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WO2019201969A1 - Dispositif d'entraînement d'un générateur - Google Patents

Dispositif d'entraînement d'un générateur Download PDF

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Publication number
WO2019201969A1
WO2019201969A1 PCT/EP2019/059875 EP2019059875W WO2019201969A1 WO 2019201969 A1 WO2019201969 A1 WO 2019201969A1 EP 2019059875 W EP2019059875 W EP 2019059875W WO 2019201969 A1 WO2019201969 A1 WO 2019201969A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
rotation
nitrogen
axis
combustion chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2019/059875
Other languages
German (de)
English (en)
Inventor
Alfred Fuchs
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of WO2019201969A1 publication Critical patent/WO2019201969A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/66—Combustion or thrust chambers of the rotary type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2261—Carbides of silicon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the device comprising a rotor rotatably mounted about a rotation axis, wherein on the rotor at a radial distance from the axis of rotation a plurality of rocket engines circumferentially arranged on one side combustion chambers and rigidly connected to the rotor to rotate in an operating state of the device about the axis of rotation and thus to rotatably drive the rotor about the axis of rotation, wherein the combustion chambers are preferably designed as expansion nozzles.
  • EP 3085922 A1 discloses a device for converting thermal energy into mechanical or electrical energy, comprising a shaft and jet engines, wherein the
  • Jet engines have combustion chambers and in one
  • the core of the invention is to provide as a thermodynamic machine, a set of small rocket engines mounted on a high-strength rotor about a common axis of rotation
  • a generator can be driven, wherein the conversion of the generated electrical energy to the mains frequency in a conventional manner electronically.
  • the rocket engines are active burners whose power is e.g. 1 MW, whereby the complexity of the system comparatively low and the performance - in contrast to known solutions - is well scalable. The division on a variety of
  • Rocket engines or burners also has great advantages for system availability. Accordingly, it is in a device for driving a generator for generating electrical energy, the device comprising a rotor rotatably mounted about an axis of rotation, provided that at the rotor at a radial distance from the axis of rotation more
  • Rocket engines are arranged circumferentially with one side open combustion chambers and rigidly connected to the rotor to rotate in an operating state of the device about the axis of rotation and thus rotatably drive the rotor about the axis of rotation, the combustion chambers preferably as expansion nozzles
  • the openings of the combustion chambers are arranged so that the support mass is substantially tangential to the rotor or to
  • the "rotary" drive means that in the operating state, a rotation of the rotor about the axis of rotation is effected by the rocket engines.
  • "Essentially tangential” is to be understood that the rocket engines with a tangent to the imaginary circle a small angle, preferably from 0 ° to 5 °, so that the exhaust jet or support mass is directed more away from the rotor to
  • the distribution of rocket engines along the imaginary circle is regular - i. in a regular sequence of angular intervals -, in particular in the same
  • Expansion nozzles are known per se and are also referred to as Laval nozzles.
  • auxiliary circle tangentially which auxiliary circle is centered about the axis of rotation and arranged in a plane perpendicular to the axis of rotation and extends through the point.
  • the point may be any point on the particular carbon fiber.
  • the low mass in the periphery of the rotor causes a low moment of inertia and allows correspondingly high angular acceleration at relatively low
  • Claim material of the rotor can be kept as small as possible.
  • silicon carbide as a matrix withstand the increased temperatures encountered in rocket engine operation, it also advantageously has a high temperature
  • Centrifugal forces That is, the carbon fibers are arranged so that they are loaded in the operating state, at least roughly parallel to the direction in which they have their maximum strength, which the strength of the rotor in terms of enormously increases loads occurring in the operating state due to the centrifugal forces.
  • the course of the respective carbon fiber with the tangent an angle of 55 ° to 90 °, preferably from 65 ° to 90 °, includes.
  • the carbon fibers can thus extend radially (to the axis of rotation or away from it), in which case said angle is 90 °.
  • Section of the rotor, in which the rocket engines are arranged, is arranged in an exhaust space, as seen from the outer radial portion of the rotor to the rotational axis, a housing, the exhaust gas chamber gas-tight, and that between the housing and the axis of rotation, a working space is arranged, in which an inner radial portion of the rotor is disposed, and wherein the working space is evacuated to in
  • the exhaust space is formed substantially closed, with means for discharging the exhaust gases are provided.
  • the terms "evacuable” and “vacuum” are clearly to be understood to mean such vacuums that can be technically easily implemented in practice.
  • the inner radial section of the rotor can be sealed off from the exhaust gas chamber, for example by means of a non-contact seal, which is arranged in the region of the housing and, for example, completely analogous to a rotor of an evacuation pump
  • a gas curtain known per se may be provided in the non-contact seal.
  • the inner radial portion of the rotor is disposed between the outer radial portion of the rotor and the axis of rotation.
  • Range from 9000 min -1 to 36000 min -1 , preferably from 16000 min -1 to 24000 min -1 , and is preferably an integer multiple of a frequency of a low-voltage power network.
  • low-voltage power grids are usually used which provide 230 V single-phase or 400 V three-phase with 50 Hz mains frequency. In some countries of the world, e.g. also 60 Hz used as mains frequency.
  • the speed is high and preferably an integer
  • a known, electronically operating frequency converter can be used, which can be co-optimized in particular with the generator.
  • a mechanical solution would also be conceivable in which a transmission, e.g. one
  • Planetary gear with a rigid gear ratio is connected between the generator and the device or the rotor according to the invention.
  • mechanical wear must be taken into account, e.g. by usual maintenance and inspection measures.
  • Low voltage power grid usable AC voltage would be e.g. the use of a generator with counter rotating field in the rotor. For example, if the rotor of the generator rotates at 6 times the mains frequency, but at the same time the rotor generates a field of excitation with 5 times the mains frequency in the opposite direction, the mains frequency will also be in the opposite direction
  • Stator windings generated so that not all the electrical power generated must be electronically transformed, but the electronics only has to muster the power of the exciter field.
  • Gas velocity corresponds, so that the energy output is maximized in a single-stage expansion process, for example, 1500 m / s.
  • a possible parameter combination is for example a speed of 18000 min -1 and a radius of 0.8 m. In this case, a centrifugal acceleration of about 290000 g occurs.
  • the centrifugal force occurring in the operating state or centrifugal force can advantageously be used to supply fuel to the rocket engines.
  • Inventive device provided that in the region of the axis of rotation a fixed supply line for fuel
  • the at least one fuel line is rigidly connected to the rotor and preferably in the rotor
  • Fuel line opens, e.g. as annular or
  • Mouth area opposite the working space can, for example, analogous to above-explained gas-tight seal of the evacuated
  • Each combustion chamber is designed as an expansion nozzle with a pre-combustion chamber and an adjoining main combustion chamber, wherein a light cross-section of the expansion nozzle
  • Fuel line merges into a fuel supply end portion, which opens into the pre-combustion chamber.
  • Partial combustion takes place, which raises the temperature level to reduce the ignition delay time.
  • the constriction between the pre-combustion chamber and the main combustion chamber prevents vortices that would contact hot particles with an inner wall of the expansion nozzle in this area and would promote corrosion.
  • an expansion area connects to the main combustion chamber.
  • the clear cross section of the main combustion chamber to the adjoining expansion area so that the clear cross section in a transition between the main combustion chamber and the
  • Cross-section which is known in expansion or Laval nozzles, ensures that a discharged from the expansion nozzle fluid, which forms the support mass, flows as parallel as possible to a longitudinal axis of the expansion nozzle and that sudden changes in the flow state, so-called.
  • the light cross-section is not extended to collisions of ash particles with an inner wall of the expansion nozzle in the
  • Rejuvenation of the clear cross section in the region of the transition can then still - be realized in fluid form by at least one fluid, preferably gas, particularly preferably nitrogen-enriched fluid or gas, in the region of the transition under relatively high pressure to the center of the clear cross section is passed, so that forms a fluid flow, the function of the rejuvenation of the clear
  • oxygen or oxygen-enriched air in particular being able to be provided as the oxidizer.
  • the oxygen or the oxygen-enriched air can be present in liquefied form or in
  • gaseous form so at least as a fluid. It should be noted that the gaseous oxidizer is due to in operation
  • Nitrogen oxide production during combustion reduced or minimized.
  • At least one Oxidator strig is provided, which is rigidly connected to the rotor and is preferably formed in the rotor, wherein the at least one
  • Oxidator at least partially radially extends up to the rocket engines to press in the operating state, an oxidizer by means of the present by the rotation of the rotor centrifugal force in the rocket engines. That it may be dispensed with additional, known from the prior art, facilities to the oxidizer in the
  • the achievable high pressures of the oxidizer can also be used to decompose the fuel into very small particles or droplets.
  • it is in a particularly preferred embodiment of the
  • Oxidatorzuchtendabitese and the openings are designed such that in the operating state, the oxidizer at a pressure of at least 1500 bar, preferably from 2000 to 6000 bar, more preferably from 2500 bar to 5000 bar, can be introduced in the direction of the constriction in the pre-combustion chamber to the
  • the oxidator is thus at high pressure in the region of the constriction, so to speak, from several sides in a
  • Pre-combustion chamber and main combustion chamber serves as it were as a guide for the radial or the center of the clear
  • the diameter of the thus comminuted fuel particles or droplets is typically less than or equal to 10 ym.
  • Oxidatorzuchtendabitese substantially star-shaped and preferably aligned with the central region.
  • the course of the Oxidatorzuchtendabitese is preferably pointing to a longitudinal axis of the expansion nozzle, which longitudinal axis lies in a plane of the rotor or in a plane normal to the rotation axis and is substantially tangential (to the rotor), and run
  • the achieved small particle size of the fuel contributes to an enormous efficiency increase of the combustion.
  • coal can be in the form of larger grains, which
  • At least one Oxidatortechnisch in Oxidatorring admiren opens, each extending annularly around one of the rocket engines in the region of a transition from the main combustion chamber to an expansion region of the expansion nozzle, and that the Oxidatorringtechnischen each in channels in a wall of the respective expansion nozzle open, which channels extend from the region of the transition in the region of the constriction of the respective expansion nozzle.
  • This arrangement is advantageous in two respects. For one thing, the
  • Oxidizer in the Oxidatorring technische-in-semiconductor
  • the main combustion chamber is cooled by the oxidizer, whereby the combustion chamber material, in particular the material of the main combustion chamber, is protected from oxidation.
  • the combustion chambers are formed of a temperature-resistant alloy with oxidation-resistant material and a ceramic coating
  • the ceramic coating in particular, a hard oxide ceramic such as e.g. Al O (alumina), in question.
  • the temperature resistant alloy e.g. a
  • Ceramic coating is biased by a sheath of the superalloy to pressure.
  • the oxygen-rich fraction when used as an oxidizer, the oxygen-rich fraction no longer has to be in liquid form
  • Air Z erkettsech a about the rotation axis rotatable, rigidly connected to the rotor vessel for the liquefied air comprises, in which vessel in the operating condition by rotating a pressure gradient can be formed in the liquefied air to produce the oxygen-rich fraction as by means of fractional crystallization, that the oxygen-rich fraction in the vessel is arranged radially further away from the axis of rotation than the nitrogen-rich fraction, and that at least one
  • Oxidator for the derivation of the oxygen-rich fraction and at least one nitrogen line for the derivation of the nitrogen-rich fraction are provided, wherein the
  • Oxidator leads into a region of the vessel, which is arranged radially further away from the axis of rotation than a region of the vessel into which opens the nitrogen line.
  • the liquefied air is at a certain level
  • Rotary axis an increased nitrogen content.
  • diverting the liquefied air (in the axial direction, parallel to the axis of rotation) from the respective area can be skimmed off according to the oxygen-rich or the nitrogen-rich proportion.
  • the operating state of the rotor rotation can be used in the present case to generate the pressure gradient or for driving the air Z erlegungshim, which allows a seamless implementation of the air separation unit.
  • the air separation unit may include a per se known air liquefaction device, which in turn is connected upstream of an axial compressor or air inlet.
  • the nitrogen-rich fraction which according to the above can be in liquid or gaseous form, can advantageously be used as a film jacket between the
  • Combustion gases and the inner wall of the main combustion chamber are mixed back to better protect the material of the main combustion chamber or the inner wall from damage, in particular by corrosion.
  • Carriage of the nitrogen-rich fraction can be dispensed under high pressure. Therefore, it is at a special preferred embodiment of the device according to the invention provided that at least one nitrogen line is provided for discharging at least part of the nitrogen-rich portion from the air Z unit, which is rigidly connected to the rotor and preferably in the rotor
  • Nitrogen at least partially extends radially up to the rocket engines to press in the operating state, the nitrogen-rich fraction by means of the centrifugal force present in the rocket engines by the rotation of the rotor, and that the at least one nitrogen line opens into nitrogen ring lines, each ring around one of the rocket engines in the area one
  • Expansion region of a main combustion chamber of the expansion nozzle wherein in the main combustion chamber, in particular in the expansion region, a plurality of openings are provided for the nitrogen-rich fraction and the respective nitrogen ring line opens into the openings. Accordingly, the
  • Rocket engines (n) are derived. Possibly. However, it may be beneficial, the mass of the exhaust gas in relation to
  • the nitrogen-rich portion of the rocket engines are fed, the remaining nitrogen-rich content can be outside be deducted or blown off. It may be noted that the steam turbine generator always withdraws energy from the exhaust gas, but the amount of heat proportional to the
  • a generator with the device according to the invention can be operatively connected to the
  • the generator or a rotor of the generator can be non-rotatably connected to the rotor of the device.
  • a frequency converter may be provided which is co-optimized with the generator.
  • a system for generating electrical energy comprising a device according to the invention and the generator.
  • inventive device or the system according to the invention can be used to further increase efficiency with a
  • downstream steam turbine can be combined to form a combination process - analogous to the known gas and steam process.
  • the rocket engines or rotating burners can be used for this purpose, e.g. in the combustion chamber of an existing one
  • Fig. 1 is a schematic representation of a rotor of a
  • Fig. 2 is a schematic representation of a sectional view through a rocket engine of the device according to the invention, wherein a longitudinal axis of
  • Rocket engine is in the cutting plane
  • Fig. 3 is a schematic representation of an inventive
  • a rotor 10 of a device according to the invention for driving a generator 3 for generating electrical energy in plan view is shown schematically.
  • the rotor 10 is about a rotation axis 5, which in Fig. 1 normal to the
  • Drawing plane is, rotatably mounted.
  • Rocket engines 14 circumferentially arranged.
  • Fig. 1 is a circle 25 with radius D for clarity of illustration
  • Embodiment eight rocket engines 14 are arranged regularly and at equal angular intervals to each other along this circle 25.
  • Rocket engines 14 and surrounding the rotor 10 surrounding 26 dashed lines.
  • the circle 25 and the circumference 26 are centered about the axis of rotation 5, wherein the radius 26 clearly has a larger radius than the circle 25.
  • the rocket engines 14 are rigid with the rotor 10
  • each rocket engine 14 is arranged so that its longitudinal axis 22 substantially tangentially touches the circle 25.
  • the rocket engines 14 have open on one side combustion chambers, each having a corresponding opening 27 of the combustion chamber along the longitudinal axes 22 and in the view of FIG. 1 counterclockwise.
  • Rocket engines is typically 0.15 m.
  • the combustion chambers of the rocket engines 14 are in the illustrated embodiment as expansion nozzles 9, which are sometimes referred to as Laval nozzles, formed and correspondingly have a main combustion chamber 9.11 and an adjoining expansion area 9.12 on.
  • the illustrated embodiment includes a pre-combustion chamber 9.10 to the main combustion chamber 9.11, see. Fig. 2.
  • a clear cross section of the expansion nozzles 9 has a constriction 15 between the pre-combustion chamber 9.10 and the
  • Rocket engines 14 from the openings 27 support mass and thus drive the rotor 10 rotationally by the
  • Rocket engines 14 rotate along the circle 25 about the axis of rotation 5.
  • the rotor 10 in particular on the
  • Conversion of the electrical energy generated by the generator 3 to the mains frequency of a low-voltage power network can be carried out in a manner known per se, e.g. done electronically, especially using frequency converters.
  • the rotor 10 may be by means of the rocket engines 14 in the operating condition with operating speeds, corresponding to an integral multiple of the line frequency and in the range of 9,000 min -1 to 36,000 min -1, for example at 18,000 min -1, are driven.
  • Rocket engine 14 at the above-mentioned radial distance D - corresponds approximately to the exhaust gas velocity and the velocity of the ejected support mass, so that the energy release is maximized in a single-stage expansion process, such. 1500 m / s.
  • One possible parameter combination is e.g.
  • the rotor 10 is designed to be both light and high-strength, the structure of the rotor 10, in particular in regions of support structures 9.7, comprising carbon fibers in a heat and pressure-resistant matrix of silicon carbide.
  • the carbon fibers run in the support structures 9.7 parallel to the longitudinal extent of the respective support structure 9.7 and thus coarse - in the illustrated Embodiment up to about 22 ° - parallel to the centrifugal forces occurring.
  • Rocket engines 14 are arranged arranged in an exhaust space 4.
  • the exhaust gas space 4 is through a housing 7 (off
  • Non-contact seal 8 is provided, which allows the gas-tight passage of the rotor 10 through the housing 7.
  • an inner radial portion 23 of the rotor 10 is arranged, wherein the working space 6 can be evacuated to allow the operating state of the device, the arrangement of the inner radial portion 23 of the rotor 10 in vacuum. As can be seen in particular from Fig. 3, is located in
  • Stability of the device according to the invention affects.
  • the supply line 13 opens into a plurality of fuel lines 13 ', which are circular in the region of the axis of rotation 5 or merge in a central circular recess 28. Opposite the working space 6, the fuel line 13 'or the recess 28 in said mouth region or in the region of the axis of rotation 5 by means of a gas or vacuum-tight
  • the fuel lines 13 ' are rigidly connected to the rotor 10 and preferably formed in the rotor 10.
  • Fuel is pressed by means of the present by the rotation of the rotor 10 centrifugal force in the rocket engines 14.
  • the fuel is using an oxidizer, which in the illustrated embodiment to
  • oxygen-enriched air is burnt.
  • oxygen means the oxidizer, unless explicitly stated otherwise, the oxidizer may be in the liquefied or gaseous state.
  • the oxidizer is supplied to the rocket engines 14 with the aid of centrifugal force.
  • Exemplary embodiments are oxidizer lines 12
  • the Oxidator Appendix 12 extend radially to the
  • Oxidator glacial to one of the rocket engines 14 in the region of a transition 16 of the main combustion chamber 9.11 to
  • Expansion area 9.12 of the expansion nozzle 9 run.
  • the Oxidator ring lines 9.2 each open into channels 9.9 in a wall of the respective expansion nozzle 9, which channels 9.9 extend from the region of the transition 16 into the region of the constriction 15 of the respective expansion nozzle 9. This results in a regenerative cooling of the main combustion chamber 9.11 of
  • Constriction 15 provided a plurality of openings 17 for the oxidizer, in which openings 17 Oxidatorzuchtendabête 18 open, wherein the channels in the Oxidatorzuchtendabête 18
  • Openings 17 are designed such that, in the operating state, the oxidizer is pressurized to at least 1500 bar,
  • the Oxidatorzuchtendabchnitte 18 together with openings 17 thereto each star-shaped and the constriction 15 may be arranged facing.
  • the device according to the invention comprises in
  • Air separation unit 2 (shown for clarity in Fig. 3 along the axis of rotation 5 shown interrupted, wherein the interruption is indicated by the two broken lines), which is coupled to the rotor 10.
  • Air separation unit 2 in turn, includes a per se known air liquefaction device (not shown, can in particular in the region not shown
  • the air Z erkettstician 2 is provided in order to divide the liquefied air into a nitrogen-rich fraction and an oxygen-rich fraction and to use the oxygen-rich fraction as the oxidizer, wherein the oxidizer, as already mentioned, may not necessarily be in liquid form, but can also be used in gaseous form.
  • the air erlegungsech Z 2 comprises a rotatable around the rotation axis 5, fixed to the rotor 10 connected container 19 for the liquefied air.
  • the vessel 19 is formed in the operating condition by rotation, a pressure gradient in the liquefied air to produce by means of fractional crystallization, the oxygen-rich fraction so that the
  • oxygen-rich fraction in the vessel 19 is arranged radially further away from the axis of rotation 5 than the nitrogen-rich fraction.
  • nitrogen-rich fraction may be in gaseous form
  • the Oxidator endeavoren 12 for discharging the oxygen-rich
  • Oxidator 12 lead into a region of the vessel 19, which is located radially further away from the axis of rotation 5 as a region of the vessel 19, in which the nitrogen lines 11 open.
  • the nitrogen-rich fraction is shown in the
  • Embodiment - at least partially - also fed to the rocket engines 14, by one
  • the nitrogen pipes 11 are not only rigidly connected to the rotor 10 and preferably formed in the rotor 10, but extend radially to the
  • Rocket engines 14 to operate in the operating state
  • the nitrogen lines 11 open into nitrogen ring lines 9.3, which extend in each case annularly around one of the rocket engines 14 in the expansion region 9.12 of the main combustion chamber 9.11 of the expansion nozzle 9. In the respective main combustion chamber 9.11, in particular in
  • a plurality of openings 20 are provided for the nitrogen-rich portion, wherein the
  • respective nitrogen ring line 9.3 opens into the openings 20, cf. Fig. 2. More specifically, the supply of the nitrogen-rich portion to the openings 20 in that region, which lies between the constriction 15 and the transition 16, via internal
  • Nitrogen ring lines 9.3 (fluid) are connected. That In this area, the inner nitrogen ring pipes 9.8 open into the openings 20.
  • Combustion chambers 9.10, 9.11, 9.12 are these in the shown
  • the ceramic coating 9.6 is biased by the metal shell 9.5 to pressure.
  • a throttle 29 may be provided in each case.
  • the throttles 29 are in

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

La présente invention concerne un dispositif d'entraînement d'un générateur (3) pour générer de l'énergie électrique. Le dispositif comprend un rotor (10) logé rotatif autour d'un axe de rotation (5), plusieurs moteurs-fusées (14) avec des chambres de combustion ouvertes d'un côté sont disposés sur le pourtour du rotor (10) à une distance radiale (D) de l'axe de rotation et sont reliés rigidement au rotor (10) pour faire tourner, dans un état de fonctionnement, le dispositif autour de l'axe de rotation et pour ainsi entraîner de manière rotative le rotor (10) autour de l'axe de rotation. Selon l'invention, la structure du rotor (10) comprend des fibres en carbone dans une matrice résistante à la chaleur et à la pression, de préférence en carbure de silicium. Plus de 50 % des fibres en carbone sont disposées de sorte que la fibre en carbone concernée est placée obliquement à une tangente, la tangente passant par un point sur la fibre en carbone concernée et est tangente en ce point à un cercle auxiliaire. Le cercle auxiliaire est centré autour de l'axe de rotation, est disposé dans un plan perpendiculaire à l'axe de rotation et passe par le point.
PCT/EP2019/059875 2018-04-18 2019-04-17 Dispositif d'entraînement d'un générateur Ceased WO2019201969A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ATA50328/2018A AT520831B1 (de) 2018-04-18 2018-04-18 Vorrichtung zum antrieb eines generators
ATA50328/2018 2018-04-18

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WO2019201969A1 true WO2019201969A1 (fr) 2019-10-24

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116122918A (zh) * 2022-12-22 2023-05-16 中国科学院工程热物理研究所 一种闭式布雷顿循环变频发电装置

Citations (5)

* Cited by examiner, † Cited by third party
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