CN107044361A - A kind of pulse detonation rocket engines and control method with combustion-compensating device - Google Patents
A kind of pulse detonation rocket engines and control method with combustion-compensating device Download PDFInfo
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- CN107044361A CN107044361A CN201710346783.2A CN201710346783A CN107044361A CN 107044361 A CN107044361 A CN 107044361A CN 201710346783 A CN201710346783 A CN 201710346783A CN 107044361 A CN107044361 A CN 107044361A
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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
- F02K9/44—Feeding propellants
- F02K9/56—Control
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention proposes a kind of pulse detonation rocket engines and control method with combustion-compensating device.Pulse detonation rocket engines proposed by the invention include oxidant feed system, fuel oil supply system, isolation gas feed system, jet feed system, whistle control system and detonation tube.Detonation tube is the circle straight tube that one end is closed, there are propellant spray hole and oxidant spray circumferential weld on its head, having close to head in spark plug, detonation tube has screw type pinking intensifier, there is jet spray section close to detonation tube afterbody, jet pipe is installed in detonation tube afterbody.The pulse detonation rocket engines are operated using liquid fuel and oxygen, and afterbody jet uses gaseous oxidant.The present invention can alleviate simultaneously pulse detonation rocket engines liquid fuel at this stage can not fully burn with the problem of working medium crosses expansion in the time segment of unsteady drying bottom, with higher application value.
Description
Technical field
The present invention relates to detonation engine technical field, be a kind of pulse detonation rocket engines with combustion-compensating device and
Control method.
Background technology
Detonation wave is that a kind of have the rate of heat release being exceedingly fast, the spread speed being exceedingly fast and the high burning from boosting capability
Ripple, due to these obvious advantages, the dynamical system designed based on detonating combustion has very high cycle efficieny, also therefore exists
Today that aeronautical and space technology is developed rapidly more and more is paid attention to.The form that detonating combustion is applied into propulsion plant has
Many kinds, wherein it is pulse detonation rocket engines (pulse that simple in construction, working stability and technology are more ripe
Detonation rocket engine, abbreviation PDRE).
PDRE possesses huge theory advantage and with good application prospect, but is also deposited when being applied to engineering practice
The problem that its performance is played completely is restricted at some, such as：The Nozzle Design problem as caused by the unstable state course of work and use
Fuel-rich combustion problem during liquid fuel.
The content of the invention
For PDRE liquid fuels fuel-rich combustion and unstable state Nozzle Design problem, the present invention proposes a kind of with afterburning dress
The pulse detonation rocket engines and control method put.According to control method proposed by the invention, the present invention design it is quick-fried
Pipe afterbody injection jet is shaken, remaining fuel after detonating combustion can be promoted to burn away and release energy, fuel availability is improved
While, reduce in the unstable state exhaust process of engine and cross expansion-loss.These new engine structures and control method
The working condition of liquid fuel pulse detonation rocket engine can be effectively improved, and promotes its practical implementation.
The technical scheme is that：
A kind of pulse detonation rocket engines with combustion-compensating device, are specifically included：Oxidant feed system, fuel supply
System, isolation gas feed system, jet feed system, six parts of whistle control system and detonation tube.As shown in figure 1, oxygen
Agent feed system includes the first oxidant air accumulator 1-1, the first pressure-reducing valve 1-2, the first electrically-controlled valve 1-3 and first check-valve 1-
4；Fuel feed system includes extruding gas air accumulator 2-1, the second pressure-reducing valve 2-2, fuel oil storage tank 2-3 and the second electrically-controlled valve 2-4；Every
Include isolation gas air accumulator 3-1, the 3rd pressure-reducing valve 3-2 and the 3rd electrically-controlled valve 3-3 from gas feed system；Jet feed system includes
Second oxidant air accumulator 4-1, the 4th pressure-reducing valve 4-2, the 4th electrically-controlled valve 4-3 and second check-valve 4-4；In addition with main
Equipment detonation tube 6, is provided with spark plug 5 thereon.The concrete structure of detonation tube 6 is as shown in Fig. 2 detonation tube main cavity 6-1
It is smooth straight and one end closing that draw ratio is 24~26；Fuel injection is machined with detonation tube main cavity 6-1 blind end
Hole 6-2 and oxidant injection circumferential weld 6-3；Position peace on detonation tube main cavity 6-1 tube wall at about 2 times away from blind end calibers
Equipped with spark plug 5；Pinking intensifier 6-4, pinking intensifier are being installed at about 4 times away from blind end calibers inside detonation tube
6-4 length is about 10 times of calibers；Export to be machined with about 3 times of calibers away from straight length on detonation tube main cavity 6-1 tube walls and penetrate
Flow section 6-6；Jet supply hole 6-7 is machined with jet segment 6-6；In jet segment 6-6, it is machined with and penetrates on main cavity 6-1 walls
Flow circumferential weld 6-13, its direction and detonation tube main cavity 6-1 axial angle is 30~50 ° and towards Way out；In detonation tube
On main cavity 6-1, the first load cell 6-5, the second load cell 6-8 and the 3rd is also equipped near jet segment 6-6 and is surveyed
Pressure sensor 6-9；Jet pipe 6-10 is installed in detonation tube main cavity 6-1 afterbodys, jet pipe 6-10 is shrinkage expansion type jet pipe, spray
Length of tube is about 3 times of calibers, and contraction section is about 1 times of caliber, and expansion segment is about 2 times of calibers, shrinkage ratio and divergence ratio scope difference
For 2.0-3.0 and 5.0-10.0；Jet pipe 6-10 passes through first flange 6-12 and second flange 6-13 and detonation tube main cavity 6-1
Connection；Whistle control system mainly includes control unit 7.
A kind of control method of the pulse detonation rocket engines with combustion-compensating device, can be specifically described as：Fuel is used
Liquid fuel；Oxidant uses oxygen；Detonation tube afterbody injects gaseous oxidant, and oxygen purity is 30%~70%；Adjust
The equivalent proportion of the supply pressure of whole fuel and oxidant, flow and explosive mixture；Injection hole 6-2, oxidant injection ring
Stitch 6-3 and jet spray orifice 6-7 to open by control sequential, fuel, oxidant and afterburning jet fill rapidly full detonation tube main chamber
Body 6-1；The spark rate of spark plug 5 is set as needed, starts igniting, now will produce stable high frequency in detonation tube 6
Detonation wave；In PDRE runnings, adjust jet spray orifice 6-7 supply flow rate and feed fluid oxygen content to improve pinking
Combustion case in pipe 6, the working condition for making it preferably match jet pipe.
Using pulse detonation rocket engines and its control method proposed by the present invention with combustion-compensating device, in detonation tube
Near exit introduces afterburning jet, and the residual fuel after detonating combustion can be promoted fully to burn, and effectively alleviates and uses liquid fuel
PDRE tissue combustion process in the insufficient problem of burning；Full combustion of fuel is promoted to improve PDRE thrust and combustion simultaneously
Expect specific impulse；The introducing of afterburning jet causes the explosive mixture equivalent proportion of detonation tube afterbody to decline to a great extent, and weakens detonation wave quick-fried
The intensity of pipe afterbody is shaken, reflection of the detonation wave in nozzle throat can be so reduced, and then reduce to engine upstream flow field
Interference；Jet pipe entrance can also be adjusted the state that flows, as increased in exhaust process latter end by introducing jet working medium
Working medium flow makes it more adapt to PDRE unstable state worked to reduce influence of the nozzle divergence cone air-negative-pressure to thrust
Journey, and then improve the pushing effect of jet pipe；Further, since the combustion process in engine export section is all under oil-poor operating mode
Carry out, the discharge of PDRE pollutants can also be reduced using the present invention.
Pulse detonation rocket engines proposed by the present invention with combustion-compensating device are simple and practical, and control method is succinct, and
Overall plan plays the role of good to the performance for improving PDRE.
Brief description of the drawings
Accompanying drawing 1：A kind of feed system of the pulse detonation rocket engines with combustion-compensating device
Accompanying drawing 2：A kind of pinking tubular construction of the pulse detonation rocket engines with combustion-compensating device
Accompanying drawing 3：The control sequential of the feed system of embodiment 1
Accompanying drawing 4：The pinking overpressure of embodiment 1 changes over time curve
Accompanying drawing 5：The control sequential of the feed system of embodiment 2
Accompanying drawing 6：The pinking overpressure of embodiment 2 changes over time curve
In figure, 1-1 is the first oxidant air accumulator, and 1-2 is the first pressure-reducing valve, and 1-3 first is electrically-controlled valve, and 1-4 is first
Check-valves, 2-1 is extruding gas air accumulator, and 2-2 is the second pressure-reducing valve, and 2-3 is fuel oil storage tank, and 2-4 is the second electrically-controlled valve, and 3-1 is
Isolate gas air accumulator, 3-2 is the 3rd pressure-reducing valve, and 3-3 is the 3rd electrically-controlled valve, and 4-1 is the second oxidant air accumulator, and 4-2 is the 4th
Pressure-reducing valve, 4-3 is the 4th electrically-controlled valve, and 4-4 is second check-valve, and 5 be spark plug, and 6 be detonation tube, and 6-1 is detonation tube main cavity,
6-2 is propellant spray hole, and 6-3 is oxidant spray circumferential weld, and 5 be spark plug, and 6-4 is pinking intensifier, and 6-5 is the first pressure measurement
Sensor, 6-6 is jet spray section, and 6-7 is jet spray orifice, and 6-8 is the second load cell, and 6-9 senses for the 3rd pressure measurement
Device, 6-10 is jet pipe, and 6-11 is second flange, and 6-12 is first flange, and 6-13 is jet spray circumferential weld.
Embodiment
In conjunction with specific embodiment, accompanying drawing, the present invention will be further described：
Embodiment 1：
A kind of pulse detonation rocket engines with combustion-compensating device, are specifically included：Oxidant feed system, fuel supply
System, isolation gas feed system, jet feed system, whistle control system and the part of detonation tube six.As shown in figure 1, oxidant
Feed system includes the first oxidant air accumulator 1-1, the first pressure-reducing valve 1-2, the first electrically-controlled valve 1-3 and first check-valve 1-4；Combustion
Expect that feed system includes extruding gas air accumulator 2-1, the second pressure-reducing valve 2-2, fuel oil storage tank 2-3 and the second electrically-controlled valve 2-4；Isolate gas
Feed system includes isolation gas air accumulator 3-1, the 3rd pressure-reducing valve 3-2 and the 3rd electrically-controlled valve 3-3；Jet feed system includes second
Oxidant air accumulator 4-1, the 4th pressure-reducing valve 4-2, the 4th electrically-controlled valve 4-3 and second check-valve 4-4；In addition with main work
Device detonation tube 6, is provided with spark plug 5 thereon.The concrete structure of detonation tube 6 is as shown in Fig. 2 detonation tube main cavity 6-1 is straight
Footpath is 24mm, and pipe range is 600mm smooth straight and one end closing；Fuel is machined with detonation tube main cavity 6-1 blind end
Hand-hole 6-2 and oxidant injection circumferential weld 6-3；Spark plug is installed away from blind end 50mm on detonation tube main cavity 6-1 tube wall
5；Pinking intensifier 6-4 is installed away from blind end 100mm inside detonation tube main cavity 6-1, its length is 240mm；Quick-fried
Being machined with shake pipe main cavity 6-1 tube walls away from straight length outlet 24mm on jet segment 6-6, jet segment 6-6 has jet spray orifice 6-
There are jet spray circumferential weld 6-13, jet spray circumferential weld 6-13 direction and detonation tube main cavity 6-1 axial direction in 7, jet segment 6-6
Angle is 45 ° and towards the Way out of detonation tube 6, and circumferential weld width is 2mm；On detonation tube main cavity 6-1, with jet segment 6-
6 apart from 50mm upstream and downstream respectively install the first load cell 6-5 and the second load cell 6-8；In detonation tube main cavity 6-1
On, the 3rd load cell 6-9 is installed apart from 100mm downstream with jet segment 6-6；Jet pipe 6- is installed in the afterbody of detonation tube 6
10, jet pipe 6-10 are shrinkage expansion type jet pipe, and jet pipe length is 70mm, shrinks segment length 24mm, expands segment length 46mm, shrinkage ratio
It is respectively 2.3 and 10.0 with divergence ratio；Whistle control system includes control unit 7.
A kind of control method of the pulse detonation rocket engines with combustion-compensating device, can be specifically described as：Use kerosene
Make fuel, make oxidant using oxygen purity for 40% oxygen-enriched air, isolation gas uses nitrogen, and jet uses carrier of oxygen
Fraction is 50% oxygen-enriched air, using control sequential as shown in Figure 3；After check device is errorless, adjustment fuel and oxidation
The supply pressure of agent is 0.5MPa and 1.0MPa, and explosive mixture equivalent proportion is 1.5；First is set according to Fig. 3 work schedule
Electrically-controlled valve 1-3, the second electrically-controlled valve 2-4, the 3rd electrically-controlled valve 3-3, the specific works parameter of the 4th electrically-controlled valve 4-3 and spark plug 5, and
It is uniformly controlled by control unit 7；The initial pressure of jet is 1.0MPa；Engine is started by control unit 7, starts igniting,
Now stable high frequency detonation wave will be produced in detonation tube 6.By the first load cell 6-5, the second load cell 6-8 and
The pressure in detonation tube main cavity 6-1 that 3rd load cell 6-9 is measured is respectively labeled as p1, p2And p3, measurement result is as schemed
Shown in 4.From fig. 4, it can be seen that 5MPa is above by the first load cell 6-5 pressure peaks measured, and in jet segment 6-6
Afterwards, all there was only 4MPa or so by the second load cell 6-8 and the 3rd load cell the 6-9 pressure peak measured.This
Phenomenon successfully demonstrates beneficial effect of the jet afterburning scheme to alleviation engine export tail gas pressure fluctuation.Meanwhile, with being not added with
The operating mode of jet is compared, and the engine average thrust with combustion-compensating device adds 84.1%.
Embodiment 2：
A kind of pulse detonation rocket engines with combustion-compensating device, its structure be the same as Example 1.
A kind of control method of the pulse detonation rocket engines with combustion-compensating device, can be specifically described as：Use kerosene
Make fuel, make oxidant using oxygen purity for 40% oxygen-enriched air, isolation gas uses nitrogen, and jet uses carrier of oxygen
Fraction is 50% oxygen-enriched air, using control sequential as shown in Figure 5；After check device is errorless, adjustment fuel and oxidation
The supply pressure of agent is respectively 0.5MPa and 1.0MPa, and explosive mixture equivalent proportion is 1.5；Set according to Fig. 5 work schedule
First electrically-controlled valve 1-3, the second electrically-controlled valve 2-4, the 3rd electrically-controlled valve 3-3, the specific works ginseng of the 4th electrically-controlled valve 4-3 and spark plug 5
Number, and be uniformly controlled by control unit 7；The initial pressure of jet is 1.0MPa；Engine is started by control unit 7, started
Igniting, now will produce stable high frequency detonation wave in detonation tube 6.Pass through the first load cell 6-5, the second load cell
The pressure in detonation tube main cavity 6-1 that 6-8 and the 3rd load cell 6-9 are measured is respectively labeled as p1, p2And p3, measurement knot
Fruit is as shown in Figure 6.From fig. 6, it can be seen that it is same as Example 1, add the pressure peak in detonation tube main cavity 6-1 after jet
Decline.Meanwhile, compared with the operating mode for being not added with jet, the average thrust of engine adds 77.7%.
In conjunction with the embodiments 1 and embodiment 2, now the advantage to the present invention be further described：Pulse-knocking rocket motor
After machine is started working, detonation wave is produced rapidly and propagated to the openend of detonation tube 6, due to pulse detonation rocket engines at this stage
Middle atomizing of liquid fuel and, in combustion product meeting residual fraction fuel not perfect with the blending of oxidant, are penetrated by control
Stream flow and oxygen content can promote the Fuel Remained in detonating combustion product further to burn, while alleviating exhaust process latter end
The mistake expansion issues that tail gas is caused when flowing through nozzle divergence cone, and then improve thrust and the fuel specific impulse of engine；Now
Because the equivalent proportion of flammable mixture is relatively low, pinking intensity of wave will weaken, and then the intensity of weakening jet pipe throat reflected shock wave,
The interference to detonation tube blind end flow field is reduced, is beneficial to PDRE stable operation, and poor oil firing reduces the row of pollutant
Put；In PDRE running, adjust jet hand-hole 6-4 supply flow rate and feed fluid oxygen content to improve detonation tube
Combustion case in 6, such as exhaust process latter end increase jet flow, can effectively reduce working medium cross expansion pushed away to engine
The loss that power is brought.
Claims (6)
1. a kind of pulse detonation rocket engines with combustion-compensating device, it is characterised in that：The pulse detonation rocket engines bag
Include oxidant feed system, fuel feed system, isolation gas feed system, jet feed system, whistle control system and pinking
Six parts of pipe.Oxidant feed system includes the first oxidant air accumulator 1-1, the first pressure-reducing valve 1-2, the first electrically-controlled valve 1-3
With first check-valve 1-4；Fuel feed system includes extruding gas air accumulator 2-1, the second pressure-reducing valve 2-2, fuel oil storage tank 2-3 and the
Two electrically-controlled valve 2-4；Isolating gas feed system includes isolation gas air accumulator 3-1, the 3rd pressure-reducing valve 3-2 and the 3rd electrically-controlled valve 3-3；Penetrate
Flowing feed system includes the second oxidant air accumulator 4-1, the 4th pressure-reducing valve 4-2, the 4th electrically-controlled valve 4-3 and second check-valve 4-4；
Main chamber is detonation tube 6, and its concrete structure is detonation tube main cavity 6-1, propellant spray hole 6-2, oxidant spray circumferential weld 6-
3, spark plug 5, pinking intensifier 6-4, the first load cell 6-5, jet spray section 6-6, jet spray orifice 6-7, jet
Spray circumferential weld 6-13, the second load cell 6-8, the 3rd load cell 6-9, jet pipe 6-10, first flange 6-12 and
Two flange 6-11.Jet spray circumferential weld 6-13 is located in jet spray section 6-6, its injection direction and detonation tube main cavity 6-1
Axial angle into 30~50 °, and towards detonation tube main cavity 6-1 caudal directions；Installed in detonation tube main cavity 6-1 afterbodys
Jet pipe 6-10, jet pipe expands jet pipe to receive；Jet pipe 6-10 passes through first flange 6-12 and second flange 6-11 and detonation tube
Main cavity 6-1 connections；Whistle control system mainly includes control unit 7.
2. a kind of pulse detonation rocket engines with combustion-compensating device, it is characterised in that：Fuel uses liquid fuel；Oxidant
Use oxygen；The oxidant that the jet of detonation tube afterbody injection is oxygen content 30%-70%.
3. a kind of pulse detonation rocket engines with combustion-compensating device, it is characterised in that：By in detonation tube afterbody spray oxygen
Agent jet, can promote the residual fuel of detonation tube afterbody to burn away heat release, improve the acting ability of working medium, and increase pulse is quick-fried
Shake thrust and the fuel specific impulse of rocket engine.
4. a kind of control method of the pulse detonation rocket engines with combustion-compensating device, it is characterised in that：By in detonation tube
Afterbody injects the jet of different oxygen content and flow, can effectively adjust the flow condition of tail gas, it is avoided in nozzle-divergence
Section produced expansion-loss, and then improved the propulsive performance of pulse detonation rocket engines.
5. a kind of control method of the pulse detonation rocket engines with combustion-compensating device, it is characterised in that：By adjust fuel oil,
Oxidant and the respective supply pressure of afterbody jet and flow, can adjust the equivalent proportion distribution of explosive mixture in detonation tube；Adjust
Whole purpose is that blind end equivalent proportion is larger, beneficial to the starting of detonation wave；Afterbody equivalent is smaller, promotes full combustion of fuel, carries
High fuel utilization rate, reduces the noxious pollutant in combustion product.
6. a kind of control method of the pulse detonation rocket engines with combustion-compensating device, it is characterised in that：The use drop of jet
The low equivalent proportion of detonation tube afterbody mixture, weakens the intensity of detonation wave at this, weakens the reflected shock wave pair being induced by it
The interference of upstream flow field in detonation tube, improves engine job stability.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710346783.2A CN107044361A (en) | 2017-05-17 | 2017-05-17 | A kind of pulse detonation rocket engines and control method with combustion-compensating device |
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| CN201710346783.2A CN107044361A (en) | 2017-05-17 | 2017-05-17 | A kind of pulse detonation rocket engines and control method with combustion-compensating device |
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| CN109252980A (en) * | 2018-11-13 | 2019-01-22 | 西北工业大学 | A kind of NEW ADAPTIVE pulse-knocking engine propellant spray system |
| CN112324586A (en) * | 2021-01-04 | 2021-02-05 | 成都裕鸢航空零部件制造有限公司 | Aeroengine combustion chamber and working method thereof |
| CN113153570A (en) * | 2021-05-27 | 2021-07-23 | 中国航空发动机研究院 | Pulse detonation tube performance calculation method and device |
| CN113970445A (en) * | 2021-10-14 | 2022-01-25 | 上海交通大学 | Entropy-sound test platform and test method thereof |
| US20220178658A1 (en) * | 2019-04-11 | 2022-06-09 | Israel Aerospace Industries Ltd. | Method of controlling ejection of a missile from a canister and system therefor |
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Application publication date: 20170815 |