CN107327356A - A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner - Google Patents
A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner Download PDFInfo
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- CN107327356A CN107327356A CN201710687101.4A CN201710687101A CN107327356A CN 107327356 A CN107327356 A CN 107327356A CN 201710687101 A CN201710687101 A CN 201710687101A CN 107327356 A CN107327356 A CN 107327356A
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- Prior art keywords
- afterburner
- combustion
- secondary injection
- liquid rocket
- efficiency
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Classifications
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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
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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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 present invention discloses a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner, circumferentially opens up secondary injection passage in after-burning room housing, and be provided with the secondary spray plumb joint connected with secondary injection passage.And design secondary injection passage axis is perpendicular to afterburner axial direction, while the ejection end aperture design of secondary injection passage is 7mm, secondary injection flow ratio is 0.75.The present invention can be effectively increased the disturbance of afterburner, be sufficiently mixed oxidant and fuel and be maintained at best oxygen combustion than nearby carrying out combustion reaction, solid-liquid rocket is reached highest efficiency of combustion.
Description
Technical field
The invention belongs to improve efficiency of combustion technical field, it is related to a kind of in afterburner raising solid-liquid rocket burning
The method of efficiency.
Background technology
Domestic and foreign scholars increasingly deploy the research of a new round to hybrid rocket engine again in recent years.With
Traditional solid or liquid-propellant rocket engine is compared, and it has simple in construction, and operation is flexible, repeatedly starts and with low cost
The advantages of.However, solid-liquid rocket combustion mode belongs to typical non-premix diffusion combustion, so also just determining that it has
There is also the deficiency of itself while standby above-mentioned advantage, such as fuel regression rate is small, and oxygen combustion is than (oxidant stream in the course of work
Amount and the ratio of fuel flow rate) change and efficiency of combustion is low.
By testing and simulation result understands that the design for changing front end ejector filler can improve the combustion stability of engine, but compared with
Hardly possible improves fuel availability and realizes efficient burning.Therefore, to realize the efficient burning of solid-liquid rocket, it is necessary in after-burning
Room strengthens the blending of propellant, improves the utilization rate of propellant, and the method generally used is increase disturbing flow device, secondary spray etc.
Mode and give solid fuel increase metallic etc..At present, many scholars are studied efficient burning technology, are mainly adopted
Measure is to increase the mode of disturbing flow device in afterburner or powder column stage casing.But the high temperature, high pressure due to engine interior
Adverse circumstances, disturbing flow device faces the ablation problem of sternness, can't work long hours.Meanwhile, disturbing flow device starts increase
The architecture quality of machine, increases volume fraction.
With continuing to develop for solid-liquid rocket, to its efficiency of combustion requirement also more and more higher in engineering, therefore compel
It is essential and wants a kind of simpler effective method to improve solid-liquid rocket operating efficiency.
The content of the invention
In order to solve the above problems, based on improve afterburner fuel steam utilization, increase propellant contact area this
Individual starting point, the present invention proposes a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner.
The method that the present invention improves solid-liquid rocket efficiency of combustion in afterburner, be specially：In after-burning room housing week
To the afterburner secondary injection passage for uniformly opening up insertion afterburner housing sidewall and afterburner heat insulation layer；.Simultaneously in afterburner
Housing circumferentially uniformly installs secondary spray plumb joint；Make secondary spray plumb joint respectively by secondary injection passage and afterburner shell
Internal portion's connection.
Above-mentioned secondary injection plumb joint uses DN4, and 60 degree of tips, material is made of high temperature-resistantungsten tungsten copper alloy.Secondary spray
Passage secondary injection passage is penetrated for 8, position is opened up in the circumference of afterburner middle section, secondary injection passage axis perpendicular to
Afterburner axial direction；Secondary injection channel injection one end internal diameter is 7mm simultaneously, and secondary injection flow ratio is 0.75.
The advantage of the invention is that：
1st, the method that the present invention improves solid-liquid rocket efficiency of combustion in afterburner, enhancing oxidant and fuel gas
Blending, and keep fixed oxygen to fire ratio, easily realize accurate control.
2nd, the method that the present invention improves solid-liquid rocket efficiency of combustion in afterburner, from gas injection, easily enters
Row heat protection design；
3rd, the method that the present invention improves solid-liquid rocket efficiency of combustion in afterburner, is particularly suitable for answering for thrust regulation
With while adding the advantage using inertia powder column.
4th, the method that the present invention improves solid-liquid rocket efficiency of combustion in afterburner, it is simple easily to realize, hair can be extended
The motivation life-span, it is adaptable to the engine worked long hours.
Brief description of the drawings
Fig. 1 sets for a kind of after-burning cell structure for the method that solid-liquid rocket efficiency of combustion is improved in afterburner of the present invention
Meter figure.
In figure：
1- combustion chambers rear flange 2- after-burner housing 3- afterburner heat insulation layers
4- rear head housing 5- rear head heat insulation layer 6- secondary injection passages
Bis- spray plumb joints of 7-
Specific embodiment
Patent of the present invention is described further below in conjunction with the accompanying drawings.
The method that the present invention improves solid-liquid rocket efficiency of combustion in afterburner, as shown in figure 1, being specially：
1st, afterburner material is selected；
In afterburner, the combustion chamber rear flange 1 positioned at front end uses 1Cr8Ni9Ti stainless steels, the after-burning positioned at middle part
Room housing 2 uses stainless steel；The afterburner heat insulation layer 3 of inner walls laying simultaneously, and rear head housing 4 and after-burning room housing
The rear head heat insulation layer 5 inlayed between 2 uses high silica；Rear head housing 4 uses ASTM A572 model steel.
2nd, design secondary injection passage 6；
In the circumferential afterburner two for uniformly opening up the side wall of insertion after-burning room housing 2 and afterburner heat insulation layer 3 of after-burning room housing 2
Secondary injection channel 6；
3rd, increase secondary injection plumb joint 7；
Secondary injection plumb joint 7 uses DN4, and 60 degree of tips, material is made of high temperature-resistantungsten tungsten copper alloy；In afterburner shell
Body 2 is circumferential uniformly to install secondary spray plumb joint 7；Make secondary spray plumb joint 7 respectively by secondary injection passage 6 and afterburner
The inside of housing 2 is connected；Realize fixed using welding manner between secondary spray plumb joint 7 and after-burning room housing 2 and seal.Thus two
Secondary injection liquid is sprayed into after-burning room housing 2 after being compressed by secondary injection passage 6, realizes secondary spray.
For solid-liquid rocket, the burning before afterburner is to be in fuel-rich state, the more combustion for not participating in reaction
Material is entered in afterburner by fuel gas inlet, and is flowed through jet pipe by afterburner outlet and finally sprayed, cause fuel waste and
The reduction of nozzle efficiency.But by increasing secondary injected liquid oxidant in after-burner, enhance the disturbance of afterburner, enter
And the blending of fuel and oxygen is enhanced, while maintaining oxidant and fuel by controlling the oxidizer flow rate of secondary spray
Than near burnt in best oxygen combustion, fuel is so not only saved, while also improving the efficiency of combustion of engine.
Pass through experiment and simulation calculation in the present invention, it is determined that the position of optimal secondary spray, spray angle, spray orifice
Footpath, spray hole count and secondary injection flow ratio, it is specific as follows：
A, ensureing that rocket engine front end oxidizer flow rate is 0.4kg/s, the secondary spray total flow of oxidant is
Under the premise of 0.15kg/s, by contrasting the different eject positions of afterburner three (along afterburner axial line distance afterburner front end point
Wei 15mm, 25mm and 35mm) secondary injection result, determine the change of eject position influences very little to efficiency of combustion, but examines
Consider the centre position for determining that eject position is after-burning chamber axis in afterburner structural strength, the present invention, i.e., apart from afterburner
It is circumferential at the 25mm of front end to open up secondary injection passage.
Under B, precondition same in A, and at the secondary injection angle (angle of injection axially bored line and engine axis
Degree) in the range of 30 °~150 °, when secondary injection passage 6 perpendicular to after-burning chamber axial direction spray, energy is obvious (90 ° near)
Efficiency of combustion is improved, efficiency of combustion increases to 94.92% from 90.92%, and final design is with perpendicular to after-burning chamber axial direction
Spray angle carries out secondary spray, i.e. secondary injection passage axis perpendicular to afterburner axial direction.
C, the aperture of different secondary injection passages 6 can influence function of the engine, in the hole of secondary injection passage 6
Footpath is from the 6 of 4mm~9mm under operating mode, and efficiency of combustion first increases to be reduced afterwards, is that efficiency of combustion reaches highest at 7mm in aperture, most
A height of 94.6868%.So there is optimal injection aperture for 7mm；Therefore design secondary injection passage 6 has 9mm in the present invention
Large diameter section, with 7mm small internal diameters section；Wherein large diameter section open up with the wall of after-burning room housing 2；Small internal diameter section is opened in after-burning
On room heat insulation layer 3, and outer end is opened on the wall of after-burning room housing 2.
D, the different quantity of secondary injection passage 6 can influence engine oxygen combustion ratio, can improve solid to a certain extent
Fluid fuel burn rate, improves engine/motor specific impulse and characteristic velocity, but cause engine/motor specific impulse efficiency and combustion to a certain extent
Burn efficiency and slightly have reduction, in the 4 of research, 6,8,10 secondary injection passages 6, in summary factor consideration finally determines secondary
The quantity of injection channel 6 is 8.
E, guarantee engine head oxidizer flow rate are that 0.4kg/s is constant, and (secondary injection is total for design secondary injection flow ratio
The ratio between flow and primary oxidant flow) it is 0.25~1, when secondary spray flow-rate ratio is 0.75 or so, propellant fully reacts,
Efficiency of combustion reaches highest 97.66%.Therefore to this specific engine structure, optimal secondary injection flow ratio is 0.75.
Claims (8)
1. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner, it is characterised in that：
The afterburner secondary injection of insertion afterburner housing sidewall and afterburner heat insulation layer is circumferentially uniformly opened up in after-burning room housing
Passage；Secondary spray plumb joint is uniformly circumferentially installed in after-burning room housing；Make secondary spray plumb joint respectively by secondary injection
Passage is connected with afterburner enclosure interior.
2. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Secondary injection plumb joint uses DN4, and 60 degree of tips, material is made of high temperature-resistantungsten tungsten copper alloy.
3. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Secondary injection passage opens up position in the circumference of afterburner middle section.
4. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Secondary injection passage axis is perpendicular to afterburner axial direction.
5. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Secondary injection channel injection one end internal diameter is 7mm.
6. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Secondary injection passage is 8.
7. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Secondary injection flow ratio is 0.75.
8. a kind of method for improving solid-liquid rocket efficiency of combustion in afterburner as claimed in claim 1, it is characterised in that：
Combustion chamber rear flange uses 1Cr8Ni9Ti stainless steels, and after-burning room housing uses stainless steel；Afterburner heat insulation layer and rear head are exhausted
Thermosphere uses high silica；Rear head housing uses ASTM A572 model steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710687101.4A CN107327356A (en) | 2017-08-11 | 2017-08-11 | A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710687101.4A CN107327356A (en) | 2017-08-11 | 2017-08-11 | A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner |
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| CN107327356A true CN107327356A (en) | 2017-11-07 |
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| CN201710687101.4A Pending CN107327356A (en) | 2017-08-11 | 2017-08-11 | A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109441666A (en) * | 2018-10-30 | 2019-03-08 | 北京航空航天大学 | Tail portion vortex centrifugal jetting type hybrid rocket engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6178739B1 (en) * | 1997-07-31 | 2001-01-30 | Iowa State University Research Foundation, Inc. | Monopropellant assisted solid rocket engine |
| CN102400814A (en) * | 2011-10-27 | 2012-04-04 | 北京航空航天大学 | Solid-liquid hybrid rocket ramjet for test |
| CN102943719A (en) * | 2012-11-06 | 2013-02-27 | 北京航空航天大学 | Turbulence device for postcombustion chamber of hybrid rocket engine |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN106968837A (en) * | 2017-04-01 | 2017-07-21 | 北京航空航天大学 | A kind of secondary spray structure of hydrogen peroxide hybrid rocket engine afterburner |
-
2017
- 2017-08-11 CN CN201710687101.4A patent/CN107327356A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6178739B1 (en) * | 1997-07-31 | 2001-01-30 | Iowa State University Research Foundation, Inc. | Monopropellant assisted solid rocket engine |
| CN102400814A (en) * | 2011-10-27 | 2012-04-04 | 北京航空航天大学 | Solid-liquid hybrid rocket ramjet for test |
| CN102943719A (en) * | 2012-11-06 | 2013-02-27 | 北京航空航天大学 | Turbulence device for postcombustion chamber of hybrid rocket engine |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN106968837A (en) * | 2017-04-01 | 2017-07-21 | 北京航空航天大学 | A kind of secondary spray structure of hydrogen peroxide hybrid rocket engine afterburner |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109441666A (en) * | 2018-10-30 | 2019-03-08 | 北京航空航天大学 | Tail portion vortex centrifugal jetting type hybrid rocket engine |
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Application publication date: 20171107 |