CN107218155B - A kind of pulse ignite in advance can steady operation detonation engine - Google Patents
A kind of pulse ignite in advance can steady operation detonation engine Download PDFInfo
- Publication number
- CN107218155B CN107218155B CN201710420199.7A CN201710420199A CN107218155B CN 107218155 B CN107218155 B CN 107218155B CN 201710420199 A CN201710420199 A CN 201710420199A CN 107218155 B CN107218155 B CN 107218155B
- Authority
- CN
- China
- Prior art keywords
- combustion tube
- ignite
- advance
- air
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The present invention be a kind of pulse ignite in advance can steady operation detonation engine, including ignite combustion tube in advance（1）, helical blade（2）, fuel-air premixer（3）, negative pole pressurizing base（10）, anode rotation pressurization base（13）, premixer's inside spin flow guide bar（14）, pre- ignite combustion tube external spiral flow guide bar（15）, high-tension ignition control ECU（19）, pinking jet pipe（22）.Premixer's inside spin flow guide bar（14）Combustion tube external spiral flow guide bar is ignited with pre-（15）So that explosive gaseous mixture is sufficiently mixed and form eddy airstream, the air-flow in convergent point is burned is lighted, and pinking occurs, it is ensured that the explosive perfectly safe generation pinking of gaseous mixture.It has the following advantages that：（1）It is able to solve the detonation, control and quickly holding of pinking；（2）It can be realized the atomization, injection, blending of liquid fuel and oxidant；（3）It can produce steady propulsion, and can realize high-frequency work.
Description
Technical field
The present invention relates to a kind of dynamic power machine, especially a kind of pulse ignite in advance can steady operation detonation engine, belong to
In aviation power technical field.
Background technique
Pulse-knocking engine (PDE) in the combustion chamber directly using the detonation wave of detonating combustion generation come compressed gas,
And then generate power.Compared with conventional engines, pulse-knocking engine eliminates the components such as compressor, turbine, has knot
The features such as structure is simple, thrust ratio is high, low in cost.Following either rocket, guided missile or the sky and space plane can use pulse
Detonation engine, it is also considered as 21 century most potential empty day power project.
The groundwork step of PDE includes four steps：The first step, detonation combustor be full of explosive mixture, second step,
Opening or closed end in combustion chamber excite detonation wave；Third step propagates detonation wave in the combustion chamber, and arranges in open end
Out；4th step is discharged combustion product from combustion chamber by a cleanup process.PDE has the following advantages that：Structure is simple
（Without rotary parts such as turbines）, size it is small（No more than 2 meters）, it is applied widely, at low cost, can use under the low speed, effect of burning
Rate is high, high speed performance is superior.It is estimated that the thrust ratio of PDE is up to 20, range of Mach numbers 0 ~ 10（Air suction type is 0 ~ 3 or 5）, fly
Row 0 ~ 50km of altitude range, thrust range 0.5kg ~ 50000kg, oil consumption rate is less than 1kg/kg*h.Pulse-knocking engine does not have
The rotary part being easily damaged, therefore structure is simpler, maintenance is easier.In addition, PDE can be used current material and with existing work
Skill production., it is expected that the cost of PDE cheap than supersonic turbine engine price 75%.PDE be at present it is only it is a kind of can be with double
The engine concept of mode work, it can be worked with air suction type and rocket type both of which.Such as in Ma number 0 ~ 3 and higher model
With the propulsion of effective air suction type in enclosing, then with the work of pulse-knocking rocket mode.Therefore, PDE is the following military and aviation boat
The promising new concept engine of its transport field.
Technological difficulties
Although the concept of PDE has been verified in laboratory, need to solve there are also following technical problem：
1）The detonation of pinking, control and keep quickly and reliably detonation be make PDE obtain practical most significant problems it
One, because high working frequency and ignition times repeatedly are the basic demands that PDE is worked normally.Changed using detonation to pinking
（DDT）Process is the preferred plan of recent PDE research.Since these data are in even concentration, without the mixture of temperature gradient
Middle single pinking as a result, almost different from the case where multiple pinking.In addition, the working frequency of practical PDE is very high, gas is mixed
Quickly, the result under low frequency is difficult as the design considerations under high frequency flow velocity.Therefore, to develop PDE, it is necessary to largely be tried
It tests, solves detonation problem.Including initiation energy, DDT method, the reinforcing of DDT, pinking from constrained environment to the mistake of untethered environment
It crosses；
2）Atomization, injection, the blending of liquid fuel and oxidant.For the PDE of combusting liquid fuel, the spray of fuel
It penetrates, blend and lights a fire and is extremely difficult.With fast reaction, high mass flow rate and there is the spraying system of high controllability to satisfaction
The high frequency operation of PDE is particularly significant.Spraying system must satisfy the requirement of cost, weight, volume and power etc..Therefore,
It should study and be sprayed with gas and liquid fuel, blend related physics, chemically and thermally force characteristic；
3）Act on the closure wall of PDE detonation chamber end（Thrust wall）On detonation pressure so that chemical energy is converted into kinetic energy.
The accessory power system that PDE needs to detonate and flow control, and it is also possible that the power extraction system for specific use.
In addition, PDE also needs to design quick acting, the propulsion valve with flying weight and fuel valve and control system component, Yi Jixian
Into combustion control system, effective import and jet pipe, consider system peculiar part comprehensive design scheme；
4）Since thrust is unstable, the PDE of practical application is needed using high frequency（Greater than 80 hertz）Multipipe structure, and it is more
There are problems that power coupling between pipe detonation combustor；
5）Cooling problem.The very high speed of hot combustion gas after detonation wave, causes the increase of tube wall heat, it is therefore necessary to take height
The cooling provision of effect；
6）Strong vibration and huge noise can be generated when detonating combustion.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of pulse ignite in advance can steady operation detonation engine,
Structure is simple, and the steady operation of pulse-knocking engine is realized using mechanism of igniting in advance.
The present invention by igniting combustion tube in advance（1）, helical blade（2）, fuel-air premixer（3）, air inlet（4）, fuel
Injector head（5）, one-way membrane ignite combustion tube front end fixed frame in advance（6）, pre- ignite combustion tube inlet valve（7）, ignite combustion tube in advance
Air inlet（8）, fuel-air premix chamber enclosure（9）, negative pole pressurizing base（10）, insulation tube（11）, cathode light a fire metal strip（12）,
Anode rotation pressurization base（13）, premixer's inside spin flow guide bar（14）, pre- ignite combustion tube external spiral flow guide bar（15）, pre- ignite
Combustion tube helical blade shaft（16）, pre- ignite combustion tube rear end fixed frame（17）, combustion gas spout（18）, high-tension ignition control
ECU（19）, HV generator（20）, power supply（21）, pinking jet pipe（22）, capacitor（23）It constitutes.
The technical scheme adopted by the invention is that：In fuel-air premixer（3）It is built into pre- ignition combustion tube（1）, and
Combustion tube front end fixed frame is ignited in advance equipped with one-way membrane, for fixed pre- ignition combustion tube（1）, before one-way membrane ignites combustion tube in advance
Hold fixed frame（6）Equipped with one-way membrane（24）, air-flow reflux is prevented, the pre- ignition combustion tube（1）Front end is equipped with pre- ignition combustion tube
Air inlet（8）, pre- to ignite combustion tube air inlet（8）Outside is equipped with pre- ignition combustion tube inlet valve（7）, the pre- ignition combustion tube into
Valve（7）Pre- ignition combustion tube air inlet is realized by rotation（8）Open and close, it is pre- to ignite combustion tube inlet valve（7）On
Welding is pre- to ignite combustion tube helical blade shaft, pre- ignition combustion tube helical blade shaft（16）It is equipped with helical blade（2）,
It is pre- to ignite combustion tube helical blade shaft（16）On helical blade（2）The anode rotation pressurization base of strip is welded on middle section
（13）, strip anode rotation pressurization base（13）Shape be helical form, helical structure and helical blade（2）It is identical, it is pre- to ignite
Combustion tube helical blade shaft（16）Connect HV generator（20）High-voltage output end, HV generator（20）Even
Meet high-tension ignition control ECU（19）, for controlling high-voltage electricity spark rate and voltage, so that anode rotation pressurization base（13）Band is high
Electrostatic is pressed, rotates pressurization base with anode（13）Corresponding position is similarly equipped with spiral helicine negative pole pressurizing base（10）, this is negative
Pole is pressurized base（10）For high-temperature insulation material, insertion is fixed on pre- ignition combustion tube（1）In inner wall, in negative pole pressurizing base（10）
The top of curved surface is embedded with the cathode igniting metal strip of strip-spiral（12）, cathode igniting metal strip（12）With negative pole pressurizing base
（10）Pass through insulation tube（11）Cathode conductor is drawn, which concatenates a capacitor（23）After connect power supply（21）It is negative
Pole, capacitor and power sources in parallel, ignite combustion tube in advance（1）It is provided with pre- ignition combustion tube external spiral flow guide bar（15）, pre- to ignite combustion
Burn pipe（1）Ignite combustion tube front end fixed frame in advance by one-way membrane（6）Combustion tube rear end fixed frame is ignited with pre-（17）It is fixed on
Fuel-air premixer（3）In cavity, the pre- ignition combustion tube（1）Outer diameter be less than fuel-air premixer（3）The 1/ of internal diameter
2, fuel-air premixer（3）Cavity inner wall is provided with premixer's inside spin flow guide bar（14）, fuel-air premixer（3）After
End is pinking jet pipe（22）, fuel-air premixer（3）Top be provided with propellant spray head（5）, outside fuel-air premixer
Shell（9）Front end be equipped with round air inlet（4）.
One-way membrane ignites combustion tube front end fixed frame in advance（6）It is equipped with petal-shaped one-way membrane（24）, the one-way membrane is using tool
The metal film of flexible is constituted.
Working principle：In fuel-air premixer（3）It is built into pre- ignition combustion tube（1）, effect be for igniting,
Fuel-air premixer（3）It is built into pre- ignition combustion tube（1）, and be equipped with one-way membrane and ignite combustion tube front end fixed frame in advance, it uses
In fixed pre- ignition combustion tube（1）, one-way membrane ignites combustion tube front end fixed frame in advance（6）Equipped with one-way membrane（24）, prevent air-flow
Reflux, the pre- ignition combustion tube（1）Front end is equipped with pre- ignition combustion tube air inlet（8）, incoming air carries out mixing it with fuel
Afterwards, belong to rich mixture, by igniting combustion tube air inlet in advance（8）Outside is equipped with pre- ignition combustion tube inlet valve（7）It enters
It is pre- to ignite combustion tube（1）Cavity in（Referring to the A-A Local map in Fig. 1）, pre- to ignite combustion tube inlet valve（7）It is real by rotation
Combustion tube air inlet is now ignited in advance（8）Switch close, it is pre- to ignite combustion tube helical blade shaft（16）Equipped with helical blade（2）Rotation
It pushes explosive gaseous mixture to flow downward during turning, is igniting combustion tube helical blade shaft in advance（16）Helical blade（2）
The anode rotation pressurization base of strip is welded on middle section（13）, strip anode rotation pressurization base（13）Shape be helical form, spiral shell
Revolve structure and helical blade（2）It is identical, it is pre- to ignite combustion tube helical blade shaft（16）Connect HV generator（20）'s
High-voltage output end, HV generator（20）It connects high-tension ignition and controls ECU（19）, for control high-voltage electricity spark rate and
Voltage, so that anode rotation pressurization base（13）Band high-pressure electrostatic rotates pressurization base with anode（13）Corresponding position is also the same
Equipped with spiral helicine negative pole pressurizing base（10）, the negative pole pressurizing base（10）For high-temperature insulation material, insertion is fixed on pre- ignition
Combustion tube（1）In inner wall, in negative pole pressurizing base（10）The top of curved surface is embedded with the cathode igniting metal strip of strip-spiral（12）,
Cathode igniting metal strip（12）With negative pole pressurizing base（10）Pass through insulation tube（11）Cathode conductor is drawn, which connects
Connect power supply（21）Cathode passes through rotation between such positive and negative anodes（Referring to the B-B Local map in Fig. 1）, by nearest place hair
Raw electric discharge, lights gaseous mixture, and gas is sprayed from combustion gas spout in burning；At the same time, fuel-air premixes chamber enclosure（9）Before
End is equipped with round air inlet（4）, incoming air enters after air inlet, with fuel-air premixer（3）Top setting combustion
Expect injector head（5）The atomized liquid fuel of ejection is tentatively mixed, and air-flow hits pre- ignition combustion tube inlet valve（7）It is laggard
Row shunts, and hits one-way membrane again and ignites combustion tube front end fixed frame in advance（6）Sinuous flow is formed, further gaseous mixture is mixed
It closes, gas enters fuel-air premixer（It is interior）, due to igniting combustion tube in advance（1）It is provided with pre- ignition combustion tube external spiral water conservancy diversion
Item（15）, combustion tube is ignited in advance（1）Ignite combustion tube front end fixed frame in advance by one-way membrane（6）Consolidate with pre- combustion tube rear end of igniting
Determine frame（17）It is fixed on fuel-air premixer（3）In cavity, the pre- ignition combustion tube（1）Outer diameter less than fuel-air premix
Room（3）Cavity internal diameter, cavity inner wall are provided with premixer's inside spin flow guide bar（14）, the chaotic air-flow structure of such structure guidance
At the explosive mixed airflow that is vortexed, which is passing through pre- ignition combustion tube rear end fixed frame（17）It is disturbed again, this process
So that incoming air and atomized fuel carried out it is sufficient mix, and constitute eddy airstream, igniting combustion tube in advance（1）Tail
End merges, at the same time, combustion gas spout（18）Gas injection is to point in the burning of middle ejection, in pinking jet pipe（22）
Front end ignite and mixed sufficient explosive gaseous mixture, generate pinking, detonation wave is in pinking jet pipe（22）Interior propagation acting, burning
Gas afterwards is from pinking jet pipe（22）Tail end discharge, thus constitutes a complete period.
The invention has following features for past detonation engine
1）In whole work process, combustion tube directly is ignited using pre-（1）The flowing of interior burning gases forces helical-blade
Piece（2）Rotation, to realize pre- ignition combustion tube inlet valve（7）Open and close, there is no need to increase additional transmission mechanism, greatly
Structure is simplified greatly；
2）Helical blade（2）Per revolution, igniting is primary, at the same time, pre- to ignite combustion tube inlet valve（7）Unlatching
Once, it when igniting, is rotated by anode and is pressurized base（13）With negative pole pressurizing base（10）The top of curved surface is embedded with spiral
The cathode igniting metal strip of strip（12）It realizes igniting, igniting is directly realized by distance each other, so that igniting is
It is controllable under high frequency condition, it is often more important that HV generator（20）It connects high-tension ignition and controls ECU（19）, can control
High-voltage electricity spark rate and voltage, this design is so that igniting becomes controllable；
3）Premixer's inside spin flow guide bar（14）Combustion tube external spiral flow guide bar is ignited with pre-（15）So that explosive gaseous mixture
It can be sufficiently mixed and be formed eddy airstream, and the air-flow in convergent point is burned is lighted, and pinking occurs.Aflame gas
From combustion gas spout（18）Middle ejection has high temperature, wants high several orders of magnitude compared to the ignition energy of electronic ignition, it is ensured that
Pinking occurs for explosive gaseous mixture；
4）In order to reduce energy consumption, a high voltage bearing bulky capacitor C can be used and absorb high-voltage pulse current, then electric discharge is to electricity
Source（21）, recycle electric energy.
The beneficial effects of the invention are as follows:（1）It is able to solve the detonation, control and quickly holding of pinking；（2）It can be realized liquid
Atomization, injection, the blending of fluid fuel and oxidant；（3）It can produce steady propulsion, and high frequency may be implemented（Greater than 80 hertz）
Work.But for strong vibration and huge noise can be generated up for further solving when cooling problem and detonating combustion.
The invention solves the main difficulty of pulse-knocking engine faced simultaneously, has good market prospects.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is overall work schematic diagram of the invention.
In Fig. 1-2：1. combustion tube is ignited in advance, 2. helical blades, 3. fuel-air premixers, 4. air inlets, the spray of 5. fuel
Head, 6. one-way membranes ignite combustion tube front end fixed frame, 7. pre- ignition combustion tube inlet valves, 8. pre- ignition combustion tube air inlets in advance
Mouthful, 9. fuel-airs premix chamber enclosure, 10. negative pole pressurizing bases, 11. insulation tubes, 12. cathode igniting metal strip, 13. anode rotations
It is pressurized base, 14. premixer's inside spin flow guide bars, 15. pre- ignition combustion tube external spiral flow guide bars, 16. pre- ignition combustion tube spirals
Blade rotor, 17. pre- ignition combustion tube rear end fixed frames, 18. combustion gas spouts, 19. high-tension ignitions control ECU, 20. high-pressure electrostatics
Generator, 21. power supplys, 22. pinking jet pipes, 23. capacitors, 24. one-way membranes.
Specific embodiment
With reference to the accompanying drawing 1 and embodiment the invention will be further described.
In fuel-air premixer（3）It is built into pre- ignition combustion tube（1）, in fuel-air premixer（3）It is built into pre-
Ignite combustion tube（1）, and be equipped with one-way membrane and ignite combustion tube front end fixed frame in advance, for fixed pre- ignition combustion tube（1）, unidirectionally
Film ignites combustion tube front end fixed frame in advance（6）Equipped with one-way membrane（24）, air-flow reflux is prevented, the pre- ignition combustion tube（1）Front end
Combustion tube air inlet is ignited equipped with pre-（8）, pre- to ignite combustion tube air inlet（8）Outside is equipped with pre- ignition combustion tube inlet valve（7）,
The pre- ignition combustion tube inlet valve（7）Pre- ignition combustion tube air inlet is realized by rotation（8）Open and close, it is pre- to ignite combustion
Burn pipe inlet valve（7）Upper welding is pre- to ignite combustion tube helical blade shaft, pre- ignition combustion tube helical blade shaft（16）On set
There is helical blade（2）, combustion tube helical blade shaft is being ignited in advance（16）On helical blade（2）Strip is being welded just on middle section
Pole rotation pressurization base（13）, strip anode rotation pressurization base（13）Shape be helical form, helical structure and helical blade（2）
It is identical, it is pre- to ignite combustion tube helical blade shaft（16）Connect HV generator（20）High-voltage output end, high-pressure electrostatic
Generator（20）It connects high-tension ignition and controls ECU（19）, for controlling high-voltage electricity spark rate and voltage, so that anode rotation increases
Press base（13）Band high-pressure electrostatic rotates pressurization base with anode（13）Corresponding position is similarly equipped with spiral helicine negative pole pressurizing
Base（10）, the negative pole pressurizing base（10）For high-temperature insulation material, specifically it can be embedded in Ceramics material and be fixed on pre- ignition
Combustion tube（1）In inner wall, in negative pole pressurizing base（10）The top of curved surface is embedded with the cathode igniting metal strip of strip-spiral（12）,
Cathode igniting metal strip（12）With negative pole pressurizing base（10）Pass through insulation tube（11）Cathode conductor is drawn, the cathode conductor string
Connect a capacitor（23）After connect power supply（21）Cathode, capacitor and power sources in parallel, ignite combustion tube in advance（1）It is provided with pre- ignition combustion
Burn pipe external spiral flow guide bar（15）, combustion tube is ignited in advance（1）Ignite combustion tube front end fixed frame in advance by one-way membrane（6）With draw in advance
Quick-fried combustion tube rear end fixed frame（17）It is fixed on fuel-air premixer（3）In cavity, the pre- ignition combustion tube（1）Outer diameter it is small
In fuel-air premixer（3）The 1/2 of internal diameter, fuel-air premixer（3）Cavity inner wall is provided with premixer's inside spin water conservancy diversion
Item（14）, fuel-air premixer（3）Rear end be pinking jet pipe（22）, fuel-air premixer（3）Top be provided with combustion
Expect injector head（5）, fuel-air premix chamber enclosure（9）Front end be equipped with round air inlet（4）.
Claims (2)
1. a kind of pulse ignite in advance can steady operation detonation engine, it is characterized in that：By igniting combustion tube in advance（1）, helical-blade
Piece（2）, fuel-air premixer（3）, air inlet（4）, propellant spray head（5）, one-way membrane ignite combustion tube front end fixed frame in advance
（6）, pre- ignite combustion tube inlet valve（7）, pre- ignite combustion tube air inlet（8）, fuel-air premix chamber enclosure（9）, cathode increase
Press base（10）, insulation tube（11）, cathode light a fire metal strip（12）, anode rotation pressurization base（13）, premixer's inside spin flow guide bar
（14）, pre- ignite combustion tube external spiral flow guide bar（15）, pre- ignite combustion tube helical blade shaft（16）, it is pre- ignite combustion tube after
Hold fixed frame（17）, combustion gas spout（18）, high-tension ignition control ECU（19）, HV generator（20）, power supply（21）, it is quick-fried
Shake jet pipe（22）, capacitor（23）, one-way membrane（24）It constitutes；
In fuel-air premixer（3）It is built into pre- ignition combustion tube（1）, and ignite combustion tube front end in advance equipped with one-way membrane and fix
Frame, for fixed pre- ignition combustion tube（1）, one-way membrane ignites combustion tube front end fixed frame in advance（6）Equipped with one-way membrane（24）, prevent
Air-flow reflux, the pre- ignition combustion tube（1）Front end is equipped with pre- ignition combustion tube air inlet（8）, pre- to ignite combustion tube air inlet（8）
Outside is equipped with pre- ignition combustion tube inlet valve（7）, the pre- ignition combustion tube inlet valve（7）Pre- ignition combustion tube is realized by rotation
Air inlet（8）Open and close, it is pre- to ignite combustion tube inlet valve（7）Upper welding is pre- to ignite combustion tube helical blade shaft
（16）, the pre- ignition combustion tube helical blade shaft is equipped with helical blade（2）, combustion tube helical blade shaft is being ignited in advance（16）
Helical blade（2）The anode rotation pressurization base of strip is welded on middle section（13）, strip anode rotation pressurization base（13）Shape
Shape is helical form, helical structure and helical blade（2）It is identical, it is pre- to ignite combustion tube helical blade shaft（16）Connect high-pressure electrostatic
Generator（20）High-voltage output end, HV generator（20）It connects high-tension ignition and controls ECU（19）, for controlling high pressure
Electric ignition frequency and voltage, so that anode rotation pressurization base（13）Band high-pressure electrostatic rotates pressurization base with anode（13）It is corresponding
Position be similarly equipped with spiral helicine negative pole pressurizing base（10）, the negative pole pressurizing base（10）For high-temperature insulation material, insertion
It is fixed on pre- ignition combustion tube（1）In inner wall, in negative pole pressurizing base（10）The top of curved surface is embedded with the cathode point of strip-spiral
Fiery metal strip（12）, cathode igniting metal strip（12）With negative pole pressurizing base（10）Pass through insulation tube（11）Cathode conductor is drawn
Out, which concatenates a capacitor（23）After connect power supply（21）Cathode, capacitor and power sources in parallel, ignite combustion tube in advance
（1）It is provided with pre- ignition combustion tube external spiral flow guide bar（15）, combustion tube is ignited in advance（1）Before igniting combustion tube in advance by one-way membrane
Hold fixed frame（6）Combustion tube rear end fixed frame is ignited with pre-（17）It is fixed on fuel-air premixer（3）In cavity, the pre- ignition
Combustion tube（1）Outer diameter be less than fuel-air premixer（3）The 1/2 of internal diameter, fuel-air premixer（3）Cavity inner wall is provided with
Premixer's inside spin flow guide bar（14）, fuel-air premixer（3）Rear end be pinking jet pipe（22）, fuel-air premixer
（3）Top be provided with propellant spray head（5）, fuel-air premix chamber enclosure（9）Front end be equipped with round air inlet（4）.
2. a kind of pulse according to claim 1 ignite in advance can steady operation detonation engine, it is characterized in that one-way membrane
It is pre- to ignite combustion tube front end fixed frame（6）It is equipped with petal-shaped one-way membrane（24）, the one-way membrane is using the metal film with toughness
It constitutes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710420199.7A CN107218155B (en) | 2017-06-06 | 2017-06-06 | A kind of pulse ignite in advance can steady operation detonation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710420199.7A CN107218155B (en) | 2017-06-06 | 2017-06-06 | A kind of pulse ignite in advance can steady operation detonation engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107218155A CN107218155A (en) | 2017-09-29 |
| CN107218155B true CN107218155B (en) | 2018-11-16 |
Family
ID=59948212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710420199.7A Active CN107218155B (en) | 2017-06-06 | 2017-06-06 | A kind of pulse ignite in advance can steady operation detonation engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107218155B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110425045B (en) * | 2019-08-13 | 2024-02-06 | 清华大学 | Continuous rotation detonation engine |
| CN111120144B (en) * | 2020-01-07 | 2021-01-05 | 姚长水 | Self-adaptive variable-frequency mutual control type pulse detonation aircraft engine and using method thereof |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101881238B (en) * | 2010-06-10 | 2013-04-17 | 西北工业大学 | Air-breathing pulse detonation engine and detonation method thereof |
| US8683780B2 (en) * | 2010-12-28 | 2014-04-01 | Masayoshi Shimo | Gas turbine engine and pulse detonation combustion system |
| US20120192545A1 (en) * | 2011-01-28 | 2012-08-02 | General Electric Company | Pulse Detonation Combustor Nozzles |
| CN103883428B (en) * | 2014-03-28 | 2016-05-25 | 西北工业大学 | A kind of air-breathing pulse detonation engine antireflux air intake structure |
-
2017
- 2017-06-06 CN CN201710420199.7A patent/CN107218155B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN107218155A (en) | 2017-09-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112879178B (en) | Solid rocket ramjet based on detonation combustion | |
| US8443583B2 (en) | Pilot fuel injection for a wave rotor engine | |
| US8683780B2 (en) | Gas turbine engine and pulse detonation combustion system | |
| US20070180814A1 (en) | Direct liquid fuel injection and ignition for a pulse detonation combustor | |
| CN105972638B (en) | A kind of reverse-flow type pulse detonation combustor | |
| CN107762661B (en) | A kind of pulse-knocking injection ultra-combustion ramjet combined engine | |
| JP2005233068A (en) | Pulse detonation engine | |
| US8006500B1 (en) | Swirl combustor with counter swirl fuel slinger | |
| CN112902225A (en) | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber | |
| CN110718843B (en) | Air-breathing type continuous rotation detonation combustion driven premixing type carbon dioxide pneumatic laser | |
| CN106640420B (en) | A kind of pulse-knocking engine of side air inlet | |
| JP2011127890A (en) | Pulse detonation system with fuel lean inlet region | |
| CN109184953A (en) | A kind of rocket type rotation pinking punching press combined engine | |
| CN108869095B (en) | Boundary suction control method with stable and self-sustaining supersonic detonation | |
| CN107218155B (en) | A kind of pulse ignite in advance can steady operation detonation engine | |
| CN109028150A (en) | For rotating the effervesce atomization structure and operating method of pinking propulsion system | |
| CN206397619U (en) | A kind of pulse-knocking engine of side exhaust | |
| CN101718236A (en) | Multitube pulse detonation combustion chamber communicated with jet deflector | |
| US2982095A (en) | Gas generating device | |
| CN111305972A (en) | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation | |
| RU2387582C2 (en) | Complex for reactive flight | |
| CN106640421B (en) | A kind of pulse-knocking engine of side exhaust | |
| CN109209681A (en) | A kind of pulse-knocking engine detonation tube structure of reverse-flow type | |
| CN204877714U (en) | Aviation, space flight, navigation in mixed engine of an organic whole | |
| CN107143432B (en) | High-piezoelectricity plasma gas relay couples spark knock engine before a kind of detonation wave |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20181008 Address after: 510450 No. 36 Ching street, Lake Town, man Town, Baiyun District, Guangzhou, Guangdong Applicant after: Guangzhou Parker Aviation Equipment Co., Ltd. Address before: 650224 9-2 1-202, century long yuan, Bailong Road, Panlong District, Kunming, Yunnan Applicant before: Chen Shuqiao |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |