CN115045776B - Dual-fuel isolation-free pulse detonation engine device and control method thereof - Google Patents
Dual-fuel isolation-free pulse detonation engine device and control method thereof Download PDFInfo
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- CN115045776B CN115045776B CN202210459739.3A CN202210459739A CN115045776B CN 115045776 B CN115045776 B CN 115045776B CN 202210459739 A CN202210459739 A CN 202210459739A CN 115045776 B CN115045776 B CN 115045776B
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- 238000005474 detonation Methods 0.000 title claims abstract description 102
- 239000000446 fuel Substances 0.000 title claims abstract description 55
- 238000000034 method Methods 0.000 title claims abstract description 40
- LCGLNKUTAGEVQW-UHFFFAOYSA-N Dimethyl ether Chemical compound COC LCGLNKUTAGEVQW-UHFFFAOYSA-N 0.000 claims abstract description 204
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 75
- 239000001301 oxygen Substances 0.000 claims abstract description 75
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 75
- 238000002485 combustion reaction Methods 0.000 claims abstract description 72
- 239000003350 kerosene Substances 0.000 claims abstract description 54
- 239000007800 oxidant agent Substances 0.000 claims abstract description 19
- 230000001590 oxidative effect Effects 0.000 claims abstract description 19
- 238000011049 filling Methods 0.000 claims abstract description 17
- 230000000694 effects Effects 0.000 claims abstract description 9
- 230000002411 adverse Effects 0.000 claims abstract description 6
- 238000013461 design Methods 0.000 claims abstract description 5
- 239000000203 mixture Substances 0.000 claims description 19
- 238000002347 injection Methods 0.000 claims description 18
- 239000007924 injection Substances 0.000 claims description 18
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 16
- 238000002955 isolation Methods 0.000 claims description 14
- 230000009977 dual effect Effects 0.000 claims description 12
- 230000008569 process Effects 0.000 claims description 9
- 239000003795 chemical substances by application Substances 0.000 claims description 8
- 238000004880 explosion Methods 0.000 claims description 8
- 229910052757 nitrogen Inorganic materials 0.000 claims description 8
- 239000003921 oil Substances 0.000 claims description 8
- 239000007789 gas Substances 0.000 claims description 6
- 230000001960 triggered effect Effects 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 5
- 239000011261 inert gas Substances 0.000 claims description 5
- 239000010742 number 1 fuel oil Substances 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 5
- 238000004200 deflagration Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 230000001737 promoting effect Effects 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000002708 enhancing effect Effects 0.000 claims description 3
- 238000001125 extrusion Methods 0.000 claims description 3
- 239000002737 fuel gas Substances 0.000 claims description 3
- 230000000977 initiatory effect Effects 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 239000002360 explosive Substances 0.000 claims description 2
- 238000005429 filling process Methods 0.000 claims description 2
- 239000002828 fuel tank Substances 0.000 claims description 2
- 238000011161 development Methods 0.000 abstract description 2
- 238000010521 absorption reaction Methods 0.000 abstract 1
- 239000003380 propellant Substances 0.000 abstract 1
- 238000009834 vaporization Methods 0.000 abstract 1
- 230000008016 vaporization Effects 0.000 abstract 1
- 230000004913 activation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
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- 238000011160 research Methods 0.000 description 1
- 238000005382 thermal cycling Methods 0.000 description 1
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
- 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
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- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R7/00—Intermittent or explosive combustion chambers
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
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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)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention provides a dual-fuel isolation-free pulse detonation engine device and a control method thereof. By means of the method of dual-fuel design of kerosene and dimethyl ether, dimethyl ether is alternately injected, and instant vaporization and heat absorption are carried out after the dimethyl ether enters a combustion chamber to form a low-temperature area, so that fresh filling fuel and oxidant are separated from high-temperature combustion products, normal operation of a detonation engine is guaranteed, meanwhile, the vaporized dimethyl ether can be fully mixed with oxygen, further, the dimethyl ether is fully combusted after detonation wave is started, contribution energy is provided for a detonation combustion system, adverse effects of inert propellant are eliminated, the propulsion efficiency of the pulse detonation engine is improved, and development of engineering application of the pulse detonation engine is promoted.
Description
Technical Field
The invention relates to the fields of detonation combustion, detonation propulsion and the like, in particular to a dual-fuel pulse detonation engine device without isolation and a control method thereof.
Background
Knocking is a combustion process that achieves a rapid chemical reaction with a lower entropy increase than slow combustion, essentially similar to isovolumetric combustion, and therefore will have a higher thermal cycling efficiency when used in a propulsion system. In addition, in the detonation combustion process, the pressure ratio of detonation waves can reach 15 to 55 times, compared with the traditional aerospace propulsion system, heavy and complex pressure boosting components such as a compressor, a turbine pump and the like can be omitted, and the structure of the propulsion system is greatly simplified. Based on the above theoretical advantages, detonation combustion and detonation propulsion have become one of the research hotspots in the current aerospace power field.
For propulsion schemes based on detonation combustion, what is more mature at the present stage is a pulse detonation engine (Pulse Detonation Engine, PDE for short). In the PDE multi-cycle working process, in order to ensure the working stability and no continuous combustion, inert isolating agents such as N 2 or H 2 O and the like are added after one cycle is finished, so that the high-temperature combustion products are prevented from igniting fresh mixture filled in the next cycle in advance. However, the injected inert isolating agent does not participate in combustion, and can take away a part of heat of a combustion system, so that the propulsion efficiency of the engine is reduced, and the practical engineering application of the PDE is restricted.
Therefore, in view of the above-mentioned drawbacks of the prior art, it is important to design a device and a method for achieving stable operation of PDE in multiple cycles without decreasing the propulsion performance. The invention provides a dual-fuel isolation-free pulse detonation engine device and a control method thereof, which can obtain multi-cycle detonation waves by utilizing dual-fuel alternate injection, do not need inert isolating agents, ensure that the propulsion efficiency of PDE is not affected, and have important significance in promoting the development and application of pulse detonation engines.
Disclosure of Invention
Technical problem to be solved
During the multi-cycle operation of a pulse detonation engine, the addition of an inert isolating agent reduces the propulsion efficiency of the PDE, impeding the engineering application of the PDE due to the need for a traditional isolating process. Therefore, the invention provides a dual-fuel non-isolation pulse detonation engine device and a control method thereof, kerosene and liquid dimethyl ether are used as dual fuels, a small amount of dimethyl ether is injected into the head of a combustion chamber when combustion is finished in one detonation cycle, and the characteristic of low boiling point of the dimethyl ether is utilized, and the dimethyl ether enters the combustion chamber to instantaneously vaporize and absorb heat, so that a low-temperature area is formed to separate high-temperature combustion products from fresh mixture filled in the next cycle, and continuous combustion is prevented. The vaporized dimethyl ether will burn in the next detonation cycle, which contributes energy to the combustion system and eliminates the adverse effect of the inert isolating agent on the propulsion efficiency of the engine. The invention can be used in the field of detonation combustion and detonation propulsion.
In order to achieve the above purpose, the invention adopts the following technical scheme:
a dual-fuel non-isolated pulse detonation engine device and a control method thereof comprise a dual-fuel non-isolated pulse detonation combustion chamber body, a detonation tube supply and control system and a control method.
The dual-fuel pulse detonation combustor body without isolation consists of a combustor head, a detonation-to-detonation transition (Deflagration to Detonation Transition, abbreviated as DDT) section and a detonation propagation section. The head of the combustion chamber axially comprises a kerosene nozzle and a dimethyl ether nozzle, an oxygen injection circumferential gap and a spark plug are circumferentially arranged, the spark plug is used for ignition, and the ignition energy is less than 50mJ; the DDT section comprises a Shchelkin spiral, which is used for enhancing the turbulence of flow, accelerating flame, promoting the conversion from knocking to knocking, and is welded on the inner wall of the combustion chamber; the detonation propagation section comprises a sensor mounting hole and a tail spray pipe, wherein the sensor mounting hole is used for mounting a pressure sensor to judge whether detonation waves are formed or not, and the tail spray pipe is used for improving thrust.
The detonation tube supply and control system consists of a coal oil tank, a dimethyl ether tank, an oxygen bottle, a nitrogen bottle, a dimethyl ether oil pump, a kerosene path electromagnetic valve, an oxygen path electromagnetic valve, a spark plug and a controller. The fuel tank and the dimethyl ether tank are used for storing liquid fuel, the fuel is supplied by adopting a nitrogen extrusion mode, the dimethyl ether is supplied by adopting an oil pump, the oxygen cylinder is used for storing high-pressure oxidant, and the mixing equivalence ratio can be adjusted by changing the supply pressure of the gas cylinder; the kerosene path electromagnetic valve and the oxygen path electromagnetic valve are respectively used for controlling the opening and closing of the kerosene tank and the oxygen cylinder; the controller is used for uniformly controlling the triggering of the fuel, the oxidant and the ignition signals of the spark plug.
The control method comprises the steps that kerosene, dimethyl ether and oxygen injection and ignition time sequences are set through a controller, after one detonation cycle is finished, the injection time sequences of the dimethyl ether and the oxygen are advanced by delta t seconds compared with the injection time sequences of the kerosene, after delta t seconds, the dimethyl ether way stops supplying, oxygen is continuously supplied, a kerosene way electromagnetic valve is opened, and after the kerosene way electromagnetic valve is filled for a period of time, the kerosene and the oxygen are closed, and ignition signals are triggered; when dimethyl ether and oxygen are simultaneously supplied, the flow of oxygen needs to be controlled to enable the injected oxygen quantity to be outside the explosion limit of the dimethyl ether, the dimethyl ether is instantaneously vaporized and absorbed after entering a combustion chamber to form a low-temperature area, kerosene is introduced after the dimethyl ether is closed to supply, at the moment, fresh filling fuel and oxidant are separated from high-temperature burnt products under the action of the low-temperature area, the fresh mixture is prevented from being ignited by high-temperature fuel gas, along with the filling, the low-temperature area moves towards an outlet of a knocking pipe, oxygen and vaporized dimethyl ether are fully mixed in the moving process, after an ignition signal is triggered, the explosion wave starts to develop and ignites the mixture of the oxygen and the dimethyl ether, the oxygen quantity in the whole process needs to be controlled to just consume the kerosene and the dimethyl ether, namely, after one cycle combustion is finished, the combustion chamber does not have oxygen, and the injected dimethyl ether is ensured not to be combusted before the explosion wave starts in the next cycle.
Specifically, one detonation cycle of a dual fuel non-sequestered pulse detonation combustor consists of filling, detonation combustion, and exhaust. In the fuel filling process, a small amount of dimethyl ether is firstly introduced, and the dimethyl ether is instantaneously vaporized and absorbed after entering a combustion chamber to form a low-temperature area, so that the supply of the dimethyl ether is stopped, and then kerosene is introduced; the oxidant uses oxygen and is supplied during the supply of dimethyl ether and kerosene; ; in the multi-cycle detonation combustion process, a fresh filling kerosene and oxygen mixture is separated from high-temperature combustion products under the action of a low-temperature zone formed after dimethyl ether injection, so that continuous combustion is avoided; after kerosene and oxygen are supplied to a predetermined filling degree, igniting the mixture by a spark plug, and forming a detonation wave by a method of converting slow combustion into detonation (Deflagration to Detonation Transition, abbreviated as DDT); after the detonation wave is started, igniting a mixture of dimethyl ether and oxygen at the downstream; the dimethyl ether can separate high-temperature combustion products from fresh mixture, promote the formation of multicycle detonation waves, participate in combustion, contribute energy to a combustion system and reduce the adverse effect of inert isolation gas on the propulsion efficiency of the pulse detonation engine.
The multi-cycle detonation wave is obtained by adopting a dual-fuel design of kerosene and dimethyl ether and alternately injecting.
The dimethyl ether is utilized to instantaneously vaporize and absorb heat after entering the combustion chamber to form a low-temperature area, so that fresh filling fuel and oxidant are separated from high-temperature combustion products, and an inert gas isolation effect is achieved; but different from inert gas, the method adopts injection of various fuels to form multi-cycle knocking, dimethyl ether can be combusted to contribute energy to the system, and adverse effects of inert isolating agents on the propulsion efficiency of the engine are eliminated.
The supply time sequence of kerosene, dimethyl ether and oxygen is controlled, so that the dimethyl ether can enter the combustion chamber in advance than the kerosene, the injection quantity of the dimethyl ether can just form an effective low-temperature zone, the direct ignition of a fresh fuel oxidant mixture is prevented, and the stable generation of multicycle detonation waves is promoted.
The equivalent ratio of the fuel to the oxidant is controlled, so that the introduced oxygen can burn the kerosene and the dimethyl ether, and the condition that no residual oxygen exists in the combustion chamber after one detonation cycle is finished is ensured, and the dimethyl ether cannot be ignited in advance.
The oxygen amount which is simultaneously introduced with the dimethyl ether is controlled to be outside the explosive limit of the dimethyl ether, so that the dimethyl ether is ensured not to burn in advance and can be well mixed with the oxygen, and the dimethyl ether is ensured to burn after the detonation wave is started.
The beneficial effects are that:
According to the dual-fuel non-isolation pulse detonation engine device and the control method thereof, inert gas is cancelled to be used as an isolating agent by alternately injecting through a method of dual-fuel design of kerosene and dimethyl ether, and the dimethyl ether is utilized to instantly evaporate and absorb heat to form a low-temperature area after entering a combustion chamber, so that fresh filling fuel and oxidant are separated from high-temperature combustion products, a fresh mixture is prevented from being ignited by the high-temperature gas, normal operation of the pulse detonation engine is ensured, meanwhile, the evaporated dimethyl ether can be fully mixed with oxygen, combustion occurs after detonation wave initiation, contribution energy is provided for a detonation combustion system, the propulsion efficiency of the engine is not reduced while normal operation of the detonation engine is realized, and a key problem that the detonation engine is oriented to engineering application is solved. The invention can be used in the field of detonation combustion and detonation propulsion.
Drawings
FIG. 1 is a diagram of a detonation combustion system of a dual fuel isolation-free pulse detonation engine device and a method of controlling the same in accordance with the present invention;
FIG. 2 is a control timing (embodiment) of a dual fuel isolation-free pulse detonation engine device and control method thereof of the present invention; wherein 1 is a kerosene nozzle, 2 is a dimethyl ether nozzle, 3 is a combustion chamber head, 4 is a DDT section, 5 is a detonation propagation section, 6 is a pressure sensor, 7 is a controller, 8 is a spark plug, 9 is an oxygen injection circumferential seam, 10-1 is an electromagnetic valve ①, 10-2 is an electromagnetic valve ②, 11 is an oxygen cylinder, 12 is a nitrogen cylinder, 13 is a dimethyl ether tank, 14 is a kerosene tank, 15 is an oil pump, 16 is an oxygen supply time sequence, 17 is a kerosene supply time sequence, 18 is a dimethyl ether supply time sequence, and 19 is an ignition time sequence.
Detailed Description
The invention will be further described with reference to the drawings and detailed description.
Referring to FIG. 1, a dual fuel non-isolated pulse detonation engine device and method of controlling the same includes a dual fuel non-isolated pulse detonation combustor body, a detonation tube supply and control system and method.
The dual-fuel pulse detonation combustor body without isolation consists of a combustor head 3, a DDT section 4 and a detonation propagation section 5. The combustion chamber head 3 axially comprises a kerosene nozzle 2 and a dimethyl ether nozzle 1, an oxygen injection circumferential gap 9 and a spark plug 8 are circumferentially arranged, the spark plug 8 is used for ignition, and the ignition energy is less than 50mJ; DDT section 4 includes a Shchelkin spiral for enhancing flow turbulence, accelerating flame, promoting deflagration to detonation transition, welded to the combustion chamber inner wall; the detonation propagation segment comprises a sensor mounting hole and a tail nozzle, wherein the sensor mounting hole is used for mounting a pressure sensor 6 to judge whether detonation waves are formed or not, and the tail nozzle is used for improving thrust.
The detonation tube supply and control system consists of a coal oil tank 14, a dimethyl ether tank 13, an oxygen bottle 11, a nitrogen bottle 12, a dimethyl ether oil pump 15, a kerosene path electromagnetic valve 10-2, an oxygen path electromagnetic valve 10-1 and a controller 7. The kerosene tank 14 and the dimethyl ether tank 13 are used for storing liquid fuel, the kerosene is supplied in a nitrogen extrusion mode, the dimethyl ether is supplied by adopting an oil pump, the oxygen cylinder 11 is used for storing high-pressure oxidant, and the mixing equivalence ratio can be adjusted by changing the supply pressure of the gas cylinder; the coal oil way electromagnetic valve 10-2 and the oxygen way electromagnetic valve 10-1 are respectively used for controlling the opening and closing of the coal oil tank and the oxygen cylinder; the controller 7 is used to control the activation of the fuel, oxidant and spark plug ignition signals in a unified manner.
The control method sets the injection and ignition time sequence of kerosene, dimethyl ether and oxygen through the controller 7, and the equivalent ratio of the mixture can be controlled by adjusting the pressure of the nitrogen cylinder 12 and the pressure of the oil pump and the oxygen cylinder 11.
Referring to fig. 2, after one knocking cycle is finished, dimethyl ether supply timing 17 and oxygen supply timing 15 are advanced by Δt seconds than kerosene supply timing 16, after Δt seconds, dimethyl ether circuit stops supplying, oxygen continues to be supplied, a kerosene circuit solenoid valve is opened, kerosene and oxygen supply are closed after filling for a period of time, and an ignition signal is triggered; when dimethyl ether and oxygen are simultaneously supplied, the oxygen flow is controlled to enable the injected oxygen quantity to be outside the explosion limit of the dimethyl ether, the dimethyl ether is instantaneously vaporized and absorbed after entering a combustion chamber to form a low-temperature area, kerosene is introduced after the dimethyl ether is closed to supply, at the moment, fresh filling fuel and oxidant are separated from high-temperature burnt products under the action of the low-temperature area, the fresh mixture is prevented from being ignited by high-temperature fuel gas, along with the filling, the low-temperature area moves towards an outlet of a knocking pipe, oxygen and vaporized dimethyl ether are fully mixed in the moving process, after an ignition signal is triggered, oxygen and dimethyl ether mixture is ignited after the explosion wave starts to develop and is successfully initiated, the oxygen quantity in the whole process is controlled to just consume the kerosene and the dimethyl ether, namely, after one cycle combustion is finished, no oxygen exists in the combustion chamber, the injected dimethyl ether is ensured not to be combusted before the initiation of the explosion wave, so that a double-fuel non-isolation pulse knocking cycle is finished, and then the multi-cycle explosion wave can be obtained by repeating the process.
The present invention is not limited to the above embodiments, and various modifications and optimization can be made to the above-described method by those skilled in the art without departing from the principles of the present invention, in conjunction with the following drawings and detailed description.
Claims (6)
1. A control method of a dual-fuel non-isolation pulse detonation engine device comprises a dual-fuel non-isolation pulse detonation combustion chamber body, a detonation tube supply and control system and a control method, and is characterized in that: one detonation cycle of a dual fuel pulse detonation combustor without isolation consists of filling, detonation combustion, and exhaust; in the fuel filling process, a small amount of dimethyl ether is firstly introduced, and the dimethyl ether is instantaneously vaporized and absorbed after entering a combustion chamber to form a low-temperature area, so that the supply of the dimethyl ether is stopped, and then kerosene is introduced; the oxidant uses oxygen and is supplied during the supply of dimethyl ether and kerosene; in the multi-cycle detonation combustion process, a fresh filling kerosene and oxygen mixture is separated from high-temperature combustion products under the action of a low-temperature zone formed after dimethyl ether injection, so that continuous combustion is avoided; after kerosene and oxygen are supplied to a predetermined filling degree, igniting the mixture by a spark plug, and forming a detonation wave by a method of converting slow combustion into detonation (Deflagration to Detonation Transition, abbreviated as DDT); after the detonation wave is started, igniting a mixture of dimethyl ether and oxygen at the downstream; the dimethyl ether can separate high-temperature combustion products from fresh mixture, promote the formation of multicycle detonation waves, participate in combustion, contribute energy to a combustion system and reduce the adverse effect of inert isolation gas on the propulsion efficiency of the pulse detonation engine;
The dual-fuel isolation-free pulse detonation combustor body consists of a combustor head, a DDT section and a detonation propagation section; the head of the combustion chamber axially comprises a kerosene nozzle and a dimethyl ether nozzle, an oxygen injection circumferential gap and a spark plug are circumferentially arranged, the spark plug is used for ignition, and the ignition energy is less than 50mJ; the DDT section comprises a Shchelkin spiral, which is used for enhancing flow field disturbance and promoting the conversion from knocking to knocking, and is welded on the inner wall of the combustion chamber; the detonation propagation section comprises a sensor mounting hole and a tail spray pipe, wherein the sensor mounting hole is used for mounting a pressure sensor to judge whether detonation waves are formed or not, and the tail spray pipe is used for improving thrust;
The detonation tube supply and control system consists of a coal oil tank, a dimethyl ether tank, an oxygen bottle, a nitrogen bottle, a dimethyl ether oil pump, a kerosene path electromagnetic valve, an oxygen path electromagnetic valve, a spark plug and a controller; the fuel tank and the dimethyl ether tank are used for storing liquid fuel, the fuel is supplied by adopting a nitrogen extrusion mode, the dimethyl ether is supplied by adopting an oil pump, the oxygen cylinder is used for storing high-pressure oxidant, and the mixing equivalence ratio can be adjusted by changing the supply pressure of the gas cylinder; the kerosene path electromagnetic valve and the oxygen path electromagnetic valve are respectively used for controlling the opening and closing of the kerosene tank and the oxygen cylinder; the controller is used for uniformly controlling the triggering of the fuel, the oxidant and the ignition signals of the spark plug;
The control method comprises the steps that kerosene, dimethyl ether and oxygen injection and ignition time sequences are set through a controller, after one detonation cycle is finished, the injection time sequences of the dimethyl ether and the oxygen are advanced by delta t seconds compared with the injection time sequences of the kerosene, after delta t seconds, the dimethyl ether way stops supplying, oxygen is continuously supplied, a kerosene way electromagnetic valve is opened, and after the kerosene way electromagnetic valve is filled for a period of time, the kerosene and the oxygen are closed, and ignition signals are triggered; when dimethyl ether and oxygen are simultaneously supplied, the flow of oxygen is required to be controlled to enable the injected oxygen quantity to be outside the explosion limit of the dimethyl ether, the dimethyl ether is instantaneously vaporized and absorbed after entering a combustion chamber to form a low-temperature region, kerosene is introduced after the dimethyl ether supply is closed, at the moment, fresh filling fuel and oxidant are separated from high-temperature burnt products under the action of the low-temperature region, the fresh mixture is prevented from being ignited by high-temperature fuel gas, along with the filling, the low-temperature region moves towards an outlet of a knocking pipe, and the oxygen and the vaporized dimethyl ether are fully mixed in the moving process; when the ignition signal is triggered, a detonation wave starts to develop and form, and the mixture of oxygen and dimethyl ether is ignited, and all the filled fuel and oxidant participate in combustion; the oxygen amount in the whole process needs to be controlled to consume the kerosene and the dimethyl ether, namely, after the combustion of one cycle is finished, no oxygen exists in the combustion chamber, so that the injected dimethyl ether cannot be combusted before the initiation of the detonation wave in the next cycle.
2. A control method of a dual fuel isolation-free pulse detonation engine arrangement as claimed in claim 1, characterised by: the multi-cycle detonation wave is obtained by adopting a dual-fuel design of kerosene and dimethyl ether and alternately injecting.
3. A control method of a dual fuel isolation-free pulse detonation engine arrangement as claimed in claim 1, characterised by: the dimethyl ether is utilized to instantaneously vaporize and absorb heat after entering the combustion chamber to form a low-temperature area, so that fresh filling fuel and oxidant are separated from high-temperature combustion products, and an inert gas isolation effect is achieved; but different from inert gas, the method adopts injection of various fuels to form multi-cycle knocking, dimethyl ether can be combusted to contribute energy to a system, the adverse effect of an inert isolating agent on the propulsion efficiency of the engine is eliminated, and no isolation on the whole effect is realized.
4. A control method of a dual fuel isolation-free pulse detonation engine arrangement as claimed in claim 1, characterised by: the supply time sequence of kerosene, dimethyl ether and oxygen is controlled, so that the dimethyl ether can enter the combustion chamber in advance than the kerosene, and the injection quantity of the dimethyl ether can just form an effective low-temperature zone.
5. A control method of a dual fuel isolation-free pulse detonation engine arrangement as claimed in claim 1, characterised by: the equivalent ratio of the fuel to the oxidant is controlled, so that the introduced oxygen can burn the kerosene and the dimethyl ether, and the condition that no residual oxygen exists in the combustion chamber after one detonation cycle is finished is ensured, and the dimethyl ether cannot be ignited in advance.
6. A control method of a dual fuel isolation-free pulse detonation engine arrangement as claimed in claim 1, characterised by: the oxygen amount which is simultaneously introduced with the dimethyl ether is controlled to be outside the explosive limit of the dimethyl ether, so that the dimethyl ether is ensured not to burn in advance and can be well mixed with the oxygen, and the dimethyl ether is ensured to burn fully after the detonation wave is started.
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