CN204239089U - A kind of high-efficiency environment friendly liquid propellant rocket engine - Google Patents
A kind of high-efficiency environment friendly liquid propellant rocket engine Download PDFInfo
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- CN204239089U CN204239089U CN201420729174.7U CN201420729174U CN204239089U CN 204239089 U CN204239089 U CN 204239089U CN 201420729174 U CN201420729174 U CN 201420729174U CN 204239089 U CN204239089 U CN 204239089U
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Abstract
The utility model relates to a kind of high-efficiency environment friendly liquid propellant rocket engine, comprise motor body, ignition mechanism, oxidize nozzle, reductant nozzle, cooling dilatant nozzle, firing chamber and spout, shell end and spout connection, housing is divided into burning zone from front to back successively, cooling expansion arc and acceleration contraction section, firing chamber is pipe assembling structure and is positioned at burning zone, ignition mechanism, oxidize nozzle, reductant nozzle is all just to the fuel batch mixing segment of chamber front end, and oxidize nozzle, reductant nozzle is symmetrical with ignition mechanism, at least two, cooling dilatant nozzle, contrary with the injection direction of two cooling dilatant nozzles of housing axisymmetrical distribution.The utility model simplifies the structure of rocket motor, reduce volume and weight, be in operation and on the one hand can effectively reduce engine operating temperature, effectively raise ability and the utilization ratio of the potential energy kinetic energy in fuel heating efficiency and fuel, cooling dilatant gasification inflation process on the other hand.
Description
Technical field
The utility model relates to a kind of high-efficiency environment friendly liquid propellant rocket engine, belongs to rocket motor technical field.
Background technique
The motor of all kinds of high speed aerospace crafts used at present is generally divided into liquid fuel jet engine and solid fuel jet engine, presently used liquid fuel jet engine mainly relies on fuel vigorous combustion within the engine, produce a large amount of high pressure, high-temperature gas also sprays at a high speed from engine terminus, thus provide driving force for equipment, such engine structure has had the applicating history of centuries, in use find, the liquid fuel of this kind of motor is before entering firing chamber, all need to be allowed for access combustion chambers burn after gasification, thus it is complicated to result in pipeline structure in motor, motor volume and weight increase, too increase production technology and the regular maintenance difficulty of motor simultaneously, improve production and the user cost of motor, the high temperature and high speed wake flame gas that the liquid fuel jet engine of current use simultaneously operationally sprays also contains amount of heat, these heats reduce fuel availability on the one hand, also be unfavorable for that infrared signature hidden by motor on the other hand, be unfavorable for that it is infrared, ultraviolets etc. see that to take aim under equipment hidden, the use of unfavorable and military class aircraft is disguised, simultaneously also material is used to propose higher requirement to motor, also the cost of motor is further increased, therefore for above deficiency, in the urgent need to developing a kind of brand-new liquid fuel jet engine.
Summary of the invention
For the deficiency that prior art exists, the utility model provides a kind of and reduces the high-efficiency environment friendly liquid propellant rocket engine that fuel consumption improves engine operating efficiency, simplify the structure of rocket motor, effectively reduce engine operating temperature, effectively raise the thermal energy kinetic energy ability in fuel heat utilization ratio and fuel combustion inflation process and utilization ratio, reduce fuel consumption and user cost, decrease Enviromental pollutants and hot driving.
To achieve these goals, the utility model realizes by the following technical solutions:
A kind of high-efficiency environment friendly liquid propellant rocket engine, it is characterized in that: described high-efficiency environment friendly liquid propellant rocket engine comprises motor body, ignition mechanism, oxidize nozzle, reductant nozzle, cooling dilatant nozzle, firing chamber and spout, described shell end and spout connection, described housing is divided into burning zone, cooling expansion arc from front to back successively and accelerates contraction section, described firing chamber is pipe assembling structure and is positioned at burning zone, and coaxially distributes in housing; Form by-pass air duct between described firing chamber and inner walls, and described chamber front end separately establishes taper fuel batch mixing segment; Described ignition mechanism, oxidize nozzle, reductant nozzle are all just to the fuel batch mixing segment of chamber front end, and oxidize nozzle, reductant nozzle are symmetrical with ignition mechanism; At least two described, cooling dilatant nozzle, is distributed in the inner walls of by-pass air duct inlet; Described cooling dilatant nozzle spray direction points to spout direction, and consistent with the tangent direction cooling the housing that dilatant nozzle is point of contact; Contrary with the injection direction of two cooling dilatant nozzles of housing axisymmetrical distribution.
Further, described housing is by alloy base material and be coated on the carbon fiber wire of base material outside, glass fiber forms.
Further, described oxidize nozzle, reductant nozzle and ignition mechanism are 0 ° of-90 ° of angle.
Further, the cooling dilatant that described cooling dilatant nozzle sprays is liquid nitrogen, liquid air.
Further, the material that described oxidize nozzle and reductant nozzle spray is liquid state.
Further, described spout is Lavalle spout.
Further, described cooling dilatant nozzle spray direction and housing axis are 0 ° of-90 ° of angle.
Further, described firing chamber and inner walls spacing are not less than 1 centimetre,
The utility model have employed direct fuel injection mode, simplify the structure of rocket motor, reduce volume and weight, and be convenient to produce and safeguard, the potential energy that before make use of INVENTIONLiquid-fueled combustion, vaporized expanding produces simultaneously, is also converted into kinetic energy by this part potential energy and is used; Cooling dilatant is adopted to absorb the heat of fuel release, realize the liquid fierce expansion to gaseous state, be in operation and can effectively reduce engine operating temperature on the one hand, contribute to the disguise improving motor and the requirement reduced engine material, effectively raise the dynamic thermal energy ability in fuel heat utilization ratio and fuel combustion inflation process and utilization ratio on the other hand, thus reach the object reducing fuel consumption, improve engine operating efficiency.
Accompanying drawing explanation
The utility model is described in detail below in conjunction with the drawings and specific embodiments;
Fig. 1 is the utility model structural representation.
Embodiment
The technological means realized for making the utility model, creation characteristic, reaching object and effect is easy to understand, below in conjunction with embodiment, setting forth the utility model further.
A kind of high-efficiency environment friendly liquid propellant rocket engine as described in Figure 1, comprise motor body 1, ignition mechanism 2, oxidize nozzle 3, reductant nozzle 4, cooling dilatant nozzle 5, firing chamber 6 and spout 7, housing 1 end is communicated with spout 7, and housing 1 is divided into burning zone 8, cooling expansion arc 9 from front to back successively and accelerates contraction section 10.
In the present embodiment, described firing chamber 6 is pipe assembling structure and is positioned at burning zone 8, and coaxially distribute in housing 1, itself and housing 1 inwall spacing are not less than 1 centimetre, by-pass air duct 11 is formed between firing chamber 6 and housing 1 inwall, and taper fuel batch mixing segment 12 is separately established in front end, firing chamber 6, ignition mechanism 2, oxidize nozzle 3, reductant nozzle 4 is all just to the fuel batch mixing segment 12 of front end, firing chamber 6, and oxidize nozzle 3, reductant nozzle 4 is symmetrical with ignition mechanism 2, 5 at least two, cooling dilatant nozzle, be distributed on housing 1 inwall of by-pass air duct 11 inlet, its injection direction points to spout 7 direction, and it is consistent with the tangent direction cooling the housing 1 that dilatant nozzle 5 is point of contact, and the injection direction of this cooling dilatant nozzle 5 and housing 1 axis are 0 ° of-90 ° of angle, and contrary with the injection direction of two cooling dilatant nozzles 5 of housing 1 axisymmetrical distribution.
In the present embodiment, described housing 1 is by alloy base material and be coated on the carbon fiber wire of base material outside, glass fiber forms, and spout is Lavalle spout.
In the present embodiment, described oxidize nozzle 3, reductant nozzle 4 and ignition mechanism 2 are in 0 ° of-90 ° of angle.
In the present embodiment, the cooling dilatant that described cooling dilatant nozzle 5 sprays is liquid nitrogen, liquid air, and the material that oxidize nozzle 3 and reductant nozzle 4 spray is liquid state.
The utility model in use, rocket liquid fuel is directly injected in the fuel batch mixing segment of chamber front end respectively by oxidize nozzle and reductant nozzle and mixes, and carry out, under ignition mechanism effect, distance combustion reaction occurs in firing chamber, cause volume of fuel undergoes rapid expansion and discharge large calorimetric, and at a high speed by cooling expansion arc and the acceleration contraction section of housing, finally from nozzle ejection to external engine.While fuel combustion, cooling dilatant nozzle ejection goes out to cool dilatant, and the inner walls high speed that the by-pass air duct that firing chamber and housing are formed is close in the shape of a spiral by cooling dilatant is in rotary moving to nozzle direction, and in the process, the heat of fuel combustion release in a large amount of absorption firing chambers, thus cooling dilatant rapid spatial expansion, and cause rotational speed to be accelerated, and finally eject from by-pass air duct, and pass through the cooling expansion arc of housing with the fuel after burning and accelerate contraction section, finally from nozzle ejection to external engine.
And while rocket motor runs; the oxygenant of rocket liquid fuel and reducing agent proportion optimizing; and guarantee that rocket fuel keeps higher level in firing chamber combustion rate; and when motor runs, the ratio of the amount of the cooling dilatant, oxygenant and the reducing agent that spray in the unit time is guaranteed to cool the mixed residuals temperatures of heat that the quantity of dilatant and oxygenant and reducing agent produces and is not less than the critical temperature cooling dilatant, oxygenant and reducing agent.
The utility model have employed direct fuel injection mode, simplify the structure of rocket motor, reduce volume and weight, and be convenient to produce and safeguard, the potential energy that before make use of INVENTIONLiquid-fueled combustion, vaporized expanding produces simultaneously, is also converted into kinetic energy by this part potential energy and is used; Cooling dilatant is adopted to absorb the heat of fuel release, realize the liquid fierce expansion to gaseous state, be in operation and can effectively reduce engine operating temperature on the one hand, contribute to the disguise improving motor and the requirement reduced engine material, effectively raise the dynamic thermal energy ability in fuel heat utilization ratio and fuel combustion inflation process and utilization ratio on the other hand, thus reach reduction fuel consumption, improve the object of engine operating efficiency.
More than describe preferred embodiment of the present utility model in detail.Should be appreciated that those of ordinary skill in the art just can make many modifications and variations according to design of the present utility model without the need to creative work.Therefore, all technician in the art according to design of the present utility model on the basis of existing technology by the available technological scheme of logical analysis, reasoning, or a limited experiment, all should by the determined protection domain of claims.
Claims (8)
1. a high-efficiency environment friendly liquid propellant rocket engine, it is characterized in that: described high-efficiency environment friendly liquid propellant rocket engine comprises motor body, ignition mechanism, oxidize nozzle, reductant nozzle, cooling dilatant nozzle, firing chamber and spout, described shell end and spout connection, described housing is divided into burning zone, cooling expansion arc from front to back successively and accelerates contraction section, described firing chamber is pipe assembling structure and is positioned at burning zone, and coaxially distributes in housing; Form by-pass air duct between described firing chamber and inner walls, and described chamber front end separately establishes taper fuel batch mixing segment; Described ignition mechanism, oxidize nozzle, reductant nozzle are all just to the fuel batch mixing segment of chamber front end, and oxidize nozzle, reductant nozzle are symmetrical with ignition mechanism; At least two described, cooling dilatant nozzle, is distributed in the inner walls of by-pass air duct inlet; The injection direction of described cooling dilatant nozzle points to spout direction, and consistent with the tangent direction cooling the housing that dilatant nozzle is point of contact; Contrary with the injection direction of two cooling dilatant nozzles of housing axisymmetrical distribution.
2. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, is characterized in that, described housing is by alloy base material and be coated on the carbon fiber wire of base material outside, glass fiber forms.
3. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, is characterized in that, described oxidize nozzle, reductant nozzle and ignition mechanism are 0 ° of-90 ° of angle.
4. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, is characterized in that, the cooling dilatant that described cooling dilatant nozzle sprays is liquid nitrogen, liquid air.
5. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, it is characterized in that, the material that described oxidize nozzle and reductant nozzle spray is liquid state.
6. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, is characterized in that, described spout is Lavalle spout.
7. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, is characterized in that, described cooling dilatant nozzle spray direction and housing axis are 0 ° of-90 ° of angle.
8. a kind of high-efficiency environment friendly liquid propellant rocket engine according to claim 1, is characterized in that, described firing chamber and inner walls spacing are not less than 1 centimetre.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420729174.7U CN204239089U (en) | 2014-11-28 | 2014-11-28 | A kind of high-efficiency environment friendly liquid propellant rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420729174.7U CN204239089U (en) | 2014-11-28 | 2014-11-28 | A kind of high-efficiency environment friendly liquid propellant rocket engine |
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| CN204239089U true CN204239089U (en) | 2015-04-01 |
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| CN201420729174.7U Expired - Fee Related CN204239089U (en) | 2014-11-28 | 2014-11-28 | A kind of high-efficiency environment friendly liquid propellant rocket engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104481733A (en) * | 2014-11-28 | 2015-04-01 | 苟仲武 | Efficient and environmentally-friendly liquid propellant rocket engine |
| CN106439224A (en) * | 2016-11-03 | 2017-02-22 | 北京航天试验技术研究所 | Pipeline butt-joint device capable of adapting to adjustment |
| CN108138697A (en) * | 2015-10-05 | 2018-06-08 | 维克托发射股份有限公司 | Improved liquid oxygen-propylene liguid rocket engine |
-
2014
- 2014-11-28 CN CN201420729174.7U patent/CN204239089U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104481733A (en) * | 2014-11-28 | 2015-04-01 | 苟仲武 | Efficient and environmentally-friendly liquid propellant rocket engine |
| CN108138697A (en) * | 2015-10-05 | 2018-06-08 | 维克托发射股份有限公司 | Improved liquid oxygen-propylene liguid rocket engine |
| CN108138697B (en) * | 2015-10-05 | 2020-11-17 | 维克托发射股份有限公司 | Improved liquid oxygen-liquid propylene rocket engine |
| CN106439224A (en) * | 2016-11-03 | 2017-02-22 | 北京航天试验技术研究所 | Pipeline butt-joint device capable of adapting to adjustment |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150401 Termination date: 20211128 |
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| CF01 | Termination of patent right due to non-payment of annual fee |