CN112065607A - Combustion chamber, engine, method and application - Google Patents
Combustion chamber, engine, method and application Download PDFInfo
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- CN112065607A CN112065607A CN202010989078.6A CN202010989078A CN112065607A CN 112065607 A CN112065607 A CN 112065607A CN 202010989078 A CN202010989078 A CN 202010989078A CN 112065607 A CN112065607 A CN 112065607A
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- combustion chamber
- combustor
- cavity
- metal coil
- chamber body
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- 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
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention relates to a combustion chamber, an engine, a method and application, comprising a combustion chamber body, wherein the combustion chamber body comprises a first cavity and a second cavity which are arranged in parallel, one end of the first cavity and one end of the second cavity are connected through a connecting cavity, the other end of the first cavity and the other end of the second cavity are respectively provided with a spray pipe, the spray pipes are communicated with the inner space of the combustion chamber body, metal coils distributed along a spiral line are wound on the peripheries of the combustion chamber body and the spray pipes, the metal coils can be connected with a power supply, and the combustion chamber body is also communicated with a fuel pipe.
Description
Technical Field
The invention relates to the technical field of rockets, in particular to a combustion chamber, an engine, a method and application.
Background
The statements herein merely provide background information related to the present disclosure and may not necessarily constitute prior art.
The combustor is a device in which fuel or propellant is burned to generate high temperature combustion gas, and is an important part of a gas turbine engine, a ramjet engine, a rocket engine, and the like.
The inventor finds that the existing combustion chambers can not effectively avoid the problem of overhigh combustion chamber temperature, which leads to higher requirements on the manufacturing materials of the combustion chambers, increases the processing cost of the combustion chambers, and limits the development of engines, thereby limiting the possibility of reusing rocket engines.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a combustion chamber, which can effectively solve the problem of overheating of the combustion chamber and a spray pipe, reduce the requirements on the manufacturing materials of the combustion chamber and reduce the production cost of the combustion chamber.
In order to achieve the purpose, the invention adopts the following technical scheme:
in a first aspect, an embodiment of the present invention provides a combustion chamber, including a combustion chamber body, where the combustion chamber body includes a first cavity and a second cavity that are arranged in parallel, one end of the first cavity and one end of the second cavity are connected by a connection cavity, the other end of the first cavity and the other end of the second cavity are both provided with a nozzle, the nozzle is communicated with an internal space of the combustion chamber body, metal coils distributed along a spiral line are wound around peripheries of the combustion chamber body and the nozzle, the metal coils can be connected with a power supply, and the combustion chamber body is further communicated with a fuel pipe.
In combination with the first aspect, an embodiment of the present invention provides a possible implementation manner of the first aspect, and the nozzle is of a conical structure, and the end with a smaller area is fixedly connected with the combustion chamber body.
In combination with the first aspect, an embodiment of the present invention provides a possible implementation manner of the first aspect, where the plurality of metal coils are provided, and each of the metal coils is connected to a power supply.
In combination with the first aspect, embodiments of the present invention provide a possible implementation manner of the first aspect, wherein the distribution density of the metal coils on the periphery of the nozzle is greater than that of the metal coils on the periphery of the combustor body.
In combination with the first aspect, an embodiment of the present invention provides a possible implementation manner of the first aspect, and the cross sections of the first chamber, the second chamber, and the connecting chamber are all circular.
In combination with the first aspect, an embodiment of the present invention provides a possible implementation manner of the first aspect, the combustion chamber body is made of a steel material or an alloy material, an outer side surface of the combustion chamber body is coated with an insulating and heat-insulating layer, and an outer periphery of the metal coil is wrapped with an insulating sleeve.
In combination with the first aspect, an embodiment of the present invention provides a possible implementation manner of the first aspect, and the metal coil is made of a copper coil.
In a second aspect, embodiments of the present invention provide a method of operating a combustion chamber: the fuel in the combustion chamber body burns, and the metal coil circular telegram produces magnetic field, and the plasma and the ion group that the fuel burning produced are produced to the magnetic field that produces are restrainted, reduce the particle count with combustion chamber body and spray tube cavity wall collision, and then reduce the heat conduction efficiency to the combustion chamber body.
In a third aspect, an embodiment of the present invention provides an engine incorporating the combustion chamber of the first aspect.
In a fourth aspect, embodiments of the present invention further provide a liquid rocket provided with the engine of the third aspect.
The invention has the beneficial effects that:
1. according to the combustion chamber, the metal coil connected with the power supply is wound on the periphery of the combustion chamber body, so that a magnetic field with certain strength can be generated in the combustion chamber body, plasma and ion clusters generated during combustion are bound, the number of particles colliding with the wall of the combustion chamber body is reduced, the heat conduction efficiency is further reduced, the temperature of the combustion chamber body is effectively controlled, the requirement on the manufacturing material of the combustion chamber body is reduced, and the possibility of recycling the rocket is increased.
2. According to the combustion chamber, the spray pipe is the position which is most easily damaged due to high temperature, and the distribution density of the metal coils on the periphery of the spray pipe is greater than that of the metal coils on the periphery of the combustion chamber body, so that stronger magnetic field binding force is generated on the spray pipe, the spray pipe is guaranteed not to be damaged by high temperature, the using amount of the metal coils is reduced to the greatest extent, and the cost is saved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the application and, together with the description, serve to explain the application and are not intended to limit the application.
FIG. 1 is a schematic view of the overall structure of embodiment 1 of the present invention;
FIG. 2 is a schematic view of an assembly of a metal coil and a first chamber according to embodiment 1 of the present invention;
FIG. 3 is a graph showing the ratio of the magnetic field intensity to the number of ions in the wall of the collision chamber in example 2 of the present invention;
the fuel pipe comprises a first cavity, a second cavity, a first spray pipe, a second spray pipe, a metal coil and a fuel pipe, wherein the first cavity is 1, the second cavity is 2, the first spray pipe is 3, the second spray pipe is 4, the metal coil is 5, and the fuel pipe is 6.
Detailed Description
It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
For convenience of description, the words "up", "down", "left" and "right" in the present invention, if any, merely indicate correspondence with up, down, left and right directions of the drawings themselves, and do not limit the structure, but merely facilitate the description of the invention and simplify the description, rather than indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention.
As introduced by the background art, the temperature is higher in the working process of the existing combustion chamber, the requirement on the combustion chamber material is higher, and the manufacturing cost of the combustion chamber is increased.
In an exemplary embodiment of the present application, as shown in fig. 1 to 2, a combustion chamber includes a combustion chamber body, the combustion chamber body includes a first chamber 1 and a second chamber 2 arranged in parallel with each other, the first chamber and the second chamber are both circular in cross section, one end of the first chamber and one end of the second chamber are respectively provided with a first nozzle 3 and a second nozzle 4, the first nozzle is communicated with an inner space of the first chamber, the second nozzle is communicated with an inner space of the second chamber, in this embodiment, the first nozzle and the second nozzle are both in a cone-shaped structure, an end of the first nozzle with a smaller area is connected with an end of the first chamber, an end of the second nozzle with a smaller area is connected with an end of the second chamber, the first chamber and the second chamber are connected by an arc-shaped connecting chamber, and the first chamber, the second chamber and the connecting chamber constitute a U-shaped structure, the cross section of the connecting chamber is also circular.
In this embodiment, the combustion chamber body is made of steel or metal alloy material, and those skilled in the art can select corresponding material according to actual needs.
The surface coating outside the combustion chamber body forms insulating and heat insulating layer by insulating thermal insulation material, and in this embodiment, insulating thermal insulation material adopts pottery, and the heat conduction effect is poor when insulating, has reduced the heat conduction efficiency to metal coil, has reduced the material requirement to metal coil.
This external and first spray tube, the second spray tube surface winding of combustion chamber is fixed with metal coil 5, and metal coil periphery parcel has the insulating cover, metal coil distributes along the helix, in this embodiment, metal coil adopts to be made by low resistance high temperature resistant material, and is preferred, metal coil adopts copper coil to make, metal coil is connected with the power, and the power can be to the metal coil circular telegram for metal coil produces magnetic field.
In this embodiment, because the metal coil is wound on the outer surface of the combustion chamber body with the U-shaped structure, after the metal coil is electrified, a clockwise or counterclockwise magnetic field can be formed inside the combustion chamber body, so that a binding effect is generated on plasma and ion clusters generated by fuel combustion.
In this embodiment, metal coil can set up a plurality ofly according to actual need, every metal coil all needs to be connected with the power, because the spray tube diameter is less, be the easiest because receive high temperature and the part that damages, consequently spray tube periphery metal coil's distribution density is greater than combustion chamber body periphery metal coil's distribution density, in this embodiment, the helix pitch at the metal coil place of winding in the spray tube part is less than the helix pitch at the metal coil place of combustion chamber body surface winding or the number of piles of spray tube part metal coil is greater than combustion chamber body periphery metal coil's number of piles, make metal coil be greater than combustion chamber body's metal coil's distribution density at the distribution density of spray tube, stronger magnetic field force has, stronger binding power has.
In this embodiment, the power supply adopts a generator, and the generator can output direct current, so that current is introduced into the metal coil to generate a magnetic field.
The combustor body is further connected with a fuel pipe 6, the first cavity and the second cavity are communicated with one fuel pipe, and the fuel pipe is used for injecting fuel into the combustor body.
Other structures of the combustion chamber can be the existing combustion chamber structure, and the detailed description is omitted.
In the conventional combustion chamber, since the thermal motion of molecules causes ions to be ejected at various angles in the thermal motion of the molecules, the motion of gas is irregular and in various directions, so that the ions will be in various directions when no magnetic field or electric field is applied for confinement. Adopt traditional combustion chamber structure, if twine metal coil, the ion collides with the chamber wall on combustion chamber upper portion easily after the circular telegram, leads to combustion chamber upper portion chamber wall high temperature. The combustion chamber, which is thus configured as a U-shaped structure, avoids this phenomenon, as seen in a classical thermodynamic model, in which the path is straight before a particle collides, so that the particle will either collide with another particle or with the combustion chamber wall, which in turn directly causes heat conduction. The combustion chamber body adopts a U-shaped structure, according to the right-hand spiral rule, the winding direction of the metal coil enables the magnetic field in the chamber to be clockwise (or anticlockwise), most of the magnetic field exists in the coil, the influence of the marginal effect is reduced, and in the physical point of view, the integral magnetic field result of any simple closed surface is 0, so that in the example that the energizing current of the cylindrical coil is I, if the direction of the magnetic field in the cylindrical coil is s, the magnetic field in the cylindrical coil is in the s directionThe magnetic field direction of the coil should be-s in the vertical plane of (a). If a closed curve is defined as a sphere with a radius R, the internal magnetic field integral should be 0 even when R is very large. When R approaches positive infinity, it can be considered that the point of the integral in the-s direction times the angle is 0 degrees. Because the integral of the magnetic field inside it is finite and the magnetic field | B |, is 0 as the distance approaches infinity, the decay of the magnetic field outside along the radius length is faster than 1/r2And because the magnetic fields at the two sides are opposite, a part of the external magnetic field is cancelled according to the superposition principle, so that the magnetic fields outside the first chamber and the second chamber are very small. And with the arrangement, the phenomenon that the magnetic field is vertical to the wall of the cavity can not occur, so that ions can be better bound, the number of colliding walls is reduced, the directions of the magnetic fields of the first chamber and the second chamber are opposite, so that the rotating directions of the charged ions are opposite, the angular momentum generated by the rotation of the ions can be offset from the statistical view, the gases of the first chamber and the second chamber are the same, the number of generated ions is also similar, the ions in one chamber can generate one-direction rotation due to the magnetic field, and the one-direction rotation brings one angular momentum. Because of conservation of angular momentum, the engine would require an opposite angular momentum to neutralize. The ions in the other chamber will also rotate due to the magnetic field, but because the magnetic field is opposite, the direction of rotation is opposite, and therefore the angular momentum is opposite. The angular momentum of the engine as a whole is 0, so the angular momentum is cancelled out.
Example 2:
this example discloses a method of operating the combustor of example 1, wherein fuel is injected into the combustor through the fuel pipe to burn, and the high temperature combustion reaction generates ion clusters and plasma, such as the combustion reaction of hydrogen, which generates some OH species-Or O2-When the generator energizes the metal coil, a magnetic field is generated in the combustion chamber body, the first spray pipe and the second spray pipe, the generated ion clusters and the plasma are bound by the magnetic field, the number of particles colliding with the wall of the combustion chamber body, the wall of the first spray pipe and the wall of the second spray pipe is greatly reduced, and further the heat conduction efficiency to the combustion chamber body, the first spray pipe and the second spray pipe is reduced, as shown in fig. 3In the particle collision-free simulation of the python program, the inner diameter of the combustion chamber is set to be 0.4m, the temperature is 4000K, the ion number is 1000, when a 0.006T magnetic field is applied, the ion number of the ion collision chamber wall can be controlled to be 10%, and if the magnetic field is not applied, the ion number of the collision chamber wall is close to 100%, so that the ion collision number can be reduced by applying the magnetic field, the temperature of the combustion chamber is reduced, the requirement on the processing materials of the combustion chamber is further reduced, the production cost is reduced, and the possibility of recycling is increased.
Example 3:
in the present embodiment, the combustion chamber described in embodiment 1 is mounted, and other structures of the engine may be the structures of the existing engines, and the specific structures thereof will not be described in detail herein.
Example 4:
this embodiment provides a liquid rocket, which is equipped with the engine described in embodiment 3, and other structures of the liquid rocket may be conventional structures, which will not be described in detail herein.
In operation, the magnetic field should be turned off or maintained at a very low level at times when no fuel is being injected. After the fuel is injected into the combustion chamber and the combustion reaction has begun to proceed smoothly, the magnetic field is increased until the magnetic field reaches a set intensity.
After the rocket is finished on the ground, the rocket will maintain the magnetic field to lift off. The magnetic field will be turned off when the stage of the rocket is detached.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, it is not intended to limit the scope of the present invention, and it should be understood by those skilled in the art that various modifications and variations can be made without inventive efforts by those skilled in the art based on the technical solution of the present invention.
Claims (10)
1. The utility model provides a combustion chamber, its characterized in that, includes the combustion chamber body, and the combustion chamber body includes parallel arrangement's first cavity and second cavity, and first cavity and second cavity one end are connected through connecting the cavity, and the other end all is provided with the spray tube, and spray tube and combustion chamber body inner space intercommunication, combustion chamber body and spray tube periphery winding have along the metal coil of helix distribution, and metal coil can be connected with the power, and the combustion chamber body still communicates with the fuel pipe.
2. A combustor according to claim 1, wherein the lance is of a conical configuration with the smaller area end thereof being fixedly connected to the combustor body.
3. A combustion chamber as claimed in claim 1, wherein a plurality of said metal coils are provided, each of said metal coils being connected to a power source.
4. The combustor of claim 1, wherein the lance outer perimeter metal coils are distributed at a density greater than the density of the combustor body outer perimeter metal coils.
5. A combustion chamber according to claim 1, wherein the first chamber, the second chamber and the connecting chamber are circular in cross-section.
6. The combustor of claim 1, wherein the combustor body is made of steel or alloy material, the outer side surface of the combustor body is coated with an insulating and heat-insulating layer, and the outer periphery of the metal coil is wrapped with an insulating sleeve.
7. A combustion chamber as claimed in claim 1, characterized in that the metal coil is made of copper.
8. A method of operating a combustor as claimed in any one of claims 1 to 7, wherein the fuel is combusted in the combustor body and the metal coil is energised to produce a magnetic field which confines the plasma and clusters of ions generated by the combustion of the fuel to reduce the number of particles which collide with the combustor body and the wall of the lance wall and thereby reduce the efficiency of heat transfer to the combustor body and the lance.
9. An engine, characterized in that a combustion chamber according to any one of claims 1-7 is installed.
10. A liquid rocket characterized by the provision of the engine of claim 9.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010989078.6A CN112065607A (en) | 2020-09-18 | 2020-09-18 | Combustion chamber, engine, method and application |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010989078.6A CN112065607A (en) | 2020-09-18 | 2020-09-18 | Combustion chamber, engine, method and application |
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| CN112065607A true CN112065607A (en) | 2020-12-11 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2605051A1 (en) * | 1986-10-13 | 1988-04-15 | Pascal Louis | Semicircular rocket propulsion unit |
| DE3903602A1 (en) * | 1989-02-08 | 1990-08-09 | Erno Raumfahrttechnik Gmbh | Use of magnetic fields in rocket motors |
| CN102434414A (en) * | 2011-11-02 | 2012-05-02 | 北京理工大学 | Magnetic nozzle of variable specific impulse magnetic plasma rocket |
| DE102010063452A1 (en) * | 2010-12-17 | 2012-06-21 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Cooled system, which is exposed to hot gas flow, comprises wall and a cooling device integrated at least partially in the wall, which is made of a porous material in a partial region and is cooled by transpiration and/or effusion cooling |
| CN108869220A (en) * | 2018-06-07 | 2018-11-23 | 西安空间无线电技术研究所 | A kind of propulsion device and propulsion method for Spatial kinematics |
| CN110545612A (en) * | 2019-09-04 | 2019-12-06 | 北京航空航天大学 | Multi-stage ionization rotating magnetic field acceleration helicon plasma source |
| CN110594036A (en) * | 2019-08-23 | 2019-12-20 | 西北工业大学 | Active cooling double-nozzle support plate ejection rocket of rocket-based combined cycle engine |
-
2020
- 2020-09-18 CN CN202010989078.6A patent/CN112065607A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2605051A1 (en) * | 1986-10-13 | 1988-04-15 | Pascal Louis | Semicircular rocket propulsion unit |
| DE3903602A1 (en) * | 1989-02-08 | 1990-08-09 | Erno Raumfahrttechnik Gmbh | Use of magnetic fields in rocket motors |
| DE102010063452A1 (en) * | 2010-12-17 | 2012-06-21 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Cooled system, which is exposed to hot gas flow, comprises wall and a cooling device integrated at least partially in the wall, which is made of a porous material in a partial region and is cooled by transpiration and/or effusion cooling |
| CN102434414A (en) * | 2011-11-02 | 2012-05-02 | 北京理工大学 | Magnetic nozzle of variable specific impulse magnetic plasma rocket |
| CN108869220A (en) * | 2018-06-07 | 2018-11-23 | 西安空间无线电技术研究所 | A kind of propulsion device and propulsion method for Spatial kinematics |
| CN110594036A (en) * | 2019-08-23 | 2019-12-20 | 西北工业大学 | Active cooling double-nozzle support plate ejection rocket of rocket-based combined cycle engine |
| CN110545612A (en) * | 2019-09-04 | 2019-12-06 | 北京航空航天大学 | Multi-stage ionization rotating magnetic field acceleration helicon plasma source |
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