CN109899179B - Scramjet engine capable of improving supersonic combustion performance of boron-containing rich-combustion solid propellant - Google Patents
Scramjet engine capable of improving supersonic combustion performance of boron-containing rich-combustion solid propellant Download PDFInfo
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- CN109899179B CN109899179B CN201910211715.4A CN201910211715A CN109899179B CN 109899179 B CN109899179 B CN 109899179B CN 201910211715 A CN201910211715 A CN 201910211715A CN 109899179 B CN109899179 B CN 109899179B
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Abstract
The invention discloses a scramjet engine for improving the supersonic combustion performance of a boron-containing fuel-rich solid propellant, which is arranged at the lower part of an aircraft main body and comprises an engine main body and a fuel gas generator, wherein a loading space is arranged in the aircraft main body, the fuel gas generator is arranged in the loading space, the engine main body comprises an air inlet channel, an isolation section, a supersonic combustion chamber and a tail spray pipe which are sequentially communicated from front to back, the fuel gas generator comprises a combustible propellant fuel gas generator and a fuel-rich solid propellant gas generator which are mutually independent, the tail parts of the two are connected with the spray pipe and a flow guide pipe, and the airflow outlet of the flow guide pipe faces into the supersonic combustion. The scramjet engine can obviously improve the combustion performance of the boron-containing rich-combustion solid propellant under the condition of supersonic incoming flow in a short time, and can temporarily avoid the problems of large research difficulty, long research period and the like of propellant formula development and process preparation, so that the scramjet engine has high practicability.
Description
Technical Field
The invention relates to the application field of scramjet engines, in particular to a scramjet engine capable of improving the supersonic combustion performance of boron-containing rich-combustion solid propellant.
Background
The solid rocket scramjet engine is a new concept scramjet engine adopting solid propellant. While the residence of the gas flow in the supersonic combustion chamberThe time is in the order of milliseconds, and the fuel and the air can hardly complete sufficient mixing and combustion in such a short time. Especially for boron-containing combustion-rich solid propellant, due to the oxidation layer (B) on the surface of boron powder2O3) The boiling point is very high (2130K), which seriously hinders the combustion of boron in the propellant, thus seriously affecting the performance improvement of the engine. The improvement of the combustion performance of the boron-containing rich-combustion solid propellant in the supersonic combustion chamber is one of key technologies of the solid rocket scramjet, and the existing solid rocket scramjet has less research at home and abroad and less accumulated experience. In the research of improving the combustion performance of the boron-containing rich-combustion solid propellant in the solid rocket scramjet engine, various units at home and abroad mainly start to carry out related research from the aspects of propellant formula, propellant manufacturing process and the like. The development mechanism of the propellant formula and the manufacturing process is complex, so that the development period is long, and the cost is increased.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the scramjet engine improves the combustion performance of boron-containing fuel-rich solid propellant under supersonic incoming flow conditions from the aspect of combustion organization.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the utility model provides a promote super-combustion ramjet that contains boron and is burnt solid propellant supersonic combustion ability installs in aircraft main part lower part, including engine subject and gas generator, the inside loading space that has of aircraft main part, gas generator arranges in the loading space, engine subject includes from going to intake duct, isolation section, supersonic combustion chamber, the tail nozzle that communicates in proper order after, gas generator includes mutually independent inflammable propellant gas generator and the solid propellant gas generator that burns, and is equipped with inflammable propellant and the solid propellant that burns respectively in the two, inflammable propellant gas generator and the solid propellant gas generator afterbody of burning all connect the spray tube, and the honeycomb duct is all even linked to the spray tube rear portion, and it has the orifice to open on the engine main part wall at supersonic combustion chamber top, the exit end of honeycomb duct passes the diapire of the loading space in the aircraft main part and with the engine main part wall at supersonic combustion chamber top The outlet end of the guide pipe at the tail part of the inflammable propellant gas generator is positioned at the front side of the outlet end of the guide pipe at the tail part of the fuel-rich solid propellant gas generator.
Preferably, the jet direction of the air flow at the outlet end of the draft tube forms an included angle with the direction of the main air flow flowing in the supersonic combustion chamber.
Preferably, the angle between the jet direction of the gas flow at the outlet end of the flow guide pipe and the flow direction of the main gas flow in the supersonic combustion chamber is set according to the criterion that under the given supersonic flow condition, the gas flow plume jetted from the outlet of the tail flow guide pipe of the flammable propellant gas generator basically covers the gas flow plume jetted from the outlet of the tail flow guide pipe of the rich-combustible solid propellant gas generator.
Preferably, the angle of the included angle is greater than 0 degrees and less than or equal to 90 degrees.
Preferably, the propellant-rich gasifier is located at the forward end of the propellant-rich gasifier.
Preferably, the fuel-rich solid propellant is maintained in a single-sided end-face combustion within the gas generator.
The flammable propellant is jetted into the supersonic combustion chamber through the jet pipe and the guide pipe at subsonic speed or supersonic speed after being combusted in the flammable propellant gas generator.
Preferably, the combustible propellant is a solid or liquid fuel.
Compared with the prior art, the invention has the advantages that: the scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant can obviously improve the combustion performance of the rich-combustion solid propellant under the supersonic incoming flow condition in a short time through a multi-fuel combined injection structure, and temporarily solves the problems of large research difficulty and long research period of propellant formula development and process preparation, so that the scramjet engine is high in practicability.
Drawings
The invention is further described below with reference to the accompanying drawings:
FIG. 1 is a side view, partially in section, of the present invention as installed in the lower portion of an aircraft body.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention:
the scramjet engine for improving the supersonic combustion performance of the boron-containing fuel-rich solid propellant is arranged on the lower portion of an aircraft body 1 and comprises an engine body and a fuel gas generator, a loading space 12 is arranged inside the aircraft body, the fuel gas generator is arranged in the loading space 12, the engine body comprises an air inlet 2, an isolation section 3, a supersonic combustion chamber 4 and a tail nozzle 5 which are sequentially communicated from front to back, dotted lines in the figure are sectional indication lines of all parts, main air flow enters from the air inlet 2, enters the supersonic combustion chamber 4 through the isolation section 3 to be combusted, and is accelerated to be discharged through the tail nozzle 5.
The fuel gas generator comprises a combustible propellant fuel gas generator 6 and a rich-combustion solid propellant fuel gas generator 7 which are independent from each other, in the embodiment, the position of an air inlet channel is arranged in front of the super-combustion ramjet, the position of a tail nozzle is arranged behind the super-combustion ramjet, and in a loading space, the combustible propellant fuel gas generator 6 is arranged at the front end of the rich-combustion solid propellant fuel gas generator 7, so that the loading space is saved.
In the flammable propellant gas generator 6 and the rich solid propellant gas generator 7, flammable propellant and rich solid propellant are respectively arranged, in the embodiment, the flammable propellant is solid or liquid fuel, the tail parts of the flammable propellant gas generator 6 and the rich solid propellant gas generator 7 are respectively connected with spray pipes (8,10), the tail parts of the spray pipes are connected with guide pipes (9,11), the top wall of the supersonic combustion chamber is provided with spray holes 13, the outlet ends of the guide pipes penetrate through the bottom wall of a loading space in an aircraft main body and are communicated with the spray holes on the engine main body wall at the top of the supersonic combustion chamber, the flammable propellant and the rich solid propellant are respectively ignited in the flammable propellant gas generator and the rich solid propellant gas generator, and the generated high-temperature and high-pressure gas passes through the spray pipes and the outlet of the guide pipes and the outlet of the supersonic combustion chamber, and the mixed gas is jetted into the supersonic combustion chamber at a certain angle to be mixed and combusted with the main flow.
The outlet of the tail guide pipe of the combustible propellant gas generator 6 is located on the front side of the outlet of the tail guide pipe of the solid propellant gas generator 7 rich in combustible propellant, therefore, high-temperature and high-pressure gas generated after the front combustible propellant is combusted is firstly mixed and combusted with incoming flow, the temperature of the incoming flow is improved, after the temperature of the incoming flow is improved, on one hand, combustible gas phase and carbon particles in the fuel gas at the jet outlet of the solid propellant gas generator rich in combustible propellant can be rapidly combusted, more sufficient residence time is provided for the subsequent combustion of other particles, on the other hand, after the temperature of the main flow is improved, the temperature of the main flow is further improved through the combustion of combustible substances in the fuel gas rich in combustible propellant, and therefore the integral combustion efficiency.
In order to improve the uniformity of the mixing combustion of the high-temperature high-pressure gas and the incoming flow and improve the combustion efficiency, as a preferred scheme, the air flow injection direction of the outlet end of the flow guide pipe (9,11) and the flowing direction of the main air flow in the supersonic combustion chamber 4 form an included angle, as a preferred scheme, in order to improve the air flow mixing effect, the included angle is larger than 0 degree and smaller than or equal to 90 degrees, and in practical application, the included angle between the outlet air flow injection direction of the flow guide pipe (9,11) and the flowing direction of the main air flow in the supersonic combustion chamber 4 is set as a criterion, and the air flow plume sprayed from the outlet of the tail flow guide pipe of the inflammable propellant gas generator basically covers the air flow plume sprayed from the outlet of the tail flow guide pipe of the inflammable solid propellant gas generator.
In the present embodiment, the rich solid propellant maintains single-sided end face combustion in the rich solid propellant gas generator 7, further improving the combustion efficiency of the rich solid propellant.
In addition, in order to further improve the combustion efficiency, the inflammable propellant or the rich-burning solid propellant is jetted into the supersonic combustion chamber through the jet pipe and the guide pipe at subsonic velocity or supersonic velocity after being combusted in the fuel gas generator.
In this embodiment, it is preferable that the boron-containing fuel-rich solid propellant is a fuel-rich solid propellant, in practical application, the air inlet channel compresses hypersonic incoming flow, the compressed main flow passes through the isolation section, the isolation section is used for isolating the influence of combustion in the supersonic combustion chamber on the air inlet channel to prevent the air inlet channel from being inactivated, the main flow passes through the outlet of the isolation section, the static pressure and static temperature are increased, the speed is reduced, but supersonic flow is still maintained, at this time, the inflammable propellant agent is ignited in the gas generator, high-temperature and high-pressure gas generated by the inflammable propellant gas generator is injected into the supersonic combustion chamber at a certain angle through the nozzle and the flow guide pipe at the rear part of the inflammable propellant gas generator to be mixed with the main flow, and the main flow is raised at a certain temperature, almost at the same time, the boron-containing fuel-rich solid propellant is ignited in the fuel-rich solid propellant gas generator, and the boron- The gas enters the supersonic combustion chamber to be mixed and combusted with the high-temperature main flow which is assisted in combustion and has raised temperature, and the high-temperature and high-pressure gas formed by combustion expands through the tail nozzle to do work to generate thrust, so that the operation of the engine is realized.
It is to be emphasized that: the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the present invention in any way, and all simple modifications, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention are within the scope of the technical solution of the present invention.
Claims (8)
1. The utility model provides a promote super-combustion ramjet of boron-containing rich solid propellant supersonic velocity combustion performance installs in aircraft main part lower part, its characterized in that: including engine body and gas generator, the inside loading space that has of aircraft body, gas generator arranges the loading space in, engine body includes air inlet, isolation section, supersonic combustion chamber, the tail spray tube that communicate in proper order after going to, gas generator includes mutually independent inflammable propellant gas generator and rich burning solid propellant gas generator, and is equipped with inflammable propellant and rich burning solid propellant in the two respectively, inflammable propellant gas generator and rich burning solid propellant gas generator afterbody all connect the spray tube, and the honeycomb duct is all even connected to the spray tube rear portion, and it has the orifice to open on the engine body wall at supersonic combustion chamber top, the exit end of honeycomb duct passes the diapire of the loading space in the aircraft body and communicates with the orifice on the engine body wall at supersonic combustion chamber top, the exit end of the honeycomb duct of inflammable propellant gas generator afterbody is located rich burning solid propellant gas generator gas outlet end on the engine body wall at supersonic combustion chamber top The front side of the outlet end of the draft tube at the tail of the generator.
2. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 1, wherein: and the jet direction of the air flow at the outlet end of the flow guide pipe and the flowing direction of the main air flow in the supersonic combustion chamber form an included angle.
3. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 2, wherein: the setting criterion of the angle between the air flow jet direction of the outlet end of the flow guide pipe and the main air flow flowing direction in the supersonic combustion chamber is that under the given supersonic incoming flow condition, the air flow plume sprayed from the outlet of the tail flow guide pipe of the inflammable propellant gas generator basically covers the air flow plume sprayed from the outlet of the tail flow guide pipe of the inflammable solid propellant gas generator.
4. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 2, wherein: the included angle is larger than 0 degree and smaller than or equal to 90 degrees.
5. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 1, wherein: the propellant-rich gas generator is located at a forward end of the propellant-rich gas generator within the stowage space.
6. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 1, wherein: the fuel-rich solid propellant maintains a single sided end face combustion within the gas generator.
7. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 1, wherein: the flammable propellant is jetted into the supersonic combustion chamber through the jet pipe and the guide pipe at subsonic speed or supersonic speed after being combusted in the flammable propellant gas generator.
8. The scramjet engine for improving the supersonic combustion performance of the boron-containing rich-combustion solid propellant according to claim 1, wherein: the flammable propellant is a solid or liquid fuel.
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| CN201910211715.4A CN109899179B (en) | 2019-03-20 | 2019-03-20 | Scramjet engine capable of improving supersonic combustion performance of boron-containing rich-combustion solid propellant |
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| CN201910211715.4A CN109899179B (en) | 2019-03-20 | 2019-03-20 | Scramjet engine capable of improving supersonic combustion performance of boron-containing rich-combustion solid propellant |
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| CN109899179A CN109899179A (en) | 2019-06-18 |
| CN109899179B true CN109899179B (en) | 2020-01-10 |
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| CN110700963B (en) * | 2019-08-15 | 2021-03-02 | 西北工业大学 | Compact layout type solid rocket gas scramjet engine based on axial symmetry |
| CN113190932B (en) * | 2021-05-31 | 2022-04-19 | 中国人民解放军国防科技大学 | Method for improving combustion efficiency of scramjet engine based on pneumatic virtual concave cavity |
| CN113653571B (en) * | 2021-08-16 | 2022-11-08 | 北京机械设备研究所 | Solid propellant combustion flow stabilizer and solid engine combustion generator |
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| GB832339A (en) * | 1945-04-28 | 1960-04-06 | Aerojet General Co | Jet propulsion |
| US3811280A (en) * | 1967-10-06 | 1974-05-21 | Us Army | Process of using storable propellant fuels in supersonic combustion ramjets |
| US5224344A (en) * | 1992-09-04 | 1993-07-06 | The United States Of America As Represented By The Secretary Of The Navy | Variable-cycle storable reactants engine |
| JPH0893556A (en) * | 1994-09-29 | 1996-04-09 | Ishikawajima Harima Heavy Ind Co Ltd | Gas generator for air turbo ram jet engine |
| CN202900445U (en) * | 2012-09-17 | 2013-04-24 | 浙江大学 | Boryl solid fuel propulsion device using plasma generator to ignite |
| CN108798934A (en) * | 2018-04-28 | 2018-11-13 | 西北工业大学 | Become mode fractional combustion solid-rocket punching press combined engine |
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2019
- 2019-03-20 CN CN201910211715.4A patent/CN109899179B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB832339A (en) * | 1945-04-28 | 1960-04-06 | Aerojet General Co | Jet propulsion |
| US3811280A (en) * | 1967-10-06 | 1974-05-21 | Us Army | Process of using storable propellant fuels in supersonic combustion ramjets |
| US5224344A (en) * | 1992-09-04 | 1993-07-06 | The United States Of America As Represented By The Secretary Of The Navy | Variable-cycle storable reactants engine |
| JPH0893556A (en) * | 1994-09-29 | 1996-04-09 | Ishikawajima Harima Heavy Ind Co Ltd | Gas generator for air turbo ram jet engine |
| CN202900445U (en) * | 2012-09-17 | 2013-04-24 | 浙江大学 | Boryl solid fuel propulsion device using plasma generator to ignite |
| CN108798934A (en) * | 2018-04-28 | 2018-11-13 | 西北工业大学 | Become mode fractional combustion solid-rocket punching press combined engine |
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