CN109899179A - 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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- CN109899179A CN109899179A CN201910211715.4A CN201910211715A CN109899179A CN 109899179 A CN109899179 A CN 109899179A CN 201910211715 A CN201910211715 A CN 201910211715A CN 109899179 A CN109899179 A CN 109899179A
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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 present invention relates to scramjet engine application field more particularly to a kind of fuel-rich solid propellant of promotion boracic are super
The scramjet engine of velocity of sound combustibility.
Background technique
Solid-rocket scramjet engine is a kind of new concept scramjet engine using solid propellant.And surpass
The residence time of air-flow is millisecond magnitude in velocity of sound combustion chamber, and fuel was difficult within the so short time and air is completed adequately
Blending and burning.Particularly with the fuel-rich solid propellant of boracic, due to the oxide layer (B on boron powder surface2O3) boiling point is high
(2130K), this seriously inhibits the burnings of boron in propellant, to seriously affect the performance boost of engine.Promote boracic
Combustibility of the fuel-rich solid propellant in supersonic speed combustion chamber is always the crucial skill of solid-rocket scramjet engine
One of art, solid-rocket scramjet engine is at home and abroad studied less at present, is accumulated experience few.It is fuel-rich with regard to promoting boracic
Solid propellant is in the research of solid-rocket scramjet engine combustibility, and domestic and international constituent parts are mainly from propellant
Formula and propellant manufacturing process, etc. start with and carry out correlative study.And the triturating machine of propellant formulation and manufacture craft
Reason is complicated, longer so as to cause the lead time, increases cost.
Summary of the invention
The technical problems to be solved by the present invention are: provide one kind promotes the fuel-rich solid propellant propulsion of boracic in terms of burning tissues
The scramjet engine of combustibility of agent under the conditions of Supersonic Stream.
In order to solve the above-mentioned technical problem, the present invention is achieved by the following technical solutions:
A kind of scramjet engine promoting the fuel-rich solid propellant supersonic combustion performance of boracic, is installed on aircraft
Lower body part, including engine main body and gas generator, aircraft body inside have loading space, the gas generator
It is placed in loading space, the engine main body includes air intake duct, distance piece, the supersonic combustion being sequentially communicated from after going to
Room, jet pipe, the gas generator include mutually independent combustible propellant gas generator and fuel-rich solid propellant
Gas generator, and combustible propellant and fuel-rich solid propellant are respectively equipped in the two, the combustible propellant combustion gas hair
Raw device and fuel-rich solid propellant gas generator tail portion are all connected with jet pipe, and jet pipe rear portion connects diversion pipe, supersonic combustion
Spray orifice is provided on the engine main body wall in ceiling portion, the outlet end of the diversion pipe passes through the loading space in aircraft body
Bottom wall is simultaneously connected to, the combustible propellant gas generator tail with the spray orifice on the engine main body wall at the top of supersonic speed combustion chamber
The outlet end of the diversion pipe in portion is located at the front side of the outlet end of the diversion pipe of fuel-rich solid propellant gas generator tail portion.
Preferably, what the jet-impingement direction at the draft tube outlets end and primary air flowed in supersonic combustion room
Direction is arranged in angle.
Preferably, the jet-impingement direction of the outlet end of the diversion pipe and primary air flow in supersonic combustion room
Direction between included angle design standard be that under the conditions of given Supersonic Stream, the combustible propellant combustion gas occurs
The air-flow plume that the outlet of device tail portion diversion pipe sprays covers fuel-rich solid propellant gas generator tail portion diversion pipe substantially
Export the air-flow plume sprayed.
Preferably, the angle of the angle is greater than 0 degree and is less than or equal to 90 degree.
Preferably, the combustible propellant gas generator be located at before fuel-rich solid propellant gas generator
End.
Preferably, the fuel-rich solid propellant keeps unilateral cigarette burning in gas generator.
The combustible propellant burn in combustible propellant gas generator after by jet pipe and diversion pipe with subsonic speed
Or supersonic speed is injected into supersonic speed afterburning chamber.
Preferably, the inflammable compound propellant is solid or liquid fuel.
Compared with prior art, usefulness of the present invention is: the fuel-rich solid propellant ultrasound quick burning of promotion boracic
The scramjet engine for burning performance can be significantly improved fuel-rich solid within a short period of time by multi fuel combined jet structure
Combustibility of body propellant under the conditions of Supersonic Stream temporarily avoids the research of propellant formulation development and technique preparation
Difficulty is big, the problem that research cycle is grown, thus practicability is high.
Detailed description of the invention
The following further describes the present invention with reference to the drawings:
Fig. 1 is the side partial cutaway structural schematic diagram when present invention is mounted on aircraft body lower part.
Specific embodiment
The technical scheme in the embodiments of the invention will be clearly and completely described below, it is clear that described implementation
Example is only a part of the embodiments of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, this field is common
Technical staff's all other embodiment obtained without making creative work belongs to the model that the present invention protects
It encloses:
A kind of scramjet engine of the fuel-rich solid propellant supersonic combustion performance of promotion boracic as shown in Figure 1,
It is installed on 1 lower part of aircraft body, including engine main body and gas generator, there is loading space inside aircraft body
12, the gas generator is placed in loading space 12, and the engine main body includes the air intake duct being sequentially communicated from after going to
2, distance piece 3, supersonic speed combustion chamber 4, jet pipe 5, the dotted line in figure are the segmentation index line of various pieces, and primary air is from air inlet
Road 2 enters, and enters burning in supersonic speed combustion chamber 4 by distance piece 3, finally passes through 5 Accelerating Removal of jet pipe.
The gas generator includes mutually independent combustible propellant gas generator 6 and the combustion of fuel-rich solid propellant
Gas generator 7, in the present embodiment, if air intake duct position is the front of aloof punching engine, jet pipe position
For the rear of aloof punching engine, in loading space, the combustible propellant gas generator 6 is placed in fuel-rich solid propellant propulsion
Loading space is saved in the front end of agent gas generator 7.
It is respectively equipped in the combustible propellant gas generator 6 and fuel-rich solid propellant gas generator 7 easily
Propellant and fuel-rich solid propellant are fired, in the present embodiment, the combustible propellant is solid or liquid fuel, described
Combustible propellant gas generator 6 and fuel-rich 7 tail portion of solid propellant gas generator connect jet pipe (8,10), jet pipe tail portion
It connects diversion pipe (9,11), spray orifice 13 is provided on supersonic speed combustion chamber roof, the outlet end of diversion pipe passes through aircraft body
The bottom wall of interior loading space is simultaneously connected to the spray orifice on the engine main body wall at the top of supersonic speed combustion chamber, combustible propellant and
Fuel-rich solid propellant is lighted a fire in combustible propellant gas generator and fuel-rich solid propellant gas generator respectively, is produced
Raw high temperature and high pressure gas is injected via the outlet of jet pipe and diversion pipe and the outlet of supersonic speed combustion chamber, and at a certain angle
Supersonic speed combustion chamber and mainstream carry out blending burning.
The outlet of the 6 tail portion diversion pipe of combustible propellant gas generator is located at fuel-rich solid propellant gas generator
The front side of the outlet of 7 tail portion diversion pipes, thus, the high temperature and high pressure gas generated after the burning of the combustible propellant of front first with come
Stream carries out blending burning, to improve the temperature of incoming flow, after promoting temperature of incoming flow, on the one hand can make fuel-rich solid propellant
Inflammable gas phase and carbon particle conflagration in gas generator jet exit combustion gas, the burning for subsequent other particles provide more
Add sufficient residence time, on the other hand, after mainstream temperature is promoted, is further mentioned using combustible material burning in fuel-rich combustion gas
Mainstream temperature is risen, thus helps to improve the integral combustion efficiency of fuel-rich solid propellant.
It carries out blending uniformity when burning to improve high temperature and high pressure gas and incoming flow, efficiency of combustion is improved, as preferred
The direction that scheme, the jet-impingement direction of diversion pipe (9, the 11) outlet end and primary air flow in supersonic speed combustion chamber 4
Be arranged in angle, preferably, to promote air-flow mixed effect, the angle of the angle be greater than 0 degree and be less than or
Equal to 90 degree, and in practical applications, the exit flow injection direction and primary air of the diversion pipe (9,11) are in ultrasonic quick burning
The included angle design standard burnt between the direction flowed in room 4 is combustible propellant gas generator tail portion diversion pipe
Outlet spray air-flow plume cover substantially fuel-rich solid propellant gas generator tail portion diversion pipe outlet spray gas
Flow plume.
In the present embodiment, the fuel-rich solid propellant keeps unilateral in fuel-rich solid propellant gas generator 7
Cigarette burning further increases the efficiency of combustion of fuel-rich solid propellant.
In addition, occurring to further increase efficiency of combustion, the combustible propellant or fuel-rich solid propellant in combustion gas
Supersonic speed afterburning chamber is injected into subsonic speed or supersonic speed by jet pipe and diversion pipe after burning in device.
In the present embodiment, preferably the fuel-rich solid propellant of boracic is fuel-rich solid propellant, in practical applications, air inlet
Road compresses hypersonic incoming flow, and compressed mainstream passes through distance piece, and the effect of the distance piece is super in order to be isolated
Influence of the velocity of sound combustion chambers burn to air intake duct, to prevent air intake duct from not starting, mainstream is exported by distance piece, static pressure, static temperature
It being increased, speed reduces, but still keeps supersonic flows, at this point, combustible propellant agent is lighted a fire in gas generator, institute
The high temperature and high pressure gas for stating the generation of combustible propellant gas generator is penetrated at a certain angle via the jet pipe and diversion pipe of the rear part
Enter and blended in supersonic speed combustion chamber with and with mainstream, and promote mainstream certain temperature, almost at the same time, boracic is fuel-rich solid
Body propellant is lighted a fire in fuel-rich solid propellant gas generator, and the fuel-rich combustion gas of boracic that the gas generator generates passes through
The jet pipe and diversion pipe of the rear part inject supersonic speed combustion chamber and at a certain angle by combustion-supporting and promotion temperature high temperature mainstreams
It is blended and is burnt, the high temperature and high pressure gas for formation of burning passes through jet pipe expansion work, generates thrust, then realizes and starts
The operation of machine.
It is emphasized that: the above is only presently preferred embodiments of the present invention, not make in any form to the present invention
Limitation, any simple modification, equivalent change and modification to the above embodiments according to the technical essence of the invention,
All of which are still within the scope of the technical scheme of the invention.
Claims (8)
1. a kind of scramjet engine for promoting the fuel-rich solid propellant supersonic combustion performance of boracic, is installed on aircraft master
Body lower part, it is characterised in that: including engine main body and gas generator, there is loading space inside aircraft body, it is described
Gas generator is placed in loading space, and the engine main body includes the air intake duct being sequentially communicated from after going to, distance piece, surpasses
Velocity of sound combustion chamber, jet pipe, the gas generator include mutually independent combustible propellant gas generator and fuel-rich solid
Body propellant gas generator, and combustible propellant and fuel-rich solid propellant are respectively equipped in the two, the inflammable propulsion
Agent gas generator and fuel-rich solid propellant gas generator tail portion are all connected with jet pipe, and jet pipe rear portion connects diversion pipe, surpass
Spray orifice is provided on the engine main body wall of velocity of sound top of combustion chamber, the outlet end of the diversion pipe passes through the dress in aircraft body
It carries the bottom wall in space and is connected to the spray orifice on the engine main body wall at the top of supersonic speed combustion chamber, the combustible propellant combustion gas
The outlet end of the diversion pipe of generator tail portion is located at the outlet end of the diversion pipe of fuel-rich solid propellant gas generator tail portion
Front side.
2. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 1
Motivation, it is characterised in that: what the jet-impingement direction at the draft tube outlets end and primary air flowed in supersonic combustion room
Direction is arranged in angle.
3. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 2
Motivation, it is characterised in that: the jet-impingement direction of the outlet end of the diversion pipe and primary air flow in supersonic combustion room
Direction between included angle design standard be that under the conditions of given Supersonic Stream, the combustible propellant combustion gas occurs
The air-flow plume that the outlet of device tail portion diversion pipe sprays covers fuel-rich solid propellant gas generator tail portion diversion pipe substantially
Export the air-flow plume sprayed.
4. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 2
Motivation, it is characterised in that: the angle of the angle is greater than 0 degree and is less than or equal to 90 degree.
5. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 1
Motivation, it is characterised in that: in loading space, the combustible propellant gas generator is located at fuel-rich solid propellant gas hair
The front end of raw device.
6. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 1
Motivation, it is characterised in that: the fuel-rich solid propellant keeps unilateral cigarette burning in gas generator.
7. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 1
Motivation, it is characterised in that: the combustible propellant burn in combustible propellant gas generator after by jet pipe and diversion pipe
Supersonic speed afterburning chamber is injected into subsonic speed or supersonic speed.
8. a kind of ultra-combustion ramjet hair for promoting the fuel-rich solid propellant supersonic combustion performance of boracic according to claim 1
Motivation, it is characterised in that: the inflammable compound propellant is solid or liquid fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 true CN109899179A (en) | 2019-06-18 |
| CN109899179B CN109899179B (en) | 2020-01-10 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110700963A (en) * | 2019-08-15 | 2020-01-17 | 西北工业大学 | Compact layout type solid rocket gas scramjet engine based on axial symmetry |
| CN113190932A (en) * | 2021-05-31 | 2021-07-30 | 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 |
| CN113653571A (en) * | 2021-08-16 | 2021-11-16 | 北京机械设备研究所 | Solid propellant combustion flow stabilizing device and solid engine combustion generator |
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| 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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| 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 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110700963A (en) * | 2019-08-15 | 2020-01-17 | 西北工业大学 | Compact layout type solid rocket gas scramjet engine based on axial symmetry |
| CN113190932A (en) * | 2021-05-31 | 2021-07-30 | 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 |
| 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 |
| CN113653571A (en) * | 2021-08-16 | 2021-11-16 | 北京机械设备研究所 | Solid propellant combustion flow stabilizing device and solid engine combustion generator |
| 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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