in the bypass and provided with an single nozzle or of several outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical characteristic one or a plurality of modulation means by partial or total blocking of the bypass entrances (109) of the aerobic fluid vein (106) and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical feature one or more modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid vein (106) for guiding the system and / or the propelled assembly and that the propulsion device, called also aerobic and / or anaerobic propulsion engine comprises as an additional technical feature that the use of modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid vein (106) is adapted to the flight conditions and the path traveled, and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises a system of by-pass generally consisting of one or more elements thus defining one or more orifices at the inlet of the fluid at the inlet of the bypass (109), where these elements then meet to form a common dilution zone (104) connected to a nozzle or to a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises at least four orifices; an inlet defining at least four aerobic fluid veins (106) uniformly distributed over the circumference of the propulsion device (101) and thereafter joining to form a supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, common to a nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises none or a plurality of Laval nozzles disposed in the at least one aerobic fluid stream (106) and located upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions.

Figure 2 shows one of the devices of the invention.

The object of the present invention is to provide, according to an industrial embodiment that is the subject of FIG. 2, an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, which does not comprise an aerobic compression stage located at the inlet of the bypass device and disposed upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, and in that said propulsion device of the type aerobic and / or anaerobic, also called aerobic and / or anaerobic propulsion engine comprises in the central part an aerobic propulsion device and / or anaerobic propellant (101) propellants or liquid propellants and / or rare-type liquid fluid having a chamber (102) aerobic and / or anaerobic and that said aerobic and / or anaerobic combustion chamber (102) is fed with an injection system (110). ) composed of at least one turbopump (1) and / or a plurality of turbopumps (1) supplying said combustion chamber (102) is made of liquid propellants or propellants and / or said aerobic and / or anaerobic combustion chamber (102) is fed with a liquid fluid injection system (111) at the periphery of said combustion chamber (102) and / or in that said outlet nozzle (103) of the aerobic and / or anaerobic combustion chamber is fed by means of an injection system (114) of fluid fluid located upstream of the neck of said outlet nozzle (103) and / or in that said exhaust nozzle (103) of the aerobic and / or anaerobic combustion chamber is fed with a system of injection (115) of liquid fluid located downstream of the neck of said outlet nozzle (103), the total gas flow of which feeds at least one outlet nozzle (103) of the combustion chamber and whose ejection of the gases in supersonic or hypersonic mode is done in the downstream part (105) of the outlet nozzle of the chamber d e combustion located downstream of the nozzle neck of the aerobic propulsion device and / or anaerobic, and in that the aerobic and / or anaerobic propulsion device, also called aerobic and / or anaerobic propulsion engine comprises a system of aerobic and / or anaerobic propulsion. bypass comprising an outer casing (107) defining an aerobic fluid vein (106) circulating between the outer casing (107) and the central body (101) of the aerobically and / or anaerobically propelled motor, and in that supersonic or hypersonic gas ejection occurring in the downstream portion (105) of the outlet nozzle of the combustion chamber generates a vacuum at the inlet of the bypass (109), which then functions as a static vacuum cleaner by fluid drive, the bypass from the front of the propelled systems and assemblies to the rear thereof by creating a general outlet nozzle (108) so that the outlet nozzle (103) ) of the combustion chamber of the aerobic and / or anaerobic central propulsion device is located inside the general outlet nozzle (108), and in that said aerobic and / or anaerobic propulsion motor comprises a general outlet nozzle ( 108) which receives the gases from the exhaust nozzle (103) of the combustion chamber of the aerobically and / or anaerobically propelled engine and which ensures the supersonic or hypersonic dilution of said gases, the thermal exchange expansion and the supersonic expansion or hypersonic of the aerobic fluid vein (106) from the bypass and at the outlet thereof in the dilution zone (104), supersonic or hypersonic operating under supersonic or hypersonic conditions, located in the downstream portion of the outlet nozzle (103) of the combustion chamber which generates a pressure difference between the inlet (109) in the bypass depression and its operating outlet in supersonic or hypersonic mode, all resulting in a significant increase in the mass flow ejected at the outlet of the general exhaust nozzle (108), the thrust and the ejection speed at the outlet of the general exhaust nozzle ( 108), and in that the depression force generated at the inlet (109) of the bypass contributes to improving the aerodynamic performance of the systems and assemblies propelled by adding to the thrust force from the general exhaust nozzle ( 108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises a bypass (107) arranged over the entire length of the system and the assembly. it is powered by a general exhaust nozzle (108), and the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least one dilution zone (104), supersonic or hypersonic operating under supersonic or hypersonic conditions, located in the general exhaust nozzle (108), followed by one or a plurality of general exhaust nozzles (108), and in that the aerobic and / or anaerobic propulsion device , also referred to as an aerobic and / or anaerobic propulsion motor, includes an anaerobic and / or aerobic motor provided with at least one or a plurality of combustion chambers (102) located upstream of at least one or a plurality of outlet nozzles (103) at least one or a plurality of combustion chambers, and in that the outlet nozzle device (103) of the combustion chamber is provided, downstream of the neck of said nozzle (103), of devices to improve the dilution and cooling of the outlet nozzle device (103) of the combustion chamber, such as, for example, that said devices for improving the dilution and the cooling consist of recesses in the wall of said nozzle (103), an aerobic and / or anaerobic propulsion device, also referred to as an aerobic and / or anaerobic propulsion engine, and in that the propulsion device, also referred to as an aerobic and / or anaerobic propulsion engine, comprises the exhaust nozzle devices (103) of the combustion chamber of the central propulsion device (101) of aerobic and / or anaerobic type, also called a propulsion motor aerobic and / or anaerobic and general outlet nozzle (108) of the aerobic and / or anaerobic central propulsion device (101), also called an aerobic and / or anaerobic propulsion engine, are of the "Laval nozzle" type, and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises an aerobic bypass system composed of an outer casing (107) comprising at least one inlet of the bypass (109) of the aerobic fluid vein (106) circulating in the bypass and provided with a single nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic propulsion motor and / or anaerobic comprises, as an additional technical feature, one or a plurality of modulation means by partial or total closure of the bypass entrances (109) of the aerobic fluid vein (106) and in that the propulsion device, also called a propulsion motor; aerobic and / or anaerobic comprises, as additional technical feature, one or a plurality of modulation means by partial or total closure of the bypass entrances (109) of the aerobic fluid vein (106) serving for guiding the system and / or the propelled assembly and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises as an additional technical feature that the use of the modulation means by partial or total closure of the bypass entries (109) the aerobic fluid vein (106) is adapted to the flight conditions and the path traveled, and the propulsion device, also referred to as the aerobic and / or anaerobic propulsion engine, comprises a one-way bypass system. general of one or more elements thus defining one or more orifices at the inlet of fluid at the inlet of the bypass (109), this or these elements is re then joining to form a common dilution zone (104) connected to a nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least four intake orifices defining at least four aerobic fluid veins (106) uniformly distributed over the circumference of the propulsion device (101) and then joining to form a supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions , common connected to a nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises no Laval nozzle or nozzles arranged in the aerobic fluid vein (s) (106) and located upstream of the dilution zone (104), supersonic or hypersonic operating under supersonic or hypersonic conditions.

FIG. 3 represents one of the devices of the invention. The present invention aims to achieve, according to an industrial embodiment in the subject of Figure 3, a motor with aerobic propulsion and / or anaerobic characterized in that said engine with aerobic propulsion and / or anaerobic (101) is composed of at least one combustion chamber (102), supplied with solid or liquid propellants, also called the propulsion or propulsion chamber of said aerobic and / or anaerobic propulsion engine (101), delimited by the walls of at least one nozzle (103); ), and in that at the periphery of at least one combustion chamber (102) are arranged fluid injection systems (111), allowing the confinement of the combustion seat of the propellants so that the injection of rare gas fluid surrounding the flame is located between said flame and the wall of said combustion chamber so that the walls are cooled and protected from oxidation and corrosion phenomena, noble gases or no being chemically inert, and that the injected fluid mixes downstream of at least one combustion chamber in a dilution zone (113) located upstream of the neck of at least one nozzle (103), and in that that the mixture of gases, consisting of the hot combustion gases exalted by the rare gas fluid injected by the injection system (111), having intrinsic characteristics improved with respect to the intrinsic characteristics of the burned gases alone, is relaxed in the part downstream (105) of at least one outlet nozzle (103) of the combustion chamber, accelerating said gas mixture to the free outlet of said at least one outlet nozzle (103) of the combustion chamber and what the fluid injected in the presence of the seat of the combustion changes of physical state by passing from the liquid state to the gaseous state making it possible to increase significantly the thrust following three processes, knowing that the space propulsion tell e that it is practiced today only converts a very small part of the thermal energy into kinetic energy of thrust, consists in acting as a thermal energy converter in kinetic energy increasing the thrust and in that the first process consists in transferring part of the thermal energy of the combustion to the injected fluid, the second process consists in improving the intrinsic qualities of the fluid medium thus constituted, namely, the increase in its density and the increase in its velocity of the sound at the neck of the Laval nozzle (103) and in that the third process consists in relaxing the fluid medium passing through the neck of the nozzle (103) allowing the acceleration of said fluid in the diverging portion of the nozzle (103) and thus converting a larger portion of the thermal energy of the fluid stream into kinetic energy, with higher energy efficiency compared to the simple use of propellants, resulting in an increase in speed and thrust, because the mass flow is increased, which now allows to operate the combustion chambers near the stoichiometric mixture of propellants avoiding to force the combustion chamber into oxygen to increase the mass flow, which has the effect of amplifying the oxidation and corrosion phenomena.

FIG. 4 represents one of the devices of the invention. The present invention also aims at producing, according to an industrial embodiment in the subject of FIG. 4, an aerobic and / or anaerobic propulsion engine characterized in that said aerobic and / or anaerobic propulsion engine (101) is composed of a plurality of fluid injection systems (114) inclined relative to and toward the axis (112) of the nozzle (103) and disposed on at least one ring at the walls of at least one nozzle (103). ) of the outlet of the combustion chamber preceding the neck of the nozzle (103), and in that the injected fluid varies, by modulation of its injection pressure and its flow, the neck section of at least one nozzle (103) by modifying the fluid flow lines from at least one combustion chamber (102) of said anaerobic motor (101), and that the modulation of the section of the neck of the nozzle (103) varies the ratio of the neck section of said nozzle relative to the outlet section of the diverging portion of the nozzle (103) type Laval and in that the ratio is smaller the higher the ejection velocity of the gases in the outlet section, considering that the fluid is not overpressured at the outlet of the nozzle (103), and in that the thermal transfer of the gases makes it possible to exalt the kinetic energy of the fluid medium ejected downstream of the nozzle (103) resulting in an increase in the mass flow and an increase in the total thrust, and in that the injection of the inert fluid allows to cool and protect the walls of the tuyère (103) of oxidation and corrosion phenomena, noble or noble gases being chemically inert.

Figure 5 shows one of the devices of the invention.

The present invention also aims at carrying out, according to an industrial embodiment in the subject of FIG. 5, an engine with aerobic and / or anaerobic propulsion characterized in that said aerobic and / or anaerobic propulsion engine (101) is composed of a plurality of fluid injection systems (115) disposed on at least one ring at the walls downstream of the neck of at least one nozzle (103), and in that the injected fluid serves to exalt the fluid from the neck of at least one nozzle (103), by modulating its injection pressure and its flow rate, resulting in a modulation of the mass flow ejected and accelerated at the outlet of said at least one nozzle (103), all operating and used to adapt the thrust of the anaerobic motor (101) to the different phases of flight, and in that the injected fluid is intended to maximize the thrust by directing the flow of gas ejected along the longitudinal axis (112) at least one e nozzle (103), and in that the injection of the inert fluid allows to cool and protect the walls of the nozzle (103) oxidation and corrosion phenomena, rare or noble gases being chemically inert.

Figure 6 shows one of the devices of the invention. FIG. 6 represents an industrial embodiment according to a possible architecture of the turbopump feed device object of the invention.

The present invention also aims to provide a turbopump (1) characterized in that said turbopump comprises, according to a possible industrial embodiment of Figure 6, a pair of pumps (8) and (9), or a plurality of pumps, composed of stages (10) and (11) or of a plurality of stages, arranged near the axis of symmetry (24) of the turbopump, and whose inlet or inlet of radial type (23) and and / or tangential and / or oblique common pumps (8) and (9) terminating in a chamber (13) common intake to the two pumps (8) and (9), supplying the inputs (19) and (20) of pumps (8) and (9), which are of the axial type, and which are filled with a plurality of axial screw feed pumps with constant or variable geometric screw thread and / or with a cylindrical geometry and / or with a conical geometry and / or frustoconical geometry (12) and whose outputs or discharges (21) and (22) pumps (8) and (9) are of type radial and / or tangential and / or oblique and in that said turbopump comprises a pair of turbines (2) and (3) or a plurality of turbines composed of stages (4) and (5) or a plurality of stages and whose inlets (15) and (17) are of radial and / or tangential and / or oblique type and whose outlets or exhausts (16) and (18) of the turbines are of axial type respectively in an outlet chamber (25) and (26) and in that said turbopump comprises a single shaft (14) of rotation common to the pumps and turbines and characterized in that the resultant axial forces, caused by all the turbines of the function " turbine "and by all the pumps of the" pump "function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper functioning of said turbopump, and whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper functioning of said turbopump and this whatever the type of sealing means used. Figure 7 shows one of the devices of the invention.

FIG. 7 represents another possible industrial embodiment according to another possible architecture of the turbopump feed device object of the invention.

The present invention also aims at producing a turbopump

(1) characterized in that said turbopump comprises, according to a possible industrial embodiment of FIG. 7, a pair of turbines

(2) and (3) or a plurality of turbines composed of the stages (4) and (5) or a plurality of stages disposed near the axis of symmetry (24) of the turbopump, and whose inputs or admissions (15) and (17) of the turbines are of the radial and / or tangential and / or oblique type and in that the outlets or exhausts (16) and (18) of the turbines are of the axial type and are carried out respectively by a outlet chamber (25) and (26) opening into a common outlet chamber (27) opening onto one or more outlet manifolds (28) of radial and / or tangential and / or oblique type and in that said turbopump comprises a pair of pumps (8) and (9) or a plurality of pumps consisting of stages (10) and (11) or a plurality of stages and whose axial inlet or inlet of each pump (13) opens into a Axial screw feed pump with helical screws with constant or variable geometric thread and / or with cylindrical and / or geometric geometry conical and / or frustoconical geometry (12) which feeds the inlet or axial inlet (19) and (20) of each pump respectively (8) and (9) and comprising stages (10) and (11), or a plurality of stages and in that the ups and downs (21) and (22) of the pumps (8) and (9) are of radial and / or tangential and / or oblique type and in that said turbopump comprises a single rotating shaft (14) common to said pumps (8) and (9) and said turbines (2) and (3) and characterized in that the resultant axial forces, caused by all the turbines of the function "Turbine" and by all pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper operation of the turbopump and whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper operation of the turbopump and whatever the type of sealing means used. Figure 8 shows one of the devices of the invention.

FIG. 8 represents another possible industrial embodiment according to another possible architecture of the turbopump device of object of the invention.

The present invention also aims at producing a turbopump

(1) characterized in that said turbopump comprises, according to a possible industrial embodiment of FIG. 8, a pair of turbines

(2) and (3) or a plurality of turbines composed of the stages (4) and (5) or a plurality of stages of the turbopump, and whose inputs or admissions (15) and (17) turbines are of radial and / or tangential and / or oblique type and in that the outlets or exhausts (16) and (18) of the turbines are of axial type and are carried out respectively by an outlet chamber (25) and (26) opening in a common outlet chamber (27) opening on one or more radial and / or tangential and / or oblique outlet manifolds (28) and in that said turbopump comprises a pair of pumps (8) and (9) or a plurality of pumps composed of the stages (10) and (11) or of a plurality of stages and whose inlet or inlet (23) of radial and / or tangential and / or oblique type common to the pumps (8) and (9) terminating in a common inlet chamber (13) to the two pumps (8) and (9) supplying the inlets (19) and (20) of the pumps (8) and (9) which are the axial type and which are filled with a plurality of axial helical screw feeding pumps with constant or variable geometric screw pitch and / or with a cylindrical geometry and / or with a conical geometry and / or with a frustoconical geometry (12) which feeds the axial admission (19) and (20) of each pump respectively (8) and (9) and comprising stages (10) and (11), or a plurality of stages and in that the ups and downs ( 21) and (22) pumps (8) and (9) are of radial and / or tangential and / or oblique type and in that said turbopump comprises a single common rotation shaft (14) connected to said pumps (8) and (9) and said turbines (2) and (3) and characterized in that the resultant axial forces, caused by all turbines of the "turbine" function and by all pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and 7 or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper operation of the turbopump and this whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper operation of the turbopump and whatever the type of sealing means used.

Figure 9 shows one of the devices of the invention.

FIG. 9 represents another possible industrial embodiment according to another possible architecture of the feed turbopump device which is the subject of the invention.

The present invention also aims at producing a turbopump

(I) characterized in that said turbopump comprises, according to a possible industrial embodiment of FIG. 9, a pair of turbines (2) and (3) or a plurality of turbines composed of stages (4) and (5) or a plurality of stages whose inputs or admissions (15) and (17) of the turbines are of the radial and / or tangential and / or oblique type and in that the outlets or exhausts (16) and (18) of the turbines are of axial type and are effected respectively by an outlet chamber (25) and (26) opening into a common outlet chamber (27) opening onto one or more radial and / or tangential outlet manifolds (28) and / or oblique and in that said turbopump comprises a pair of pumps (8) and (9) or a plurality of pumps composed of stages (10) and

(II) or a plurality of stages and whose axial inlet or inlet of each pump (13), resulting from the two admissions (30) of the radial type and / or tangential and / or oblique, opens into a pump of axial feed with helical screw with constant or variable geometric screw pitch and / or cylindrical geometry and / or conical geometry and / or frustoconical geometry (12) which feeds the inlet or axial inlet (19) and (20) of each pump respectively (8) and (9) and having stages (10) and (11), or a plurality of stages and in that the discharge or outlet, also known as the outlet manifold (29) of the pumps (8) and (9) are of radial and / or tangential and / or oblique type and in that said turbopump comprises a single common rotation shaft (14) connected to said pumps ( 8) and (9) and said turbines (2) and (3) and characterized in that the resultant axial forces, caused by all turbines of the "turbine" function and by all the pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant speed or variable, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper functioning of the turbopump and whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper functioning of the turbopump and that whatever the t ype of sealing medium used.

Claims

1. Combined aerobic and / or anaerobic propulsion device of combined and simultaneous type in continuous operation and propulsion systems and assemblies comprising such a device and characterized in that the device has a combined and simultaneous type of continuous operation and in that that the statement "presents a continuous operation of combined and simultaneous type" defines an additional characteristic defining the device itself and not the manner in which the device is operated and that said device makes it possible to increase the thrust relative to to the state of the art today, and in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is equipped on the one hand with systems for aerobic and / or anaerobic propulsion. By-pass or "bypass" and / or in that the aerobic and / or anaerobic propulsion engine is equipped with turbopumps improved characteristics resulting in an increase in mass flow and thrust for liquid propellant engines and / or in that the mass flow of said engines is adapted to the conditions and the flight path by the use of at least one propellant with at least one cryogenic liquid fluid of the rare gas type, thus making it possible to vary the thrust continuously by controlling the speed of rotation of the turbopump and the mass flow rates injected into said engine and thus to adapt the thrust to the conditions and the flight time of the system or systems and propulsion systems comprising such a device and in that said balanced turbopumps having a resultant zero or almost zero axial forces can generate propellant and / or fluid supply pressure flow torques liquid propulsion device allowing pressures in the combustion chamber ranging from 20 to 100 mega pascal s and more and in that the rare gas injection systems used to increase the thrust (111), (114) and (115) are used in addition to the bypass in the Earth or Mars take-off phase, are used then to compensate for the thrust of the bypass system due to altitude rise and the consequent decrease in the density of the air or the atmosphere whether terrestrial or Martian or still used to obtain an aerobic and / or anaerobic propulsion device with variable thrust in the absence of atmosphere in the "void" as for example in the moon landing or takeoff phases, or in conjunction with the bypass system in the case of a "marshalling" or take-off on Mars , and in that the bypass system associated with the rare gas injection constitutes a thermal energy converter into kinetic energy resulting in the increase of the total thrust, and in that said aerobic propulsion device and / or anaerobic, also called aerobic and / or anaerobic propulsion engine, is characterized by a very significant increase in thrust and in that said engine does not have an "aerobic" compression stage located at the entrance of the engine. positive by-pass and disposed upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, knowing that a dilution consists of the addition of a first fluid composed of the aerobic fluid vein of the by-pass to a second fluid composed of the hot combustion gases in order to reduce the concentration of this second fluid consisting of said hot combustion gases and in that said aerobic and / or anaerobic propulsion device, also called an aerobic propulsion engine and / or anaerobically, comprises in the central part an aerobic and / or anaerobic propulsion device (101) using at least one solid or liquid propellant and / or a rare-type liquid fluid and in that said at least one liquid propellant and and / or a rare-gas type liquid fluid are injected upstream of the neck of the nozzle (103) into at least one combustion chamber (102) and / or downstream of the neck of the nozzle (103) using at least one feed system composed of at least one feed turbopump, this being part of the invention and in that the propulsion device has at least one aerobic and / or anaerobic combustion chamber (102). ) which generates hot combustion gases supplying upstream of an outlet nozzle (103) of the combustion chamber, the ejection of hot combustion gases in supersonic mode or hypersonic is in the downstream portion (105) of the outlet nozzle of the combustion chamber located downstream of the throat of the nozzle of the aerobic and / or anaerobic propulsion device, and that the aerobic propulsion device and or anaerobic, also called aerobic and / or anaerobic propulsion engine includes a bypass system consisting of an outer casing (107) defining an aerobic fluid vein (106) flowing between the outer casing (107) and the central body of the aerobic and / or anaerobic propulsion device (101) and in that the ejection of the hot combustion gases in supersonic or hypersonic mode occurring in the downstream part (105) of the combustion chamber outlet nozzle generates a vacuum at the inlet of the bypass (109) which operates as a static vacuum cleaner by fluid drive, the bypass from the front of the system and / or the propelled assembly to the rear of this one by creating a general outlet nozzle (108) such that the outlet nozzle (103) of the combustion chamber of the aerobic and / or anaerobic central propulsion device is located inside the general outlet nozzle (108) , and in that said "aerobic and / or anaerobic" type propulsion device, also called an "aerobic and / or anaerobic" propulsion engine, comprises a general outlet nozzle (108) which receives the hot combustion gases from the outlet nozzle (103) of the combustion chamber of the aerobically and / or anaerobically propelled engine and which ensures the supersonic or hypersonic dilution of said hot combustion gases, the thermal exchange expansion and the supersonic or hypersonic expansion of the fluid stream aerobic (106) derived from and leaving the bypass in the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the downstream portion of the outlet nozzle (103) of the combustion chamber which creates a pressure difference between the inlet depression of the bypass (109) and its output operating in supersonic or hypersonic mode, all resulting in a significant increase in the mass flow ejected at the outlet of the general outlet nozzle (108), the thrust and the ejection speed at the outlet of the general nozzle output (108), and in that the depression force generated at the inlet (109) of the bypass contributes to improving the aerodynamic performance of the systems and assemblies propelled by adding to the thrust force from the general nozzle (108) and that said "aerobic and / or anaerobic" type propulsion device having one of its essential characteristics is to operate using the capacity of a fluid stream to flow when it is subjected to applying a force resulting from the driving ability of a moving layer on the other adjacent layers knowing that the movement of the aerobic fluid vein (106) in the bypass can be considered as resulting from the slippage fluid layers on each other and in that the aerobic fluid vein (106) is subjected to a pressure difference between the bypass inlet and the supersonic or hyper dilution zone (104). Sonic operating under supersonic or hypersonic conditions, resulting in entrainment of the aerobic fluid vein (106) in the bypass and in that one of the other essential features is that the fluid entrainment is effected from a zone Supersonic or hypersonic supersonic or hypersonic dilution device (104), creating a permanent fluid drive from supersonic or hypersonic conditions of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, and not from subsonic conditions and in that one of the other essential characteristics is that the bypass feeds a supersonic or hypersonic dilution zone generated by the dilution of the hot combustion gases from a Laval nozzle (103) creating a vein supersonic or hypersonic fluid mixing with the aerobic fluid vein (106) of the bypass, it also if in supersonic or hypersonic mode thus carrying out a supersonic or hypersonic dilution in a dilution zone and whose essential characteristic is that this dilution zone opens downstream of the outlet of the Laval nozzle (103) from which the hot gases of combustion in a general outlet nozzle (108), the profile of which is in the extension of the nozzle (103) of upstream Laval and characterized in that the section of the beginning of the divergent of the general outlet nozzle (108) has a section equal to or greater than the outlet section of the nozzle (103) thus allowing a particular operation in that the nozzle (103) is nested in the nozzle (108) precisely and in such a way that the hot combustion gases at the outlet of the nozzle (103) have a supersonic or hypersonic velocity which they retain at the beginning section diverging from the general outlet nozzle (108) and which are then accelerated a second time by the dilution in the diverging portion of the nozzle (108), thus allowing the generation of a continuous and continuous supersonic or hypersonic flow characterized in that that the by-pass system object of the invention provides a significant thrust gain of a coefficient greater than one and up to three and more and in that the nozzle (103) and the vein aerobic uide (106) does not supply another combustion chamber or a subsonic dilution zone that would be located, for example, upstream of the neck of a Laval nozzle in subsonic or sonic mode and in that said dilution zone ( 104), supersonic or hypersonic operating under supersonic or hypersonic conditions, performs a dilution and exaltation of the hot combustion gases from the nozzle (103) and the aerobic fluid stream from the bypass by dilation and acceleration of the fluid stream resulting from the by-pass and in that this expansion is carried out simply by thermal exchanges by conduction, by convection and by thermal radiation and in that the aerobic fluid stream proceeds to exalt the hot combustion gases whose kinetic energy released from the absorption of a portion of the thermal energy of the hot combustion gases, on the one hand generates said fluid entrainment of the aerobic fluid vein (106) circulates in the bypass and also generates the increased thrust of the propulsion device, steady state and continuous type combined and simultaneous and that the device of the invention does not proceed from the principles of operation of the ramjets that have a static compression stage at the level of the air inlet whose fluid vein feeds a combustion chamber in the subsonic to then be relaxed and accelerate in a Laval nozzle and in that to date no industrial device using the principles of the invention to obtain for example with an engine with aerobic propulsion (by-pass) and anaerobic (engine -fusee) at takeoff a thrust equal to at least three times and more the thrust of the said engine in the vacuum has been achieved and in that the device of the invention relates to systems and propulsion systems comprising such a device.

2. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an "aerobic and / or anaerobic" propulsion engine, comprises a propellant. pass consisting of an outer casing (107) disposed over the entire length of the system and the propelled assembly thereof being provided with a general outlet nozzle (108).

3. Propulsion device of the "aerobic and / or anaerobic" type according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least one aerobic and / or anaerobic propulsion device. a supersonic or hypersonic dilution zone (104) operating at supersonic or hypersonic conditions, located in the general outlet nozzle, followed by one or a plurality of general exit nozzles (108).

Aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least one or a a plurality of combustion chambers (102) located upstream of at least one or a plurality of outlet nozzles (103) of at least one or a plurality of combustion chambers.

Aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises an aerobic propulsion device. and / or anaerobic, also called aerobic and / or anaerobic motor provided with at least one outlet nozzle device (103) of the combustion chamber and in that said nozzle is, downstream of the neck of the nozzle (103), provided with devices for improving the dilution and cooling of the outlet nozzle device (103) of the combustion chamber, as for example in that said devices for improving dilution and cooling consist of recesses in the wall of said nozzle (103), the aerobic propulsion device and / or anaerobic, also called aerobic and / or anaerobic propulsion motor .

An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises an aerobic propulsion device and an aerobic propulsion device. or anaerobic, also called an aerobic and / or anaerobic motor provided with at least one outlet nozzle device (103) of the combustion chamber and in that said nozzle is, downstream of the throat of the nozzle (103), provided with devices for improving the dilution and cooling of the outlet nozzle device (103), the combustion chamber such as in that said devices for improving the dilution and cooling consist of axial recesses, longitudinal or parallel to the axis of the nozzle (103) and located in the wall of said nozzle (103) after the neck in the non-cylindrical divergent portion, of the aerobic propulsion device and / or anaerobic, also called an aerobic and / or anaerobic propulsion engine, and in that the presence of the devices for improving the dilution and the cooling makes it possible to amplify the phenomenon of supersonic or hypersonic fluid entrainment of the aerobic fluid vein (106). ) resulting in an increased vacuum force at the inlet of the bypass system (109).

An aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic type motor, according to claim 1, characterized in that the outlet nozzle devices (103) of the combustion chamber, of the propulsion device central (101) of aerobic and / or anaerobic type, also called aerobic and / or anaerobic motor, and general outlet nozzle (108) of the aerobic propulsion device and / or anaerobic, also called aerobic and / or anaerobic type motor, are of the "Laval nozzle" type and in that the general outlet nozzle (108) of the Laval nozzle type has a profile which is in the extension of the nozzle (103), also Laval type nozzle located upstream of the nozzle (108) and characterized in that the neck of the general outlet nozzle (108) has a section greater than or equal to the outlet section of the nozzle (103) and in that the outlet section of the nozzle (103) corresponds to the exit section of the neck of the outlet nozzle (108) allowing a particular operation in that the nozzle (103) is nested in the nozzle (108) very precisely and so that the hot combustion gases from the nozzle (103) can in no way be influenced by the convergent portion of the nozzle (108) and even less that of the influence of the neck of the nozzle (108) so that in this case in particular, the hot combustion gases of the nozzle (103) have a supersonic or hypersonic velocity which they retain at the inlet of the divergent nozzle (108) and are then accelerated a second time in the dilution zone (104), supersonic or hypersonic system operating under supersonic or hypersonic conditions, by exaltation of the hot combustion gases by means of the aerobic fluid vein (106) thus enabling the generation of a supersonic or hypersonic flow whose physical phenomenon is permanent and continuous and characterized in that the by-pass system of the invention provides a significant thrust gain of a coefficient greater than one up to three and more.

8. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises a by-pass system. aerobic pass composed of an outer casing (107) comprising at least one bypass inlet (109) of the aerobic fluid vein (106) circulating in the bypass and provided with a single nozzle or with a plurality of general nozzles output (108).

Aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said propulsion device aerobic and / or anaerobic type, also called aerobic and / or anaerobic propulsion motor, comprise at least one or a plurality of bypass systems.

10. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion motor, comprises the presence of recesses. consecutive and successive ovoids in the divergent nozzle (103) which allows the exaltation of the kinetic energy of the hot combustion gases from the aerobic fluid stream (106) which by successive exaltations, the recesses being one upstream others, allows to exalt the resulting total kinetic energy of the total fluid stream of output, by the process of having a fluid vein exalted by a first ring of recesses that heats and expands said injected fluid allowing a conversion of thermal energy into kinetic energy so that the kinetic energy of the hot combustion gases is higher at the second stage. t and in that the process is repeated in a cascade step by step and recesses in recesses to the extent that the recesses are calibrated according to the available convertible thermal energy, which has the consequence of having a phenomenon of fluid entrainment of the aerobic fluid vein (106) much higher compared to the same system without recesses, knowing that the fluid entrainment of the aerobic fluid vein (106) in the bypass is more important in the case of a recessed nozzle, the vacuum force at the inlet of the bypass is increased, which makes it possible to increase the mass flow rate at the outlet of the general nozzle (108) and consequently to increase the total thrust force which is the sum of the thrust force at the outlet of the nozzle (108) and the tensile and suction force of the aerobic fluid vein (106) at the inlet of the bypass (109) and in that the fact to use recessed nozzles in the diverging part ente constitutes a thermal energy converter into kinetic energy.

11. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said device for aerobic and / or anaerobic propulsion, also called an aerobic and / or anaerobic propulsion engine, comprises, as additional technical features, one or a plurality of modulation means by partial or total closure of the entries of the bypass (109) of the vein aerobic fluid (106) circulating in the outer casing (107) of the bypass for modulating the mass flow of the aerobic fluid stream (106) creating an asymmetric flow in the general outlet nozzle (108).

12. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical characteristic a or a plurality of modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid stream (106) circulating in the casing (107) of the bypass serving to guide the system and the set powered.

13. Aerobic and / or anaerobic propulsion device according to any one of claims 11 and 12, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical feature that the use of the modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid stream (106) circulating in the outer casing (107) of the bypass, is adapted the flight conditions and the route traveled.

14. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises a by-pass system. pass composed generally of one or more elements thereby defining one or a plurality of orifices at the fluid inlet at the inlet of the bypass (109), where these elements then meet for forming a dilution zone (104), supersonic or hypersonic operating at the conditions supersonic or hypersonic, common connected to a nozzle or a plurality of general exhaust nozzles (108).

15. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises at least four orifices. an inlet defining at least four aerobic fluid veins (106) uniformly distributed over the circumference of the propulsion device (101) and which then join to form a supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic, supersonic conditions or hypersonic common connected to a nozzle or a plurality of general outlet nozzles (108).

16. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called aerobic and / or anaerobic propulsion engine, comprises several Laval nozzle arranged in the aerobic fluid vein (s) (106) circulating in the bypass casing (107) and located upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the general nozzle of output (108).

17. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is produced according to FIG. in that one of the devices of the invention comprises an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, which does not comprise an aerobic compression stage located at the entrance. of the bypass device and arranged upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, and in that said aerobic and / or anaerobic propulsion device, also called a propulsion motor aerobic and / or anaerobic comprises in the central part an aerobic and / or anaerobic propulsion device (101) with propellants or propellants solids having an aerobic and / or anaerobic combustion chamber (102) supplying the upstream side of an outlet nozzle (103) of the combustion chamber, the ejection of the hot combustion gases in the supersonic or hypersonic mode being effected in the downstream portion (105) of the outlet nozzle of the combustion chamber located downstream of the throat of the nozzle of the aerobic propulsion device and / or anaerobic, and that the aerobic and / or anaerobic propulsion device, called also aerobic and / or anaerobic propulsion engine comprises a bypass system consisting of an outer casing (107) defining an aerobic fluid vein (106) flowing between the outer casing (107) and the central body (101) of the engine aerobically and / or anaerobically propelled, and in that the ejection of hot combustion gases in supersonic or hypersonic mode occurring in the downstream portion (105) of the outlet nozzle of the combustion chamber generates a negative pressure in the combustion chamber. the bypass inlet (109), which then functions as a static vacuum cleaner by fluid drive, the bypass from the front of the powered systems and assemblies to the rear of these by creating a general outlet nozzle (108) such that the outlet nozzle (103) of the combustion chamber of the aerobic and / or anaerobic central propulsion device is located inside the general outlet nozzle (108) , and in that said aerobic and / or anaerobic propulsion motor comprises a general outlet nozzle (108) which receives the hot combustion gases from the outlet nozzle (103) of the combustion chamber of the propulsion engine aerobic and / or anaerobic and which ensures the supersonic or hypersonic dilution of said hot combustion gases, the thermal exchange expansion and the supersonic or hypersonic expansion of the aerobic fluid vein (106) from the bypass and at the outlet of this it in the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the downstream portion of the combustion chamber outlet nozzle (103) which generates a pressure difference between the combustion chamber input (109) in the bypass depression and its output operating in supersonic or hypersonic mode, all resulting in a significant increase in the flow rate mass ejected at the outlet of the general outlet nozzle (108), the thrust and the ejection speed at the outlet of the general outlet nozzle (108), and in that the depression force generated at the inlet (109) of the bypass contributes to improve the aerodynamic performance of the systems and assemblies propelled by adding to the thrust force from the general exhaust nozzle (108), and in that the propulsion device, also called engine aerobic and / or anaerobic propulsion comprises a bypass (107) disposed over the entire length of the system and the powered assembly thereof being provided with a general outlet nozzle (108), and in that the propulsion, also called an aerobic and / or anaerobic propulsion engine, comprises at least one supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, located in the general exhaust nozzle (108), followed by a or a plurality of general exit nozzles (108), and in that the aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises an anaerobic and / or aerobic motor provided with at least one or a plurality of combustion chambers (102) located upstream of at least one or a plurality of outlet nozzles

(103) of at least one or a plurality of combustion chambers, and in that the outlet nozzle device (103) of the combustion chamber is provided, downstream of the neck of said nozzle (103), with in order to improve the dilution and the cooling of the outlet nozzle device (103) of the combustion chamber, for example in that the said devices for improving the dilution and the cooling consist of recesses in the wall of the said nozzle (103), of the aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises the nozzle devices outlet (103) of the combustion chamber of the central propulsion device (101) of aerobic and / or anaerobic type, also called aerobic and / or anaerobic propulsion engine and of the general exhaust nozzle (108) of the central propulsion device (101) of the aerobic and / or anaerobic type, called also aerobic and / or anaerobic propulsion engine, are of the "Laval nozzle" type, and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises an aerobic bypass system composed of a external casing (107) having at least one inlet of the bypass (109) of the aerobic fluid stream (106) circulating in the bypass and provided with a single nozzle or with several outlet nozzles (108), and the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical characteristic one or a plurality of modulation means by partial or total closure of the bypass entrances (109) of the aerobic fluid vein ( 106) and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical feature one or a plurality of partial or partial shutter modulation means. tale entries of the bypass (109) of the aerobic fluid vein (106) for guiding the system and / or the powered assembly and that the propulsion device, also called aerobic and / or anaerobic propulsion engine it is understood as an additional technical feature that the use of the modulation means by partial or total closure of the entrances of the bypass (109) of the aerobic fluid vein (106) is adapted to the flight conditions and the path traveled, and that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises a bypass system generally consisting of one or more elements thus defining one or more orifices at the fluid inlet to the the bypass inlet (109), which element (s) then rejoins to form a common dilution zone (104) connected to a nozzle or a plurality of outlet nozzles (108), and in that the device of propulsion, also called an aerobic and / or anaerobic propulsion engine, comprises at least four intake ports defining at least four aerobic fluid veins (106) uniformly distributed over the circumference of the propulsion device (101) and then joining together to form a a supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, common to a nozzle or at a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises no Laval nozzle or nozzles arranged in the aerobic fluid vein (s) (106). and located upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions.

An aerobic and / or anaerobic propulsion device according to claim 1 characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is produced according to FIG. 2 and in that one of the devices of the invention comprises an aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, and which does not comprise an aerobic compression stage situated at the inlet of the device by-pass and disposed upstream of the supersonic or hypersonic dilution zone (104) operating under supersonic or hypersonic conditions, and in that said aerobic and / or anaerobic propulsion device, also called an aerobic propulsion motor, and / or anaerobic comprises in the central part an aerobic and / or anaerobic propulsion device (101) with liquid propellants or propellants and / or with a typical liquid fluid e rare gas having an aerobic and / or anaerobic combustion chamber (102) and in that said aerobic and / or anaerobic combustion chamber (102) is fed with an injection system (110) consisting of at least one turbopump (1) and / or a plurality of turbopumps (1) supplying said combustion chamber (102) with liquid propellants or propellants and / or in that said aerobic combustion chamber (102) and / or anaerobic is fed with an injection system (111) of liquid fluid located at the periphery of said combustion chamber (102) and / or in that said exhaust nozzle (103) of the aerobic combustion chamber and / or anaerobically is fed with an injection system (114) of liquid fluid located upstream of the neck of said outlet nozzle (103) and / or in that said outlet nozzle (103) of the aerobic and / or anaerobic combustion chamber is fed by means of an injection system (115) of liquid fluid located downstream of the neck of said outlet nozzle (103), whose total gas flow feeds at least one outlet nozzle (103) of the combustion chamber and whose gas ejection in supersonic or hypersonic mode is in the downstream part (105) of the exhaust nozzle of the combustion chamber located downstream of the throat of the nozzle of the aerobic and / or anaerobic propulsion device, and in that the aerobic and / or anaerobic propulsion device, also called an aerobic propulsion motor, and / or anaerobic comprises a bypass system consisting of an outer casing (107) defining an aerobic fluid vein (106) flowing between the outer casing (107) and the central body (101) of the aerobic propulsion motor and / or anaerobic, and in that the gas ejection in supersonic or hypersonic mode occurring in the downstream portion (105) of the outlet nozzle of the combustion chamber generates a vacuum at the inlet of the bypass (109), this one then functioning as an aspirant static stator by fluid drive, the bypass from the front of the propelled systems and assemblies to the rear of these by creating a general outlet nozzle (108) so that the outlet nozzle (103) ) of the combustion chamber of the aerobic and / or anaerobic central propulsion device is located inside the general outlet nozzle (108), and in that said aerobic and / or anaerobic propulsion motor comprises a general outlet nozzle (108) which receives the gases coming from the outlet nozzle (103) of the combustion chamber of the aerobically and / or anaerobically propelled engine and which ensures the supersonic or hypersonic dilution of said gases, the expansion by exchanges thermal and supersonic or hypersonic expansion of the aerobic fluid vein (106) from the bypass and at the outlet thereof in the dilution zone (104), supersonic or hypersonic operating under supersonic conditions o u hypersonic, located in the downstream portion of the outlet nozzle (103) of the combustion chamber which generates a pressure difference between the inlet (109) in the bypass depression and its output operating in supersonic or hypersonic mode , all resulting in a significant increase in the mass flow ejected at the outlet of the general outlet nozzle (108), the thrust and the speed of ejection in output of the general exhaust nozzle (108), and in that the vacuum force generated at the inlet (109) of the bypass contributes to improving the aerodynamic performance of the propulsion systems and assemblies by adding to the thrust force from the general outlet nozzle (108), and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises a bypass (107) arranged over the entire length of the system and the assembly propelled it being provided with a general outlet nozzle (108), and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises at least one dilution zone (104), supersonic or hypersonic operating at supersonic or hypersonic conditions, located in the general exhaust nozzle (108), followed by one or a plurality of general exhaust nozzles (108), and that the aerobic propulsion device and / or anaerobic, also referred to as an aerobic and / or anaerobic propulsion engine, comprises an anaerobic and / or aerobic motor provided with at least one or a plurality of combustion chambers (102) located upstream of at least one or a plurality of jet nozzles. outlet (103) of at least one or a plurality of combustion chambers and in that the outlet nozzle device (103) of the combustion chamber is provided, downstream of the neck of said nozzle (103), devices for improving the dilution and cooling of the outlet nozzle device (103) of the combustion chamber, such as, for example, that said devices for improving dilution and cooling consist of recesses in the wall of the combustion chamber. said nozzle (103), the aerobic propulsion device and / or anaerobic, also called aerobic and / or anaerobic propulsion engine, and in that the propulsion device, also called aerobic propulsion motor and / or anaerobic co mprenne the outlet nozzle devices (103) of the combustion chamber of the aerobic and / or anaerobic central propulsion device (101), also called an aerobic and / or anaerobic propulsion engine and a general exhaust nozzle (108) of the aerobic and / or anaerobic central propulsion device (101), also called an aerobic and / or anaerobic propulsion engine, are of the type "Laval nozzle", and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises an aerobic bypass system composed of an outer casing (107) comprising at least one inlet of the bypass. pass (109) of the aerobic fluid stream (106) circulating in the bypass and provided with a single nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called engine aerobic and / or anaerobic propulsion unit comprises, as an additional technical feature, one or a plurality of modulation means by partial or total closure of the entries of the bypass (109) of the aerobic fluid vein (106) and in that the propulsion device , also called an aerobic and / or anaerobic propulsion engine, comprises as an additional technical feature one or a plurality of modulation means by partial or total closure of the bypass entrances (109) of the aerobic fluid vein ( 106) for guiding the system and / or the powered assembly and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine comprises as an additional technical feature that the use of the partial shutter modulation means or total entries of the bypass (109) of the aerobic fluid vein (106) is adapted to the flight conditions and the path traveled, and in that the propulsion device, also called aerobic and / or anaerobic propulsion engine includes a bypass system generally consisting of one or more elements thereby defining one or more orifices at the inlet of the fluid at the inlet of the bypass (109), this or these elements joining together then to form a common dilution zone (104) connected to a nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic propulsion motor and / or anaerobic comprises at least four intake ports defining at least four aerobic fluid veins (106) uniformly distributed over the circumference of the propulsion device (101) each disposed at one hundred twenty degrees and then joining together to form a dilution zone (104). supersonic or hypersonic operating under supersonic or hypersonic conditions, common to a nozzle or a plurality of outlet nozzles (108), and in that the propulsion device, also called an aerobic and / or anaerobic propulsion engine comprises no Laval nozzle or nozzles arranged in the aerobic fluid vein (s) (106) and located upstream of the dilution zone (1 04), supersonic or hypersonic operating under supersonic or hypersonic conditions.

19. An aerobic and / or anaerobic propulsion device according to any one of claims 1 to 18, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic propulsion unit, and / or or anaerobic, is intended to be used to propel a torpedo or a boat in water or on water, and in that said aerobic and / or anaerobic propulsion device, also called an aerobic propulsion engine, and / or or anaerobic, is intended to be used to propel into the atmosphere a missile, a rocket, boosters, an aircraft, a spacecraft or spacecraft, a space shuttle or an intercontinental strategic ballistic missile, propelled systems and assemblies. , the aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion motor, having a very high thrust in the launching phase; u take - off or in the ascent phase in the atmosphere, with a significant increase in acceleration and rate of climb, range, range and / or payload and in that the case of the propulsion of an intercontinental strategic ballistic missile to enable it then to pass instantly, by the dropping of the first stage and the bypass, from the aerobic and / or anaerobic propulsion mode to the "anaerobic" propulsion mode by the firing of the second stage then of the third stage ensuring a continuity of the thrust in the atmosphere and the exit of the dense layers of the atmosphere.

20. An aerobic and / or anaerobic propellant according to any one of claims 1 to 18, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic propulsion motor. and / or anaerobic, can be assembled alone or in series thus constituting at least two or a plurality of aerobic and / or anaerobic propulsion stages for propelling a system and / or an assembly comprising such a device.

21. An aerobic and / or anaerobic propulsion device according to any one of claims 1 to 18, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion motor. , can be assembled alone or in parallel and in that the assemblies thus formed can be assembled, for example, to form at least one cluster assembly, to propel a system and / or an assembly comprising such a device.

22. aerobic propulsion device and / or anaerobic, according to any one of claims 1 to 18, characterized in that said aerobic propulsion device and / or anaerobic, also called aerobic and / or anaerobic propulsion motor constituting assemblies in series which can in turn be assembled in parallel and that the assemblies thus formed can be assembled, for example, to form a cluster assembly, to propel a system and / or an assembly comprising such a device .

23. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is made according to an industrial embodiment. the object of FIG. 3, and in that said motor with aerobic and / or anaerobic propulsion (101) is composed of at least one combustion chamber (102), fed with solid or liquid propellants, also called propellant chamber or for propulsion of said aerobic and / or anaerobic propulsion motor (101) delimited by the walls of at least one nozzle (103), and in that at the periphery of at least one combustion chamber (102) are arranged fluid injection systems (111), for confining the seat of the propellant combustion so that the injection of the rare gas fluid surrounding the flame is between said flame and the wall of the said combustion chamber so that the walls are cooled and protected oxidation and corrosion phenomena, noble or noble gases being chemically inert, and in that the injected fluid mixes downstream of at least one combustion chamber in a dilution zone (113) located upstream of the neck at least one nozzle (103), and in that the gas mixture, consisting of hot combustion gases exalted by the rare gas fluid injected by the injection system (111), having intrinsic characteristics improved compared to the intrinsic characteristics of the burned gases alone, either expanded in the downstream part (105) of at least one outlet nozzle (103) of the combustion chamber, accelerating said gas mixture to the free outlet of said at least one outlet nozzle (103) of the combustion chamber and in that the fluid injected in the presence of the seat of the combustion changes its physical state by passing from the liquid state to the gaseous state making it possible to significantly increase the thrust following three processes, knowing that the space propulsion as it is practiced today only converts a very small part of the thermal energy into kinetic energy of thrust, is to act as a thermal energy converter in kinetic energy increasing the thrust and in that the first process consists in transferring part of the thermal energy of the combustion to the injected fluid, the second process consists in improving the intrinsic qualities of the fluid medium thus constituted, namely, the increase of its density and the increase of its speed of sound at the neck of the Laval nozzle (103) and in that the third process consists in relaxing the fluid medium passing through the throat of the nozzle (103) allowing accelerating said fluid in the divergent portion of the nozzle (103) and thereby converting a larger portion of the thermal energy of the fluid stream into kinetic energy e, with a higher energy efficiency compared to the simple use of propellants, resulting in an increase in speed and thrust, because the mass flow is increased, which allows now to operate the combustion chambers close to the mixture stoichiometric propellant avoiding to force the oxygen combustion chamber to increase the mass flow which has for consequences of amplifying the phenomena of oxidation and corrosion.

24. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is produced according to an industrial embodiment. the object of FIG. 4, and in that said aerobic and / or anaerobic propulsion engine is characterized in that said aerobic and / or anaerobic propulsion motor (101) is composed of a plurality of injection systems of fluid (114) inclined relative to and towards the axis (112) of the nozzle (103) and disposed on at least one ring at the walls of at least one outlet nozzle (103) of the combustion chamber preceding the neck of the nozzle (103), and in that the injected fluid varies, by modulation of its injection pressure and its flow, the neck section of at least one nozzle (103) by modifying the current lines fluid from at least one combustion chamber (102) of said anaerobic motor (101), and in that the modulation of the nozzle neck section (103) varies the ratio of the neck section of said nozzle to the section output of the divergent portion of the nozzle (103) Laval type and in that the smaller the ratio is the higher the ejection velocity of the gases in the outlet section is important, considering that the fluid is not on relaxed at the outlet of the nozzle (103), and in that the thermal transfer of the gases makes it possible to exalt the kinetic energy of the fluid medium ejected downstream of the nozzle (103), resulting in an increase in the mass flow rate and an increase in the total thrust, and in that the injection of the inert fluid allows to cool and protect the walls of the nozzle (103) oxidation and corrosion phenomena, noble or noble gases being chemically inert.

25. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is produced according to an industrial embodiment. the object of FIG. 5, and in that said engine with aerobic and / or anaerobic propulsion is characterized in that said aerobic and / or anaerobic propulsion motor (101) is composed of a plurality of fluid injection systems (115) disposed on at least one ring at the walls downstream of the neck of at least one nozzle (103), and in that the injected fluid serves to exalt the fluid from the neck of at least one nozzle (103), by modulating its injection pressure and its flow, resulting in a modulation of the mass flow ejected and accelerated at the outlet of said at least one nozzle (103), all operating and used to adapt the thrust of the anaerobic motor (101) to the different phases of flight, and in that the purpose of the injected fluid is to maximize the thrust by directing the flow of gas ejected along the longitudinal axis (112) of at least one nozzle (103), and in that the injection of the inert fluid makes it possible to cool and to protect the walls of the nozzle (103) of the oxidation and corrosion phenomena, rare or noble gases being chemically inert.

26. An aerobic and / or anaerobic propulsion device according to claim 25, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, has the additional feature that the device for aerobic and / or anaerobic propulsion injection of fluid (115) based on dense rare gas such as krypton, allows to increase the thrust being associated or not with an afterburner system and / or bypass having the consequences and advantages an increase of autonomy, the radius of action, and the maximum speed of the system and powered assembly comprising such a device such as for example a fighter plane, a drone, a reconnaissance aircraft, a space shuttle.

27. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion motor, has the additional characteristic of having a wall. which behaves like a mirror reflecting the thermal radiation in order to maximize the radiation heat exchange between the different fluids, for example the hot combustion gases and the injected fluid, and minimize the absorption of thermal radiation by the wall of the nozzle.

28. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, is characterized in that the present invention aims to performing a propulsion device also called an aerobic and / or anaerobic propulsion engine (101) having as an additional feature the injection of dense "rare" gases, for example argon, krypton or xenon, also called "noble" gases dense or dense "inert" gases, for the exaltation of the hot combustion gases in order to modify the intrinsic characteristics of the fluid medium by increasing the density and the speed of sound of said fluid medium and in that the increase of said characteristics of the medium come from the intrinsic characteristics of the fluid used for exaltation knowing that the speed of sound of the medium will also be t is increased by the temperature rises and in that the characteristics can be greatly increased by a factor of two or more and that the present invention makes it possible to achieve sound velocities at the neck of the nozzle (103). Laval important, with for example krypton, allowing acceptable combustion temperatures by the materials composing the walls of the combustion chamber (102) and the nozzle (103) thus allowing very high thrust engines pushing the current technological barriers.

29. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, and characterized in that the present invention is intended to provide a propulsion device also called an aerobic and / or anaerobic propulsion engine (101) which has the additional characteristic of injecting "rare" gases, for example helium, also called "noble" gases or "gases". inert ", for the exaltation of hot combustion gases to modify their intrinsic characteristics by increasing their density and the speed of the sound of the medium.

30. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, and characterized in that the present invention aims to to produce a propulsion device also called an aerobic and / or anaerobic propulsion motor (101) having the additional feature of having a combustion chamber (102) composed of at least one liquid propellant injector system having at least one axial and / or radial swirl to create a "swirl" movement, also called "swirl" movement, in the downstream flow of at least one injection system to promote the mixing of said liquid propellants.

31. An aerobic and / or anaerobic propulsion device according to claim 1, characterized in that said aerobic and / or anaerobic propulsion device, also called an aerobic and / or anaerobic propulsion engine, and characterized in that the present invention aims to also to realize an aerobically and / or anaerobically propelled engine (101) having as an additional feature having fluid injector systems (111),

(114) and (115) having at least one axial and / or radial swirler to create a "swirl" movement, also called "swirl" movement, in the downstream flow of at least one injector system for promote the mixing of the different fluids involved.

32. Fuel pump according to claim 1 which aims to increase the thrust of the aerobic propulsion device and / or anaerobic also called aerobic and / or anaerobic propulsion engine and characterized in that said turbopump is a turbo pump. a variable-speed balanced supply of the aerobic and / or anaerobic propulsion device also known as aerobic and / or anaerobic propulsion engines and propulsion systems and assemblies comprising said turbopump and in that said turbopump is balanced and has characteristics of high service life, reliability, flow and / or pressure as well as mechanical drive power enabling the reliable operation of the high speed constant or variable speed turbopump adze and that said turbopump comprises at least one or two pumps, or a plurality of liquid fluid pumps, composed of at least one a stage or a plurality of associated stages in the latter case in series and / or in parallel, at least one or two turbines, or a plurality of turbines, with gas or liquid fluid, composed of at least one stage or a plurality of stages associated in the latter case in series and / or in parallel, a single common rotation shaft connected to said pumps and said turbines and characterized in that the resultant axial forces , caused by all the stages of the "turbine" function and the stages of the "pump" function, in the common rotation shaft to be zero or almost zero and / or in that the resultant of the various axial forces in the common rotation shaft t is zero or almost zero and in that said turbopump has sufficient number of bearings and necessary for the proper functioning of said turbopump, and this regardless of the type of bearing used, and sealing means sufficient and necessary for the proper functioning of lad and regardless of the type of sealing means used, and in that said turbopump comprises turbines, of gas type or of fluid type, whose inputs or inlets and the outputs or discharges on the body of the turbopump. the turbopump may be either of radial type and / or of axial type and / or of tangential type and / or of oblique type, in that said turbopump has pump assemblies whose inputs or admissions and whose outputs or back-ups on the body of the turbopump may be either of the radial type and / or of the axial type and / or of the tangential type and / or of the oblique type. 33. Turbocharger according to claim 32, characterized in that said turbopump has the additional technical characteristic of being a feed turbopump, of the aerobic and / or anaerobic propulsion device, also called aerobic and / or anaerobic propulsion device, in at least one propellant, and / or at least one liquefied gas, and / or at least one liquid fluid and / or at least one cryogenic fluid and in that said turbopump is a turbopump supply of at least one combustion chamber also called propulsion chamber.

34. A turbopump according to claim 32 and characterized in that said turbopump comprises sufficient number of bearings necessary for the proper operation of said turbopump and in that at least one of the bearings is a magnetic bearing.

35. Turbopump according to claim 32 and characterized in that said turbopump comprises a plurality of turbines whose resultant forces is mainly tangential type to maximize the torque in the rotation shaft common to the pumps and turbines.

36. A turbopump according to claim 32 and characterized in that said turbopump comprises a plurality of axial screw feeding pumps with helical screws with constant or variable geometric thread and / or cylindrical geometry and / or conical geometry and / or geometry truncated.

37. A turbopump according to claim 32 and characterized in that said turbopump comprises a plurality of liquid fluid pumps and a plurality of turbines having the same rotation shaft in common, and in that said turbopump can simultaneously pump two liquid fluids and / or two propellants of different chemical nature, such as for example dioxygen and dihydrogen or alternatively dioxygen and kerosene, irrespective of the type of kerosene, thus ensuring the stability of the ratio of the mixture of the two propellants in at least one chamber of combustion also called propulsion chamber, each plurality of pumps being for example separated and disposed on either side of one or a plurality of turbines grouped in this case near the central axis of symmetry of said turbopump.

38. A turbopump according to claim 32 and characterized in that said turbopump comprises at least one or two turbines, or a plurality of gas turbines fed in parallel from a single gas generator or a plurality of gas generators. having the same characteristics and whose head losses in each line of the function "entry or admission turbine" are strictly distributed and identical, these being located between the gas generator (s) and the inlet of each turbine, a portion of the pipes being able to be common to a plurality of gas turbines, the same principle being applied for the circuits of the "exhaust or exhaust turbine" function said turbines so that there is no operating imbalance due to different head losses and that these principles also apply in the case, for example of the oxygen turbine pump equipped with pumps to oxygen and comprising liquid dihydrogen turbines fed from the very high pressure liquid dihydrogen taken at the outlet of the "pump" function of the dihydrogen turbopump or generally in the case of at least two liquid fluids of a kind different chemical.

39. Turbopump according to claim 32 and characterized in that said turbopump comprises a "pump" function, the pressure losses in each pipe of the "input or admission" function, are strictly distributed and identical, and whose pressure losses in each channel of the function "outlet or exhaust" are strictly distributed and identical so that there is no operating imbalance between the stages of the "pump" function of said turbopump due to different losses of loads.

40. Turbopump according to claim 32 and characterized in that said turbopump comprises a "turbine" function, the pressure losses in each pipe of the "input or admission" function, are strictly distributed and identical, and whose losses of loads in each pipe of the function "outlet or exhaust" are strictly distributed and identical so that there is no operating imbalance between the stages of the "turbine" function of said turbopump due to the different losses of loads.

41. Turbopump (1) according to claim 32 and characterized in that said turbopump comprises, according to a possible industrial embodiment of Figure 6, a pair of pumps (8) and (9), or a plurality of pumps , consisting of stages (10) and (11) or a plurality of stages, arranged near the axis of symmetry (24) of the turbopump, and the inlet or inlet of radial type (23) and / or tangential and / or oblique common pumps (8) and (9) ending in a chamber (13) common admission to both pumps (8) ) and (9), supplying the inlets (19) and (20) of the pumps (8) and (9), which are of the axial type, and which are filled with a plurality of axial screw-in booster pumps. constant or variable geometric screw and / or cylindrical geometry and / or conical geometry and / or frustoconical geometry (12) and whose outputs or discharges (21) and (22) pumps (8) and (9) are of radial and / or tangential and / or oblique type and in that said turbopump comprises a pair of turbines (2) and (3) or a plurality of turbines composed of stages (4) and (5) or a plurality of stages and whose inlets (15) and (17) turbines are radial and / or tangential and / or oblique and whose outlets or exhausts (16) and (1) 8) turbines are axial type respectively in an outlet chamber (25) and (26) and in that said turbopump comprises a single shaft (14) of rotation common to the pumps and turbines and characterized in that the resultant axial forces, caused by all turbines of the "turbine" function and by all the pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and / or in that the resulting from the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper functioning of said turbopump , and this whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper operation of said turbopump and whatever the type of sealing means used.

42. Turbopump (1) according to claim 32 and characterized in that said turbopump comprises, according to another possible industrial embodiment of Figure 7, a pair of turbines (2) and (3) or a plurality of turbines composed of stages (4) and (5) or a plurality of stages arranged near the axis of symmetry (24) of the turbopump, and whose inputs or admissions (15) and (17) Turbines are of radial and / or tangential and / or oblique type and in that the outlets or exhausts (16) and (18) of the turbines are of the axial type and are respectively effected by an outlet chamber (25). ) and (26) opening into a common outlet chamber (27) opening on one or more radial and / or tangential and / or oblique outlet manifolds (28) and in that said turbopump comprises a pair of pumps (8). ) and (9) or a plurality of pumps composed of the stages (10) and (11) or of a plurality of stages and whose axial inlet or inlet of each pump (13) opens into an axial feeding pump to helical screw with constant or variable geometric screw pitch and / or cylindrical geometry and / or conical geometry and / or frustoconical geometry (12) which feeds the inlet or axial inlet (19) and (20) of each pump respectively (8) and (9) and having stages (10) and (11), or a plurality of stages and in that the ups and downs (21) and (22) of the pumps (8) and (9) are of the radial and / or tangential and / or oblique type and in that said turbopump comprises a single rotation shaft (14) common connected to said pumps (8) and (9) and said turbines (2) and (3) and characterized in that the resultant axial forces, caused by all turbines of the function "turbine" and by all the pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or quasi zero, allowing operation at constant or variable speed, and in that said turbopump comprises sufficient bearings (7) and necessary for the proper functioning of the turbopump and whatever the type of bearing used, sealing means ( 6) sufficient and necessary for the proper functioning of the turbopump and this whatever the type of sealing means used.

43. Turbopump (1) according to claim 32 and characterized in that said turbopump comprises, according to another possible industrial embodiment of Figure 8, a pair of turbines (2) and (3) or a plurality of turbines composed of floors (4) and

(5) or a plurality of stages of the turbopump, and whose inputs or admissions (15) and (17) of the turbines are of radial and / or tangential and / or oblique type and in that the outlets or exhausts (16) and (18) of the turbines are of the axial type and are effected respectively by an outlet chamber (25) and (26) opening into a common outlet chamber (27) opening onto one or more radial and / or tangential and / or oblique outlet manifolds (28) and in that said turbopump comprises a pair of pumps (8) and (9) or a plurality of pumps consisting of stages (10) and (11) or a plurality of stages and whose inlet or inlet (23) of radial type and / or tangential and / or oblique common to the pumps (8) and (9) terminating in a common inlet chamber (13) to the two pumps (8) and (9) feeding the inlets (19) and (20) of the pumps (8) ) and (9) which are of the axial type and which are filled with a plurality of axial helical screw feeding pumps with a constant geometric thread or and / or cylindrical geometry and / or conical geometry and / or frustoconical geometry (12) which feeds the inlet or axial inlet (19) and (20) of each pump respectively (8) and (9) and comprising stages (10) and (11), or a plurality of stages and in that the ups and downs (21) and (22) of the pumps (8) and

(9) are of radial and / or tangential and / or oblique type and in that said turbopump comprises a single common rotation shaft (14) connected to said pumps (8) and (9) and to said turbines (2) and (3) and characterized in that the resultant of the axial forces, caused by all the turbines of the "turbine" function and by all the pumps of the "pump" function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the proper functioning of the turbopump and whatever the type of bearing used, sealing means (6) sufficient and necessary for the proper functioning of the turbopump and whatever the type of sealing means used .

44. Turbopump (1) according to claim 32 and characterized in that said turbopump comprises, according to another possible industrial embodiment of Figure 9, a pair of turbines (2) and (3) or a plurality of turbines composed of stages (4) and (5) or of a plurality of stages whose inputs or admissions (15) and (17) of the turbines are of radial and / or tangential and / or oblique type and in that the outlets or exhausts (16) and (18) turbines are axial and are respectively effected by an outlet chamber (25) and (26) opening into a common outlet chamber (27) opening on one or more outlet manifolds (28). ) of the radial type and / or tangential and / or oblique and in that said turbopump comprises a pair of pumps (8) and (9) or a plurality of pumps composed of the stages (10) and (11) or of a plurality of stages and whose admission or axial inlet of each pump (13), resulting from the two admissions (3 0) of the radial type and / or tangential and / or oblique, opens into an axial screw feeding pump with helical screws with constant or variable geometric thread and / or with a cylindrical geometry and / or with a conical geometry and / or with a frustoconical geometry (12) which feeds the inlet or axial inlet (19) and (20) of each pump respectively (8) and (9) and having stages (10) and (11), or a plurality of stages and in that the discharge or outlet, also called the outlet manifold (29) of the pumps (8) and (9) are of radial and / or tangential and / or oblique type and in that said turbopump comprises a single rotation shaft (14) connected to said pumps (8) and (9) and said turbines (2) and (3) and characterized in that the resultant axial forces, caused by all the turbines of the "turbine" function and by the 'set of pumps'pump' function, in the common rotation shaft is zero or almost zero, and / or in that the resultant of the various axial forces in the common rotation shaft is zero or almost zero, allowing operation at constant or variable speed, and in that said turbopump comprises bearings (7) in sufficient number and necessary for the good operation of the turbopump and whatever the type of bearing used, sealing means (6) sufficient and necessary the proper functioning of the turbopump and this whatever the type of sealing means used.

45. Turbocharger according to claim 32 and characterized in that said turbopump has the additional feature of using composite materials.

46. A turbopump according to claim 32 and characterized in that said turbopump has the additional feature of using thermo-structural materials.

47. A turbopump according to claim 32 and characterized in that said turbopump has the additional feature of using ceramic materials.

48. A turbopump according to claim 32 and characterized in that said turbopump has the additional characteristic of being driven by at least one gas turbine and in that said gas is water vapor.

49. A turbopump according to claim 32 and characterized in that said turbopump has the additional characteristic of being driven by at least one electric motor in place of the gas turbine or steam turbine drive.

50. A turbocharger according to claim 32, characterized in that said turbopump relates to the field of feed turbopumps and in particular feed turbopumps, the aerobic propulsion device and / or anaerobic also called aerobic propulsion engines. and / or anaerobically, in rare gas type liquid fluid such as helium, neon, argon, krypton or xenon.

51. A turbopump according to claim 32 and characterized in that said turbopump has the additional feature of being able to operate at a constant speed or at variable speed by varying in the one or more gas turbines of said turbopump the mechanical driving power of the turbopumps. gases produced by one or a plurality of gas generators.

52. Turbopump (1) according to claim 32 and characterized in that said turbopump (1) has the characteristic of being able to operate at a constant speed and at variable speed and in that said turbopump (1), comprising a single rotation shaft ( 14) connected to the pumps (8) and (9) and to the turbines (2) and (3), has the additional feature of being able to vary the pressure, the speed of rotation and the flow rate of the said pumps (8) and (9). of said turbopump (1).

53. A plurality of turbopumps according to any one of claims 32 to 52 and characterized in that said set of plurality of turbopumps has the additional feature of being assembled so that the "pump" function of the plurality of turbopumps are mounted in series to increase the pressure.

54. A set of plurality of turbopumps according to any one of claims 32 to 52 and characterized in that said plurality of turbopumps has the additional feature of being assembled so that the "pump" function of the plurality of turbopumps is connected in parallel to increase the flow.

55. A plurality of turbopumps according to any one of claims 32 to 52 and characterized in that said plurality of turbopumps has as additional features to be assembled so that the function

"Pump" of a plurality of turbopumps is connected in series to increase the pressure and in that the "pump" function of a plurality of turbopumps is connected in parallel to increase the flow rate.

A plurality of turbopumps according to any one of claims 32 to 52 and characterized in that said plurality of turbopumps is assembled so that the respective turbines of each turbopump are connected in parallel and fed from a same gas generator or a plurality of gas generators having the same characteristics and in that said gas is produced from liquefied gas or liquid or solid propellant and / or liquid fluid. 57. Aerobic and / or anaerobic propulsion engines characterized in that said engines comprise at least one combustion chamber also called propulsion chamber and at least one turbopump according to any one of claims 32 to 52. for supplying at least one liquid fluid and / or at least a liquid propellant of said at least one combustion chamber also called propellant chamber.

58. Propulsive systems and systems characterized in that said systems and the propulsion units comprise at least one combustion chamber also called propulsion chamber and at least one turbopump according to any one of claims 32 to 52, for the supply of fuel. at least one liquid fluid and at least one liquid propellant of said at least one combustion chamber also called propulsion chamber in that said propulsion systems and assemblies are of rocket, missile, aircraft, rocket aircraft type , supersonic and / or hypersonic aircraft, drone, airplane or orbital network, aircraft or spaceship, intercontinental reconnaissance aircraft, intercontinental strategic bomber, and other powered systems and assemblies.