Ignition concept and combustion concept for engines and rockets; most effective or directed excitation, ignition and combustion by means of adapted electromagnetic radiation or electromagnetic waves (e.g. radio waves, microwaves, magnetic waves) and catalytic absorbers to increase the energetic efficiency and thrust

Abstract

Self-ignited burns can be increased by stimulation. External ignition must often be carried out in the combustion chamber. Often an ignition nucleus is formed electrically. This has energetic disadvantages. Required internals can be disadvantageous. Ignitions with plasma torches also need fixed internals. Electromagnetically, however, the ignition field can be widened, the combustion rate increased and the temperature changed. Due to high electrical consumption, this effective ignition has not yet been advantageous for aerospace applications. This concept should be feasible with low electrical energy requirements.

Sufficient electrical energy can be provided by turbopump, generator or thermocouple. For better coupling of electromagnetism, catalytic absorbers and possibly other particles are used. These lower the activation energy. Contactless ignition can be achieved using ceramics or metallic antennas. Ignition in the center of the combustion chamber at the highest pressures is particularly promising. The aim is to achieve combustion that is as directional as possible.

Claims

1. A method without using electromagnetic light waves and for at least one of the following processes in chemical combustion processes: Excitation or ignition, in which at least one of the aforementioned processes is used with at least one liquid propellant component in at least one of the following effective areas: before a combustion chamber (e.g. rocket engine, gas turbine, or gas turbine for turbopump), in a combustion chamber (e.g. rocket engine, gas turbine, or gas turbine for turbopump), after a combustion chamber (e.g. rocket engine, gas turbine, or gas turbine for turbopump), before a combustion chamber (turbine engine, pulse jet engine, ramjet), in a combustion chamber (turbine engine, pulse jet engine, ramjet), after a combustion chamber (turbine engine, pulse jet engine, ramjet) comprising: a variable energy input with at least one coupling of electromagnetic waves (e.g. microwaves, radio waves, X-ray waves) is used in at least one combustion-free catalytic absorber or catalytic absorber convertible by means of endothermic reaction for combustion of the remaining propellant components.

2. A method according to claim 1 comprising: In that at least one absorber as homogeneous catalyst consists of at least one element of the platinum group metals or noble metals (excluding Cu).

3. A method according to claim 1 comprising: In that the homogeneous catalyst is designed as a composite structure (e.g. fiber composite or particle composite).

4. A method according to claim 1 comprising: In that the electromagnetic absorption is selectively enhanced by at least one difference of the constituents in the following properties in a composite structure: electrochemical properties, thermal properties, electrical properties, photo-catalytic properties, porosity for electrolytes.

5. A method according to claim 1 comprising: Characterized in that at least one electromagnetic absorber is introduced into the chemical combustion process distributed in a solution, in which the solution has at least one of the following properties: oxidation-inhibiting effect, wetting properties, amphoteric properties, inducing ignition delay, exhibiting knock-inhibiting effect, freezing point lowering properties, exhibiting electrolytic properties.

6. A method according to claim 1 comprising: In that a multilayer homogeneous catalyst is designed with a ferromagnetic core shielded against electromagnetic heating.

7. A method according to claim 1 comprising: In that at least part of the propellant is magnetized or magnetizable (e.g. as ferrofluid).

8. A method according to claim 1 comprising: Characterized in that the coupling of said electromagnetic power in at least one direction or at least one particular region of the mass flow is enhanced by at least one of the following devices: Use of an electrical filter (e.g. YIG filter, Gaussian filter, Bessel filter), pulsing of the electromagnetic waves, use of a polarization filter, use of a microwave laser, use of a maser, unilateral excitation of the absorbers, magnetic alignment of the absorbers, magnetic acceleration of the absorbers.

9. A method according to claim 1 comprising: Characterized in that, in order to further reduce the required activation energy by means of electromagnetic waves for a named chemical process, at least one of the following methods is used: Preheating of the absorbers, preheating of the solution, adherent pyrotechnic agents, adherent phosphorus-containing component, multistage feed, increased heat reflection of the combustion chamber walls e.g. by means of coating of platinum or gold compounds, aligned heat reflection of the combustion chamber walls e.g. by means of spatially inclined coating of platinum or gold compounds.

10. A method according to claims 1 comprising: Characterized in that in the composite structure of fibers attached energetic components are used, which are not designed for coupling of the electromagnetic waves, e.g. by size of the fibers or shielding by means of coatings or shielding by means of further fibers.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0122] FIG. 1a shows a diagram of the initial situation.

[0123] FIG. 1b presents schematic diagrams of the basic concept of the subject invention.

[0124] FIG. 1c presents an illustration of a multistage excitation and ignition system.

[0125] FIG. 1d presents a diagram of a magnetic field for acceleration.

[0126] FIG. 2 shows a spatial presentation of homogeneous catalysts in a fiber structure with ferromagnetic properties.

[0127] FIG. 3 presents a cross-section of homogeneous catalysts in a particulate structure with ferromagnetic properties.

[0128] FIG. 4 shows a longitudinal and a transverse diagram of an embodiment with pulsation, or wavelength, and a schematic diagram, respectively.

[0129] FIG. 5 shows an illustration in the longitudinal direction to a rocket engine with an electromagnetic stimulation from the side and a schematic illustration to an electromagnetic wave.

[0130] FIG. 6 shows a longitudinal presentation of a rocket engine with a ceramic head plate and electromagnetic stimulation from above.

[0131] FIG. 7 shows a longitudinal presentation of a rocket engine with an electromagnetic stimulation from the side and shielded permanent magnets at the nozzle throat as well as a schematic presentation of an electromagnetic wave.

[0132] FIG. 8 is a longitudinal presentation of an aerospike with a ceramic coupler and includes a cross-section of a combustion chamber.

[0133] FIG. 9 presents a longitudinal presentation of a ramjet engine with ceramic coupler from the side and includes a cross-section.

[0134] FIG. 10 presents a longitudinal presentation of a Ramjet engine with ceramic coupler in the intermediate body.

[0135] The above designs are examples. Further variants are covered in the patent specification or claims (e.g. for generators for turbopumps/turbopumps).

[0136] In general, the following applies to chemical engines: The conversion of the chemically bound energy from the reducing agent (4) and oxidizer (5) supplies thermal energy. Furthermore, kinetic energy is obtained by lossy conversion. This is because it is only through the lossy thermodynamic change of state at the nozzle throat and the nozzle that a further part of this thermal energy is converted into kinetic energy in the direction of thrust (7). As a general rule, the reaction is accelerated at a high combustion temperature. The combustion temperature cannot be increased at will (e.g. due to the limited heat resistance of materials on the engine and the increasing cooling requirements).

DETAILED DESCRIPTION

[0137] FIG. 1a: Initial situation.

[0138] In the reaction, reducing agent (4) and oxidizing agent (5) react in the following reactant (11) by approach/contact. Energy is released by the chemical reaction. The thermal energy is to be understood as the movement of the particles, or the reaction products (6). Reactions take place in different directions (12), since the reaction partners (11) react freely in the combustion chamber.

[0139] FIG. 1b: Basic concept.

[0140] In this FIG. the basic concept is schematized together with an engine.

[0141] Electromagnetic waves (10) (e.g., microwaves, radio waves) can be used to selectively excite, or accelerate, the advancing motions of the catalytic absorbers (8). The catalytic absorbers (8) and the electromagnetic excitation (10) increase the reaction in the thruster system. The reaction directions (12) in the thrust direction (7) are made effective, or increased, by this excitation. Catalytic absorbers (8) are used for improved coupling. At the same time, the required activation energy of the reactants (11) decreases. Reducing agents (4) and oxidizing agents (5) react at increased reaction rates. Reaction products (6) are formed at a higher rate.

[0142] The aim is to achieve an overridingly uniform or as uniformly as possible accelerated ignition (13) in the direction of thrust (7). The combustion rate is increased. The average temperature in the combustion chamber (3) can be reduced.

[0143] FIG. 1c: Multi-stage excitation and ignition.

[0144] With multistage electromagnetic excitation and ignition (13, 16), the mixture of reducing agent (4), oxidizing agent (5) and catalysts (8) in the combustion chamber (3) can be heated more uniformly.

[0145] In front of the actual combustion chamber (3), a mixing area (2) can be placed. In the embodiment, mixing areas (2) are arranged to form resonator chambers (15). These are designed to match the wavelengths of the electromagnetic pre-excitation (16).

[0146] Reducing agents (4), oxidizing agents (5) and catalysts (8) are introduced into the mixing region (2) via a line system (1). The catalysts (8) may comprise fibers or particles, or a combination thereof. In the embodiment, fine holes are used to introduce the homogeneous catalysts (8). Alternatively, multi-channel nozzles, ejectors, hollow cone nozzles or other nozzles/bores can be used for mixing.

[0147] During mixing, the entropy increases and increasing movements are carried out. Electromagnetic excitation by means of microwaves (16) with respect to the direction of thrust causes the components at the end of the mixing zone (2) to be excited again in alignment with the direction of thrust (7) and heated proportionally.

[0148] In the combustion chamber (3), the components are ignited by a further electromagnetic excitation (13).

[0149] FIG. 1d: Magnetic field for acceleration.

[0150] Compared to the embodiment FIG. 1b, magnets (17) are additionally arranged in this embodiment. Magnets (17) (electromagnets in this case) additionally excite the propellant components consisting of reducing agent (4), oxidizing agent (5) and catalysts (8). This means that the propellant components are accelerated and ionized/or voltages are induced. Cations (18) and anions (19) are formed. This is advantageous for the electromagnetic waves (10), e.g. microwaves, since coupling of the radiation power is facilitated. In addition, the reactivity in the combustion chamber (3) increases and the kinetic power in the direction of thrust (7) is increased.

[0151] Coupling takes place predominantly through the catalytic absorbers (8).

[0152] FIG. 2 Homogeneous catalysts fiber structure with ferromagnetic properties.

[0153] In this embodiment, homogeneous catalysts are shown as absorbers in a fiber-like structure (20).

[0154] Individual fibers are bundled together to form a fiber-like structure (20). In order to specifically incorporate ferromagnetic properties, a ferromagnetic fiber (21) e.g. made of compounds of iron, nickel, cobalt is combined with a catalytic fiber (22) as absorber. The catalytic fiber (22) can be constructed of gold or an alloy containing gold (e.g. with silver or platinum). Due to the relatively high cost and maximum permissible penetration depth of the catalytic waves (microwaves), the catalytic fiber (22) has a thickness of only about 1 μm at most. The ferromagnetic fiber (21) is not designed to couple electromagnetic power due to its larger size. Other catalytic fibers (23) with different electrochemical, thermal or e.g. electrical properties can also be used specifically to supplement the catalytic absorber (22).

[0155] Advantages result from this structure. In conjunction with external electric generators, the magnetic and catalytic structures can induce a voltage at the combustion chamber for supply by means of electrical energy. The voltage is induced by movement of the magnetic structures in the combustion chamber (law of induction). Or, conversely, the magnetic and catalytic structures can be selectively accelerated, or ionized, to accelerate the reaction in the combustion chamber. In addition to the catalytic effect, or increased catalytic effect.

[0156] FIG. 3 Homogeneous catalysts.

[0157] Particle Structure with Ferromagnetic Properties

[0158] In this embodiment, a homogeneous catalyst with a non-energetic but ferromagnetic core (31) is shown.

[0159] The particle (30) is formed in the core (31) from a ferromagnetic body

[0160] (e.g. compounds of iron, nickel, cobalt). A catalytically active material (32) is applied in a layer around the core (31) (e.g. platinum, rhenium, palladium, gold, rhodium). Additional layers of alternative catalytic material (33) may also be added. The larger core (31) does not serve as an absorber for microwaves because it is shielded by the catalytic layer (32). This also results in thermal inertia, which temporarily protects the magnetic properties.

[0161] Advantages result from this structure. In conjunction with external electric generators, the magnetic and catalytic structures can induce a voltage at the combustion chamber for supply by means of electrical energy. The voltage is induced by movement of the magnetic structures in the combustion chamber (law of induction). Or, conversely, the magnetic and catalytic structures can be accelerated or ionized in a targeted manner. In this way, the reactions in the combustion chamber can be accelerated or aligned and the thrust of the engine increased.

[0162] FIG. 4: Pulsation, or wavelength.

[0163] In this embodiment, a rocket engine system is shown.

[0164] In principle, excitation by electromagnetic radiation (e.g. microwaves, radio waves) occurs over the entire oscillation (40), since this is perceived as electromagnetic waves. I.e. there is a deflection in both vibration directions. The magnetic oscillation is not decisive in this embodiment.

[0165] In the direction of thrust is excited by electromagnetic oscillation (41). The countermovement (42) is used for contact/compression with reaction partners to reduce the escape of the released chemical energy via the walls of the combustion chamber (3). The width of the combustion chamber (3) is selected to create a wavelength. A larger cross-section can also be selected by opposite coupling. Also, any multiple of the wavelength can be used.

[0166] Alternatively, for smaller engines, a combustion chamber cross section with half a wavelength can be used for excitation. To prevent feedback into the feeder/waveguide (43), the feed can be rotated by a few degrees so that the electromagnetic waves propagate in the combustion chamber.

[0167] Theoretically, radio waves with a longer wavelength and more efficient heat transfer can also be used.

[0168] An electric igniter (46) can be placed in the combustion chamber (supporting redundant system) to start combustion and additionally control the combustion chamber temperature in the start phase.

[0169] A feeder, transmitter, or waveguide (43) for coupling the electromagnetic oscillations (41 and 42) is arranged around the combustion chamber (3) near the head plate (47). The electromagnetic oscillations (41 and 42) are fed into the combustion chamber (3) via a ceramic coupler (44). The ceramic coupler (44) is electromagnetically permeable. The electromagnetic oscillations (41) are fed in the circumferential direction, i.e. rotationally symmetrically.

[0170] The catalyst (8) in particular, but also to a lesser extent the reducing agent (4) and the oxidizer (5), are energetically excited (thermally) in the desired direction by excitation. Alternatively, the combustion chamber (3) can also be excited with an adapted wavelength. If necessary, radio waves with a higher frequency can be used.

[0171] FIG. 5: Rocket engine stimulation from the side.

[0172] Compared with FIG. 4, in this embodiment catalysts (8) are additionally injected into the combustion chamber (3). Due to the high energy absorption during electromagnetic excitation (57), thin-layer metals (maximum layer thickness of a few micrometers) of the catalysts (8) are strongly heated and accelerated.

[0173] The metallic catalysts (8) are additionally thermochemically activated by the excitation (57) and thermal heating. This means that the catalytic activity increases.

[0174] FIG. 6: Rocket engine ceramic head plate, stimulation from above.

[0175] Compared to FIG. 5, in this embodiment the electromagnetic oscillations (61) are introduced from the direction of injection of the reducing agent (4), oxidizer (5) and catalyst (8) in the direction of thrust (7).

[0176] The radiation source (60) is arranged above the head plate (67) of the combustion chamber (3). The electromagnetic waves (61) are guided in a waveguide (63), or in front of an electromagnetically permeable layer (64). Electromagnetic waves (61) are coupled into the combustion chamber (3) through the electromagnetically permeable layer (64), e.g. made of a ceramic.

[0177] The direction of oscillation is perpendicular to the direction of thrust (7). The oscillation is carried out completely. This causes the particles to be excited alternately transversely in the direction of motion.

[0178] By selecting an appropriate frequency with reduced penetration depth, or larger absorbers (8), the particles are detected on one side towards the radiation source, i.e. excited on one side (65). Since the oscillations are carried out transversely to the direction of thrust (7), the effects predominantly cancel each other out, and heating occurs. The heating is toward the radiation source. A pressure gradient is created in the direction of thrust (7).

[0179] An electric or chemical igniter (46) can be placed in the combustion chamber (3) to start combustion or to additionally control the combustion chamber temperature in the start phase (supporting redundant system).

[0180] FIG. 7: Rocket engine excitation from the side and shielded permanent magnets at the nozzle throat.

[0181] Compared to FIG. 6, in this embodiment permanent magnets (70) are arranged at the nozzle throat (e.g., made of aluminum-nickel-cobalt or samarium-cobalt). The permanent magnets (70) exert an attraction on the catalytic absorbers (8), which are designed as a composite structure (FIG. 2). The composite structure is supplemented by ferromagnetic components. The catalytic absorbers (8) additionally have a ferromagnetic fiber (compounds e.g. of iron, nickel, cobalt) next to the fiber of highly active catalysts (e.g. platinum, palladium, rhodium, rhenium, gold, molybdenum). The catalytic absorbers (8) with ferromagnetic components are attracted to the permanent magnets (70). The direction of flow of the catalytic absorbers (8) is guided, controlled and accelerated in the direction of thrust (7). In the combustion chamber (3), the catalytic absorbers (8) lose their ferromagnetic properties due to the temperature and reaction even before they reach the nozzle (9). This allows the reaction products to escape unaffected through the nozzle (9) with the rest of the engine flow. The permanent magnets can be antimagnetically shielded (71) from the outside, e.g. to protect the other systems and electrics.

[0182] Alternatively, attraction by means of electromagnets is possible. For this purpose, the energy from external coils on the combustion chamber or the turbopump can be used. The magnets can also be arranged in the area, e.g., on upstream ejectors, mixing chambers, combustion chamber head, etc.

[0183] To start the combustion, or to control the combustion chamber temperature additionally in the start phase, an electric or chemical igniter (46) can be placed in the combustion chamber (supporting redundant system).

[0184] FIG. 8: Aerospikes ceramic coupler.

[0185] Aerospikes are shown in this embodiment variant.

[0186] The embodiment is designed according to FIG. 5 with electromagnetic couplers (82) on the side of the combustion chamber (83). Waveguides, or transmitters (81), are arranged accordingly around the circumference, which feed into the combustion chambers (83) via electromagnetically permeable couplers (82). The permeable couplers (82) are made of ceramic, for example.

[0187] The combustion chambers (83) are located opposite the nozzle neck (84) of the aerospikes. The electromagnetic excitation takes place in the direction of thrust (7).

[0188] The electromagnetically excited reaction of reducing agent (4), oxidizer (5) and catalysts (8) aims at a low combustion temperature at high exit velocity. The aim is to improve cooling of the aerospikes, in particular of the respective nozzle throat (84). The aim is to achieve a nozzle throat (84) with reduced necking. This can be achieved, for example, by greater reaction speed with higher mass flow. The necking of a conventional design (85) is indicated for comparison.

[0189] An electric or chemical igniter can be placed in the combustion chamber (redundant system) to start the combustion or to additionally control the combustion chamber temperature in the start phase. This is not shown in this design variant.

[0190] FIG. 9: Ramjet engine ceramic coupler from the side.

[0191] In this embodiment, an air-breathing engine with subsonic combustion is shown (ramjet).

[0192] The incoming air mass flow (95) serves as an oxidizer. Reducing agents (4) and catalytic absorbers (8) are injected into the air mass flow (95) through injectors or nozzles (104). In the ramjet engine (100), only a short time can be used for ignition (105) and combustion in the combustion chamber (103). Therefore, the combination of electromagnetic waves (40) such as microwaves with catalytic absorbers (8) is provided to inject highly active ignition nuclei into the combustion chamber (103). The combustion chamber length is to be limited to minimize friction losses.

[0193] Appropriately directed electromagnetic waves (40) (e.g. microwaves) make it possible to ignite from the outside without internals in the combustion chamber and eliminate aerodynamic resistance (e.g. from plasma flames). Electromagnetic waves (40) also offer the possibility of covering further ignition ranges (105) with more uniform combustion. Ignition areas (105) are created at maximum compression, which cannot be reached with internals, or only with difficulty (e.g. in the center of the combustion chamber).

[0194] The electromagnetic waves (40) are coupled into the combustion chamber (103) via a transmitter, e.g. a rod antenna or waveguide (101), and an electromagnetically permeable layer (102), such as a ceramic. The remaining area of the combustion chamber (103) is electromagnetically reflective to form a resonator cavity for the electromagnetic waves (40).

[0195] For the electrotechnical supply of the electromagnetic waves (40), thermocouples on the combustion chamber or outer skin, electric generators on the turbopump of the fuel supply, or electric generators on the engine duct are possible. The electric generators on the engine can be fed by induction during the movement of the catalytic absorbers (8) in the engine duct. Any additionally added metal parts or ionized combustion gases are also relevant.

[0196] To start the combustion, or to additionally control the combustion chamber temperature in the start phase, an electrical or chemical igniter can be placed in the combustion chamber as an alternative or supplement (supporting redundant system). This is not shown in this embodiment.

[0197] FIG. 10: Ramjet engine with ceramic coupler in intermediate body.

[0198] Compared to the embodiment of FIG. 9, at the Ramjet engine the electromagnetic waves (40) are coupled in by the intermediate body (111). The electromagnetic waves (40) are injected in the direction of flow.

[0199] For this purpose, corresponding devices are arranged on the downstream side of the intermediate body (111). The intermediate body (111) contains a transmitter, e.g. a rod antenna or waveguide (101), and an electromagnetically permeable layer (102), such as a ceramic, for coupling into the combustion chamber (103).

What is described herein are specific examples of possible variations on the same invention and are not intended in a limiting way. The invention can be practiced using other variations not specifically described above.