CN114962066B - Counter-flow rotary gas wave ignition knocking combustion device - Google Patents
Counter-flow rotary gas wave ignition knocking combustion device Download PDFInfo
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- CN114962066B CN114962066B CN202210546874.1A CN202210546874A CN114962066B CN 114962066 B CN114962066 B CN 114962066B CN 202210546874 A CN202210546874 A CN 202210546874A CN 114962066 B CN114962066 B CN 114962066B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 72
- 238000005474 detonation Methods 0.000 claims abstract description 194
- 239000007921 spray Substances 0.000 claims abstract description 13
- 230000035939 shock Effects 0.000 claims description 42
- 239000000446 fuel Substances 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 7
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 238000011161 development Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 18
- 230000008901 benefit Effects 0.000 description 8
- 230000008569 process Effects 0.000 description 6
- 238000004891 communication Methods 0.000 description 5
- 238000000889 atomisation Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 238000011144 upstream manufacturing 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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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)
Abstract
The invention discloses a countercurrent rotary air wave ignition detonation combustion device, and belongs to the technical field of detonation engines. The device comprises an air inlet spray pipe, a detonation combustion chamber, a rotary jet flow disc and a motor which are coaxially arranged, wherein the motor is arranged in the detonation combustion chamber, a rotating shaft of the rotary jet flow disc is connected with the motor, and a plurality of jet flow cavities, an exhaust channel and an overflow cavity are sequentially arranged on the periphery of the rotary jet flow disc in the circumferential direction; the detonation combustion chamber comprises a plurality of detonation tubes which are circumferentially and coaxially arranged, one end of each detonation tube is sealed by adopting a concave cavity structure, and the other end of each detonation tube is arranged in an opening way; the detonation tube and the exhaust channel on the rotary jet disc are communicated with each other to form a communicated detonation channel. The invention has the characteristics of active control of stable working frequency of pulse detonation combustion, adjustable power of the combustion device, reduced structural quality of the combustion chamber and convenience for transplanting to the combustion chamber of the traditional aeroengine, and meets the urgent need of the development of the pulse detonation engine.
Description
Technical Field
The invention belongs to the technical field of detonation engines, and particularly relates to a countercurrent rotary gas wave ignition detonation combustion device.
Background
Because detonation combustion has the advantage of self-pressurization, the comprehensive thermal efficiency of the engine can be obviously improved after the detonation combustion chamber is used for replacing the isobaric combustion chamber. Moreover, compared with isobaric combustion, the knocking combustion has the advantages that the problems of unstable combustion, easy flameout and the like are solved, the combustion speed of the knocking combustion is high, the residence time of combustion products in a high-temperature area is short, and the emission of pollutants such as NOx can be reduced. Based on the advantages of detonation combustion, a large number of research institutions and universities at home and abroad have developed a great deal of research on using pulse detonation combustors for aviation gas turbine engines so as to greatly improve the performance of the existing engines. As patent CN201911094367.3 discloses a pulse detonation engine that relies on an independently controlled pulse ignition unit to achieve pulse ignition, patent CN201410472741.X discloses a pulse detonation engine that first vaporizes liquid fuel and utilizes a detonation tube to detonate a main detonation tube for pulse detonation combustion purposes, and so on.
To push the advantages of detonation combustion to engineering, much work has been done on the ignition initiation and short-range rapid reach detonation combustion of pulse detonation engines. The former can be classified into continuous ignition initiation and pulse ignition initiation. The continuous ignition detonation mode has the advantages of convenient control, controllable ignition energy and the like, but the additional consumed ignition energy is high, and a set of independent fuel supply system is required to be improved, so that the engine structure is complex. The pulse ignition detonation mode can greatly reduce the consumption of ignition energy under the condition that the detonation frequency is matched with the working frequency of the detonation engine, but a very high ignition energy peak value is required to be instantaneously generated for achieving the purpose of stable detonation, which has certain difficulty in engineering. The pneumatic ignition mode is a novel ignition mode, such as shock wave focusing ignition, supersonic jet impact ignition and the like, and can achieve very high ignition energy at the local part of a flow field, so that the engineering difficulty is expected to be solved.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a countercurrent rotary gas wave ignition detonation combustion device, which adopts a rotary jet device to periodically connect and close detonation oscillation wave with a closed cavity at one end and an opening at one end, generates pulse shock waves in a detonation oscillation tube and moves towards the direction of the closed cavity, when the pulse shock waves reach the closed cavity, a shock wave focusing phenomenon can be generated, and the shock wave focusing point reaches a very high transient temperature, thereby realizing the pulse ignition detonation of combustible gas in the detonation tube, the detonation wave after detonation propagates to the opening end of the detonation tube, and then is ejected from the tail end of the detonation combustion chamber, so that a detonation combustion cycle is completed, the complex detonation device structure of a conventional pulse detonation engine can be effectively avoided, and simultaneously, the ignition detonation frequency is continuously adjustable, thereby facilitating the control of the output power of the engine.
In order to achieve the above purpose, the invention provides a countercurrent rotary gas wave ignition detonation combustion device, which comprises a gas inlet spray pipe, a detonation combustion chamber which rotates in an annular manner, a rotary jet flow disc and a motor, wherein the gas inlet spray pipe, the detonation combustion chamber which rotates in an annular manner, the motor is arranged in the detonation combustion chamber, a rotary shaft of the rotary jet flow disc is connected with the motor, and the rotary jet flow disc rotates under the drive of the motor; a plurality of jet cavities, exhaust channels and overflow cavities are sequentially arranged on the periphery of the rotary jet disc in the circumferential direction; one or more air inlet holes are formed in the side, facing the air inlet inflow of the air inlet spray pipe, of the rotary jet flow disc surface, and the air inlet holes are communicated with the jet flow cavity through an inner channel of the rotary jet flow disc;
The detonation combustion chamber comprises a plurality of detonation tubes which are circumferentially and coaxially arranged, one end of each detonation tube is sealed by adopting a concave cavity structure, and the other end of each detonation tube is arranged in an opening way; the detonation tube and the exhaust channel on the rotary jet flow disk are communicated with each other to form a communicated detonation channel; the detonation tube and detonation booster shock tube remain stationary.
Further, the jet cavity outlet is arranged opposite to the opening end of the detonation tube, and the jet moves towards the closed end of the concave cavity of the detonation tube.
Further, the circumferential length d of the jet cavity satisfies the following relationship:
Wherein n is the rotating speed of the rotary jet disc, and the unit is rpm; r is the median radius of the jet cavity height; u s is the propagation velocity of the pulse shock wave within the detonation tube.
Furthermore, the concave cavity of the detonation tube can have various forms, such as a pointed cone concave cavity, an elliptic concave cavity and the like, and the cross-section form of shock wave focusing can be met.
Further, the rotary jet disc also comprises a detonation force oscillating tube, and the detonation force oscillating tube is an optional component. The detonation tube and the exhaust channel on the rotary jet flow disk are communicated with each other to form a communicated detonation channel
Further, the height of the jet cavity and the height of the exhaust channel are the same as the height of the detonation tube and the detonation-boosting shock tube.
Further, the detonation stress application oscillating pipes and the detonation pipes are arranged in the same mode, and the number of the detonation stress application oscillating pipes is the same.
Further, the detonation tube and the detonation energizing shock tube are both provided with continuous fuel nozzles, and the injection directions of the detonation tube and the detonation energizing shock tube face to the closed end of the concave cavity of the detonation tube.
Further, the height of the flow passing cavity on the rotary jet disc is larger than the height of the channel of the detonation tube, so that the air of the incoming flow is conveniently ejected to enter the detonation tube, and conditions are created for detonation combustion in the next period.
Further, the length of the detonation tube is equivalent to the atomization distance when fuel injection atomization is arranged on the detonation tube, so that good combustible mixed gas of atomized liquid fuel droplets and air is formed at the sealing concave cavity of the detonation tube, and the detonation ignition is ensured to be successful.
Compared with the prior art, the countercurrent rotary gas wave ignition detonation combustion device provided by the invention has the advantages that pulse shock waves are generated by periodically connecting or closing the jet cavity and the opening end of the detonation tube, the shock wave focusing attenuation problem and the high-frequency unstable shock wave focusing ignition problem caused by continuous supersonic velocity core-focusing jet collision are overcome by utilizing the concave cavity shock wave reflection focusing ignition principle, and the countercurrent rotary gas wave ignition detonation combustion device has the following advantages:
firstly, changing the rotation speed of a rotary jet disc to actively control the shock wave focusing frequency, namely the working frequency of a detonation combustion device, and breaking through the technical limit of improving the working frequency of a pulse detonation engine by using a traditional igniter;
secondly, by utilizing the supercharging characteristic of the motion shock wave, the pressure energy of incoming air is reasonably recovered, the atomization evaporation and blending characteristics of fuel oil are improved, combustible mixed gas is easy to form, and the ignition energy of detonation can be effectively reduced;
Thirdly, the concave cavity shock wave focusing ignition principle is adopted, so that the inherent defects of the traditional spark plug or continuous ignition mode are avoided, and the complexity of the structure of the knocking combustion device is greatly reduced;
fourth, adopt the inlet mode of axial flow inlet channel, keep unanimous with traditional engine inlet mode, can conveniently transplant to traditional aeroengine combustion chamber.
In summary, the pulse detonation combustion control system has the characteristics of active control of stable working frequency of pulse detonation combustion, adjustable power of the combustion device, reduced structural quality of the combustion chamber and convenience in transplanting to the combustion chamber of the traditional aeroengine, and meets urgent needs of development of the pulse detonation engine.
Drawings
FIG. 1 is a schematic diagram of a countercurrent rotary gas wave ignition detonation combustion device provided by the invention;
FIG. 2 is a schematic diagram of a rotating jet disk configuration;
FIG. 3 is a structural effect diagram of a detonation tube;
FIG. 4 is a structural effect diagram of a detonation boost shock tube;
Reference numerals:
The device comprises a 1-air inlet spray pipe, a 2-first fixed ring, a 3-detonation fuel atomizing nozzle, a 4-detonation combustion device barrel shell, a 5-engine positioning disk, a 6-boosting fuel atomizing nozzle, a 7-motor, an 8-rotating shaft, a 9-jet cavity, a 10-third fixed ring, a 11-detonation boosting oscillating pipe, a 12-rotating jet disk, a 13-second fixed ring, a 14-detonation tube, a 15-shock wave focusing concave cavity, a 16-overflow cavity, a 17-shaft hole, an 18-exhaust channel, a 19-communication hole and a 20-air inlet hole.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not interfere with each other.
The focusing reflection of shock waves on the wall surface of the concave cavity can generate a local high-temperature and high-pressure area, and can induce ignition and even detonation of combustible premixed gas under proper conditions. This process is a typical unsteady process, and the basic premise of successful ignition stabilization is that a shock wave focusing process can be generated in each cycle of detonation combustion. This determines that a pulse shock must be periodically generated within the detonation tube. The core technology of the invention is that a rotary jet disc is adopted to periodically connect and close the jet cavity with the opening end of the detonation tube through rotary motion, pulse shock wave is generated at the moment of connecting the detonation tube, the stable and reliable occurrence of unsteady shock wave of shock wave focusing phenomenon of the cavity at the closed end of the detonation tube is ensured, and finally, the controllable and stable ignition of shock wave focusing ignition is realized.
With reference to fig. 1 and 2, the countercurrent rotary gas wave ignition detonation combustion device provided by the invention comprises an air inlet spray pipe 1, a detonation tube 14, a rotary jet disc 12, a detonation stress-vibration tube 11 and a motor 7, which are coaxially arranged in sequence.
The air inlet spray pipe 1 and the barrel shell 4 of the knocking combustion device form the whole shell of the knocking combustion device, and a detonation tube 14 and a detonation stress vibration tube 11 are coaxially arranged in the shell, and are statically arranged in the whole shell of the knocking combustion device by means of a first fixed ring 2, a second fixed ring 13 and a third fixed ring 10 respectively; the schematic structure of the detonation/detonation tube 14 is shown in fig. 3, one end of the detonation/detonation tube 14 is sealed by adopting a concave cavity structure, the other end of the detonation/detonation tube is arranged in an opening way, and the detonation/detonation tube 14 is periodically arranged around a shaft to form an annular detonation/detonation chamber; the schematic structure of the knocking afterburner 11 is shown in fig. 4, two ends of the oscillating tube are both arranged in an opening way, and the annular knocking afterburner is formed by periodic axial arrangement; the detonation tube 14 and the detonation stress vibration tube 11 have the same section height, and can form a smooth communicated detonation tube through the exhaust channel 18; the rotary jet disc 12 is arranged between the static detonation tube 14 and the detonation boosting vibration tube 11, and is provided with a jet cavity 9, an exhaust channel 18 and an overflow cavity 16, and a plurality of jet cavities can be periodically arranged; the jet cavity 9 is a semi-closed cavity which is opened towards the detonation tube 14, and the section height of the semi-closed cavity is equal to the section height of the detonation tube 14; the exhaust passage 18 is a through hole structure, and the height of the through hole is equal to the height of the section of the detonation tube 14; the flow-through cavity 16 is of a step-shaped structure, and the step height is larger than the section height of the detonation tube 14, so that a flow-through area is formed; the rotary jet disc 12 is provided with an air inlet hole 20 towards the air inlet side of the combustion device, the air inlet hole 20 is connected with a communication hole 19 through a communication channel in the rotary jet disc 12, and the communication hole 19 is connected with the jet cavity 9; the rotary jet disc 12 is driven to rotate by the motor 7 through the rotary shaft 8 and the motor 7; the rotary shaft 8 is fixedly mounted by the engine positioning plate 5.
When the countercurrent rotary air wave ignition detonation combustion device provided by the invention starts to work, the motor 7 rotationally drives the rotary jet disc 12 to coaxially rotate. The air inlet spray pipe 1 sucks high-pressure air formed by stamping in the flight process of the aircraft, and the high-pressure air flows through the communication hole 19 and enters the jet cavity 9 through the air inlet hole 20 after being decelerated and diffused. Under the rotation of the rotary jet disc 12, when the jet cavity 9 rotates to be connected with the opening end of the detonation tube 14, pressurized high-pressure air is reversely jetted into the detonation tube 14, and pulse shock waves are formed to propagate to the closed end of the concave cavity of the detonation tube 14. When the running pulse shock wave propagates to the closed end of the cavity of the detonation tube 14, a shock wave focusing point is generated under the reflection focusing of the cavity wall surface, and a high-temperature and high-pressure area is instantaneously generated. The detonation fuel atomizing nozzle 3 reversely sprays atomized liquid fuel in the detonation tube, after a certain atomization distance, the atomized liquid fuel is mixed with the sucked air at the closed end of the concave cavity of the detonation tube 14 to form combustible mixed gas, and the combustible mixed gas is ignited and detonated under the action of a high-temperature high-pressure area generated by the shock wave focusing. After successful ignition initiation, the detonation wave will propagate downstream of the detonation tube 14 as reflected by the closed end of the cavity. When the detonation wave propagates downstream to the open end of the detonation tube 14, the exhaust channel 18 communicates with the open end of the detonation tube 14 upon rotation of the rotating jet disk 12, allowing the detonation wave to continue to propagate downstream to the detonation booster shock tube 11. If the output power of the detonation combustion device needs to be increased, the afterburner fuel atomizing nozzle 6 sprays additional fuel in the detonation afterburner oscillation tube 11 in a countercurrent mode, and the afterburner fuel atomizing nozzle ignites and detonates under the action of detonation waves transmitted from the upstream to improve the output power of the combustion device. After the high-temperature high-pressure fuel gas in the detonation tube 14 is emptied, the overflow cavity 16 is communicated with the opening end of the detonation tube 14 under the rotation of the rotary jet disc 12, the detonation tube 14 is communicated with the air cavity behind the air inlet spray tube 1 through the opening structure of the overflow cavity 16, fresh air is sucked under the action of expansion waves in the detonation tube 14, and an oxidant is provided for detonation combustion in the next period. The above process is repeated, so that each detonation tube 14 of the detonation combustion device ignites and detonates and produces detonation waves which are discharged through the detonation booster oscillating tube 11, thereby producing positive thrust.
According to the working process, the counter-flow rotary gas wave ignition detonation combustion device provided by the invention utilizes the periodical connection and closure of the opening end of the detonation tube and the jet cavity to stably generate pulse shock waves, the frequency and intensity of the pulse shock waves can be flexibly regulated by the rotating speed of the rotary jet disc, the structure is simple, and the reliability of direct ignition detonation of the detonation combustion chamber is greatly improved. The invention adopts the axial airflow inlet, is consistent with the suction direction of the traditional engine, and can be well transplanted into the existing engine combustion chamber design.
It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (10)
1. The counter-flow type rotary air wave ignition detonation combustion device comprises an air inlet spray pipe (1), a detonation combustion chamber, a rotary jet flow disc (12) and a motor (7) which are coaxially arranged, wherein the motor (7) is arranged in the detonation combustion chamber, a rotating shaft of the rotary jet flow disc (12) is connected with the motor (7), and the rotary jet flow disc (12) rotates under the drive of the motor (7); it is characterized in that the method comprises the steps of,
A plurality of jet cavities (9), exhaust channels (18) and overflow cavities (16) are sequentially arranged on the periphery of the rotary jet disc (12) in the circumferential direction; one or more air inlet holes (20) are formed in the side, facing the air inlet incoming flow, of the air inlet spray pipe (1) of the rotary jet flow disc (12), and the air inlet holes (20) are communicated with the jet flow cavity (9) through an inner channel of the rotary jet flow disc (12);
The detonation combustion chamber comprises a plurality of detonation tubes (14) which are circumferentially and coaxially arranged, one end of each detonation tube (14) is sealed by adopting a concave cavity structure, and the other end of each detonation tube is arranged in an opening manner; the detonation tube (14) and the exhaust channel (18) on the rotary jet disc (12) are communicated with each other to form a communicated detonation channel.
2. Counter-flow rotary gas wave ignition detonation combustion device according to claim 1, characterized in that the outlet of the jet cavity (9) is arranged opposite to the open end of the detonation tube (14), the jet output by the jet cavity (9) moving towards the closed end of the detonation tube (14).
3. Counter-flow rotary gas wave ignition detonation combustion device according to claim 1, characterized in that the circumferential length d of the jet cavity (9) satisfies the following relationship:
Wherein n is the rotating speed of the rotary jet disc, and the unit is rpm; r is the median radius of the jet cavity height; u s is the propagation velocity of the pulse shock wave within the detonation tube.
4. A counter-flow rotary gas wave ignition detonation combustion device as claimed in claim 1 wherein the cavity structure of the detonation tube (14) is a pointed cone cavity or an elliptical cavity.
5. A counter-flow rotary gas wave ignition detonation combustion device according to claim 1, further comprising a detonation boost shock tube (11), wherein the rotary jet disc (12) is arranged between the detonation shock tube (14) and the detonation boost shock tube (11), and the detonation shock tube (14) and the exhaust channel on the rotary jet disc (12) and the detonation boost shock tube (11) are communicated with each other to form a communicated detonation channel.
6. Counter-flow rotary gas wave ignition detonation combustion device according to claim 5, characterized in that the height of the jet cavity (9) and the height of the exhaust channel (18) are the same as the height of the detonation tube (14) and the detonation tube (11).
7. Counter-flow rotary gas wave ignition detonation combustion device according to claim 5, characterized in that the detonation boost shock tube (11) is arranged in the same way as the detonation shock tube (14), the same number.
8. A counter-flow rotary gas wave ignition detonation combustion device as claimed in claim 5 wherein the detonation tube (14) and detonation boost shock tube (11) are each provided with a continuous fuel jet, the injection direction being towards the closed end of the detonation tube (14) cavity.
9. The counter-flow rotary gas wave ignition detonation combustion device of claim 5 wherein the flow chamber height above the rotary jet disk (12) is greater than the detonation tube (14) channel height.
10. A counter-flow rotary gas wave ignition detonation combustion device as claimed in claim 8 wherein the detonation tube (14) is of a length commensurate with the atomizing distance upon which fuel injection is atomized.
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| CN202210546874.1A CN114962066B (en) | 2022-05-18 | 2022-05-18 | Counter-flow rotary gas wave ignition knocking combustion device |
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| CN202210546874.1A CN114962066B (en) | 2022-05-18 | 2022-05-18 | Counter-flow rotary gas wave ignition knocking combustion device |
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| CN114962066A CN114962066A (en) | 2022-08-30 |
| CN114962066B true CN114962066B (en) | 2024-07-02 |
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| CN116147018B (en) * | 2022-11-23 | 2024-08-16 | 中国航天空气动力技术研究院 | Supersonic combustion chamber for accelerating fuel atomization by using multi-degree-of-freedom variable shock waves |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606548A (en) * | 2012-03-23 | 2012-07-25 | 大连理工大学 | Radial-flow type fluidic pressure wave supercharger |
| CN102606547A (en) * | 2012-03-23 | 2012-07-25 | 大连理工大学 | Axial-flow type jet flow gas wave pressure supercharger |
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| US6845620B2 (en) * | 2001-07-06 | 2005-01-25 | Mohamed Razi Nalim | Rotary ejector enhanced pulsed detonation system and method |
| US10240794B2 (en) * | 2016-02-11 | 2019-03-26 | Rolls-Royce Corporation | Thermal and thrust management in dynamic pressure exchangers |
| CN106016362B (en) * | 2016-05-16 | 2018-10-09 | 中国科学院工程热物理研究所 | A kind of soft combustion chamber of gas turbine and its control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606548A (en) * | 2012-03-23 | 2012-07-25 | 大连理工大学 | Radial-flow type fluidic pressure wave supercharger |
| CN102606547A (en) * | 2012-03-23 | 2012-07-25 | 大连理工大学 | Axial-flow type jet flow gas wave pressure supercharger |
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