CN203962199U - A kind of high-frequency pulse pinking combustion-powered apparatus - Google Patents
A kind of high-frequency pulse pinking combustion-powered apparatus Download PDFInfo
- Publication number
- CN203962199U CN203962199U CN201420293451.4U CN201420293451U CN203962199U CN 203962199 U CN203962199 U CN 203962199U CN 201420293451 U CN201420293451 U CN 201420293451U CN 203962199 U CN203962199 U CN 203962199U
- Authority
- CN
- China
- Prior art keywords
- detonation
- section
- combustion chamber
- nozzle
- thrust
- 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.)
- Expired - Fee Related
Links
- 238000005474 detonation Methods 0.000 claims abstract description 116
- 238000002485 combustion reaction Methods 0.000 claims abstract description 103
- 239000000446 fuel Substances 0.000 claims abstract description 25
- 230000003416 augmentation Effects 0.000 claims description 30
- 239000007921 spray Substances 0.000 claims description 8
- 230000008602 contraction Effects 0.000 claims description 4
- 238000010304 firing Methods 0.000 abstract 8
- 239000007789 gas Substances 0.000 description 10
- 238000006243 chemical reaction Methods 0.000 description 6
- 230000004888 barrier function Effects 0.000 description 5
- 230000006872 improvement Effects 0.000 description 5
- 238000004200 deflagration Methods 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 4
- 238000005728 strengthening Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
Landscapes
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
A high-frequency pulse pinking combustion-powered apparatus, comprises from left to right connected successively pulse detonation combustor, jet pipe and plural serial stage pushing structure; Wherein, pulse detonation combustor comprises from left to right connected successively head of combustion chamber end cap, firing chamber igniting section, the firing chamber section of detonating and firing chamber pinking section, and the right-hand member of firing chamber pinking section is connected with jet pipe; Head of combustion chamber end cap is provided with main nozzle, and main nozzle is provided with main nozzle air pipe line and main nozzle fuel conduit; Firing chamber igniting section week be upwards provided with spark plug; The firing chamber section of detonating and firing chamber pinking section circumferentially in axial direction equal intervals be provided with some pilot jets, pilot jet is provided with pilot jet air pipe line and pilot jet fuel conduit.The utility model can reduce the filling time of firing chamber, improves the frequency of okperation of motor, increases the thrust that the motor unit time produces; In addition, at jet pipe, design plural serial stage pushing structure, further improved the thrust of motor.
Description
[ technical field ] A method for producing a semiconductor device
The utility model relates to the technical field of engines, especially, relate to a high frequency pulse detonation combustion power device.
[ background of the invention ]
Detonation combustion is another form of combustion, which, unlike the slow-burn combustion process, is very rapid and produces a supersonic combustion wave, i.e., a detonation wave. The detonation wave is propagated by the high-speed chemical reaction of the knock mixture under the action of the layer-by-layer strong impact compression of the shock wave, so that the detonation wave can be considered as a strong shock wave coupling the chemical reaction. The detonation combustion has a much greater propagation velocity than the retarded combustion, typically at 103In the order of m/s. And slow burningCompared with combustion, detonation combustion has the advantages of self-pressurization, high flame propagation speed, high combustion efficiency, low pollutant discharge and the like, detonation combustion replaces isobaric combustion in a traditional power device, and the utilization efficiency of the existing energy can be improved by developing a novel power device based on detonation circulation.
The pulse detonation engine is a new concept propulsion device which generates high-temperature and high-pressure fuel gas by using intermittent detonation combustion to generate thrust. Pulse detonation engines are classified into aspirated pulse detonation engines and rocket pulse detonation engines according to whether the pulse detonation engines are self-contained with oxidants or not. The detonation combustion is divided into a direct detonation mode and an indirect detonation mode, the former needs huge ignition energy, the latter gradually forms detonation waves through the conversion from detonation to detonation, namely, a smaller ignition energy is firstly adopted to form detonation waves, then the detonation waves are finally formed through the interaction of flame and compression waves in a detonation chamber, the distance of the conversion from detonation to detonation is called DDT, and the length of DDT is mainly determined by parameters such as the size of a combustion chamber, fuel characteristics and the like. In view of practicality, pulse detonation engines generally adopt an indirect detonation mode to obtain a detonation wave, so that the length of a combustion chamber is necessarily larger than DDT, and in order to ensure that fuel in the combustion chamber mostly releases heat in detonation combustion, the length of the combustion chamber is generally designed to be 4 to 5 times of the distance of the DDT. The air intake mode of the traditional air-breathing type and rocket type pulse detonation engine adopts the mode of air intake from the head part of the pulse detonation combustion chamber, which influences the filling time of the combustion chamber to a certain extent, so that the working frequency of the engine is reduced along with the increase of the length of the combustion chamber. Meanwhile, because the working frequency of the pulse detonation engine is not high, compared with the traditional isobaric combustion chamber which is always in a filling and combustion state, the traditional pulse detonation engine combustion chamber is filled with less fuel in unit time, so that the thrust generated in unit time of the pulse detonation engine is lower, and the application pace of the pulse detonation engine is prevented.
Review analysis can see that while detonation combustion has advantages over traditional isobaric combustion, pulse detonation engines still suffer from the following major problems: 1) the pulse detonation engine has low working frequency and is easily limited by the length of a combustion chamber; 2) the thrust generated by the pulse detonation engine per unit time is small.
[ Utility model ] content
The utility model aims to solve the low, thrust little scheduling problem that the frequency received combustion chamber length restriction, the engine unit interval to produce of traditional pulse detonation engine operating frequency, provide a high frequency pulse detonation combustion power device, its filling time that can shorten the pulse detonation combustion chamber increases the thrust that produces in the engine unit interval, can solve the problem that engine operating frequency is limited to combustion chamber length simultaneously.
In order to achieve the above object, the utility model adopts the following technical scheme:
a high-frequency pulse detonation combustion power device comprises a pulse detonation combustion chamber, a tail nozzle and a multi-stage series-connection boosting structure which are sequentially connected from left to right; wherein,
the pulse detonation combustor comprises a combustor head end cover, a combustor ignition section, a combustor detonation section and a combustor detonation section which are sequentially connected from left to right, and the right end of the combustor detonation section is connected with a tail nozzle; a main nozzle is arranged on the head end cover of the combustion chamber, and a main nozzle air pipeline and a main nozzle fuel pipeline are arranged on the main nozzle; spark plugs are arranged on the circumferential direction of the ignition section of the combustion chamber; and a plurality of auxiliary nozzles are arranged at equal intervals along the axial direction in the circumferential direction of the combustion chamber detonation section and the combustion chamber detonation section, and an auxiliary nozzle air pipeline and an auxiliary nozzle fuel pipeline are arranged on each auxiliary nozzle.
The utility model discloses the further improvement lies in: the tail nozzle is a convergent nozzle, the contraction ratio is 1.2 to 1.5, and the convergence angle is 6 to 10 degrees.
The utility model discloses the further improvement lies in: the multistage series-connection boosting structure comprises a first-stage boosting device, a second-stage boosting device and a third-stage boosting device which are sequentially connected from left to right.
The utility model discloses the further improvement lies in: the first-stage thrust augmentation device comprises a first arc-shaped air inlet end face and a first axisymmetric straight spray pipe, the second-stage thrust augmentation device comprises a second arc-shaped air inlet end face and a second axisymmetric straight spray pipe, and the third-stage thrust augmentation device comprises a third arc-shaped air inlet end face and a third axisymmetric straight spray pipe; the multistage series-connection thrust augmentation structure connecting rods are uniformly arranged in the circumferential direction of the first arc-shaped air inlet end face, one end of each multistage series-connection thrust augmentation structure supporting plate is connected with the corresponding multistage series-connection thrust augmentation structure connecting rod, and the other end of each multistage series-connection thrust augmentation structure supporting plate is connected with the tail of the pulse detonation combustion chamber; the first-stage thrust increaser connecting rods are uniformly arranged in the circumferential direction of the second arc-shaped air inlet end face, one end of each first-stage thrust increaser supporting plate is connected with the corresponding first-stage thrust increaser connecting rod, and the other end of each first-stage thrust increaser supporting plate is connected with the first axisymmetric straight spray pipe; and the plurality of second-stage thrust increaser connecting rods are uniformly arranged in the circumferential direction of the third arc-shaped air inlet end surface, one end of each of the plurality of second-stage thrust increaser supporting plates is connected with the corresponding second-stage thrust increaser connecting rod, and the other end of each of the plurality of second-stage thrust increaser supporting plates is connected with the second-axis symmetric straight spray pipe.
The utility model discloses the further improvement lies in: the number of the support plates of the multistage series-connection thrust augmentation structure and the number of the connecting rods of the multistage series-connection thrust augmentation structure are both 4, the number of the connecting rods of the thrust augmentor between the first-stage support plates and between the first-stage support plates is 4, and the number of the connecting rods of the thrust augmentor between the second-stage support plates and between the second-stage support plates are 4.
The utility model discloses the further improvement lies in: the inner wall of the combustion chamber detonation section is provided with a first spiral obstacle, the inner wall of the combustion chamber detonation section is provided with a second spiral obstacle, and the pitch of the first spiral obstacle is smaller than that of the second spiral obstacle.
Compared with the prior art, the utility model relates to a high frequency pulse detonation combustion power device, it has the fuel nozzle except that the design has at the combustion chamber head, still has designed a plurality of auxiliary fuel nozzles at combustion chamber priming section and detonation section equidistant, divides the combustion chamber into a plurality of small intervals, and every nozzle is responsible for the fuel supply of an interval, can reduce the filling time of combustion chamber, improves the operating frequency of engine, increases the thrust that the engine unit time produced; in addition, a multistage series boosting structure is designed at the tail of the pulse detonation combustion chamber, so that the thrust of the engine can be further improved.
Furthermore, because the spiral obstacle detonation wave strengthening structure in the combustion chamber adopts a variable pitch design, the DDT distance of the conversion from the detonation of the combustion chamber to the detonation can be shortened on the premise of reducing the flow resistance of the combustion chamber of the engine.
[ description of the drawings ]
FIG. 1 is an overall configuration diagram of a high-frequency pulse detonation combustion power plant according to the present invention;
FIG. 2 is a schematic diagram illustrating a multi-stage series boost configuration of the power plant shown in FIG. 1;
fig. 3 is a view from a-a of fig. 2.
Wherein: 1. a main nozzle air line; 2. a main nozzle fuel line; 3. a main nozzle; 4. a combustion chamber head end cap; 5. a pulse detonation combustor; 6. a spark plug; 7. a combustion chamber ignition section; 8. an auxiliary nozzle fuel line; 9. an auxiliary nozzle air line; 10. a combustion chamber initiation section; 11. a first helical barrier; 12. an auxiliary nozzle; 13. a second helical barrier; 14. a combustion chamber detonation section; 15. a support plate with a multistage series-connection boosting structure; 16. the multistage serial thrust augmentation structure connecting rods; 17. a tail nozzle; 18. a multi-stage series boosting structure; 19. a gas flow path; 20. a first arcuate inlet end face; 21. a first axisymmetric straight nozzle; 22. a first-stage thrust increasing device; 23. a first-stage intermediate thruster extension plate; 24. a first-stage booster connecting rod; 25. a second arcuate inlet end face; 26. a second axisymmetric straight nozzle; 27. a secondary thrust booster; 28. a second-stage booster support plate; 29. a second-stage booster connecting rod; 30. a third arcuate inlet end face; 31. a third axis symmetric straight nozzle; 32. and a third-stage thrust augmentation device.
[ detailed description ] embodiments
The following describes in detail embodiments of the present invention with reference to the accompanying drawings.
Referring to fig. 1 to 3, the utility model relates to a high frequency pulse detonation combustion power device, including pulse detonation combustion chamber 5, tail nozzle 17 and multistage series connection increase and push structure 18 that link to each other in proper order from a left side to the right side.
The pulse detonation combustor 5 comprises a combustor head end cover 4, a combustor ignition section 7, a combustor initiation section 10 and a combustor detonation section 14 which are sequentially connected from left to right, and the right end of the combustor detonation section 14 is connected with a tail nozzle 17; a main nozzle 3 is arranged on the head end cover 4 of the combustion chamber, and a main nozzle air pipeline 1 and a main nozzle fuel pipeline 2 are arranged on the main nozzle 3; a spark plug 6 is arranged on the circumferential direction of the combustion chamber ignition section 7; a plurality of auxiliary nozzles 12 are arranged on the circumferential direction of the combustion chamber detonation section 10 and the combustion chamber detonation section 14 at equal intervals along the axial direction, and auxiliary nozzle air pipelines 9 and auxiliary nozzle fuel pipelines 8 are arranged on the auxiliary nozzles 12. Therefore, the main nozzle 3 and the auxiliary nozzle 12 can simultaneously fill the combustion chamber, so that each nozzle only needs to be responsible for supplying fuel to a small space of the combustion chamber, the filling time of the combustion chamber can be reduced, and the working frequency of the engine is improved.
Further, the jet nozzle 17 is a convergent nozzle, the contraction ratio is 1.2 to 1.5, and the convergence angle is 6 to 10 degrees. The inner wall of the combustion chamber detonation section 10 is provided with a first spiral obstacle 11, the inner wall of the combustion chamber detonation section 14 is provided with a second spiral obstacle 13, and the pitch of the first spiral obstacle 11 is smaller than that of the second spiral obstacle 13. The smaller the pitch of the barrier strengthening structure is, the larger the turbulence of combustible mixed gas in the combustion chamber is, and the stronger the heat exchange intensity between airflows is, so that the conversion distance DDT from deflagration to detonation can be shortened, but the smaller the pitch is, the larger the internal flow resistance of the engine is, and the smaller the pitch is, the DDT distance can be shortened while the flow resistance of the engine is reduced.
Referring to fig. 2 and 3, the multistage series thrust augmentation structure 18 includes a first-stage thrust increaser 22, a second-stage thrust increaser 27 and a third-stage thrust increaser 32 which are connected in sequence from left to right. The first-stage thrust booster 22 comprises a first arc-shaped air inlet end surface 20 and a first axisymmetric straight nozzle 21, the second-stage thrust booster 27 comprises a second arc-shaped air inlet end surface 25 and a second axisymmetric straight nozzle 26, and the third-stage thrust booster 32 comprises a third arc-shaped air inlet end surface 30 and a third axisymmetric straight nozzle 31; the 4 multistage series-connection thrust augmentation structure connecting rods 16 are uniformly arranged in the circumferential direction of the first arc-shaped air inlet end face 20, one ends of the 4 multistage series-connection thrust augmentation structure supporting plates 15 are connected with the corresponding multistage series-connection thrust augmentation structure connecting rods 16, and the other ends of the 4 multistage series-connection thrust augmentation structure supporting plates are connected with the tail portion of the pulse detonation combustion chamber 5; the 4 first-stage thrust augmentation connecting rods 24 are uniformly arranged in the circumferential direction of the second arc-shaped air inlet end face 25, one ends of the 4 first-stage thrust augmentation supporting plates 23 are connected with the corresponding first-stage thrust augmentation connecting rods 24, and the other ends of the 4 first-stage thrust augmentation supporting plates are connected with the first axisymmetric straight nozzle 21; the 4 second-stage thrust increaser connecting rods 29 are uniformly arranged in the circumferential direction of the third arc-shaped air inlet end surface 30, one end of each of the 4 second-stage thrust increaser supporting plates 28 is connected with the corresponding second-stage thrust increaser connecting rod 29, and the other end of each of the 4 second-stage thrust increaser connecting rods is connected with the second axisymmetric straight spray pipe 26.
When the high-speed pulse detonation gas is discharged from the tail nozzle 17 and enters the primary booster 22, due to the action of airflow viscous force, the air at the upstream of the arc-shaped air inlet end face 20 is inevitably driven to be sucked into the engine, so that the dynamic pressure of the total air pressure at the upstream of the arc-shaped air inlet end face 20 is increased, the static pressure is reduced, the static pressure of the air at the downstream of the arc-shaped air inlet end face 20 is unchanged, and the additional thrust is inevitably generated at the arc-shaped air inlet end face 20 due to pressure. The direction of the arrow is a gas flow path 19.
For further understanding of the present invention, the present invention will now be described in conjunction with specific embodiments.
The utility model relates to a high frequency pulse detonation combustion power device, including pulse detonation combustion chamber 5, jet-tail pipe 17 and multistage series connection increase and push away structure 18. The pulse detonation combustor 5 mainly comprises a combustor head end cover 4, a combustor ignition section 7, a combustor initiation section 10 and a combustor detonation section 14, wherein the diameter of the combustor is 60mm, and the length of the combustor is 1300 mm; the combustor head end cover 4 is located at the foremost end of the present embodiment, and the main nozzle 3 is installed at the center position thereof; the combustion chamber ignition section 7 is positioned at the downstream of the combustion chamber head end cover 4, is 300mm long, and is provided with an ignition spark plug 6 at the middle of the axial position of the combustion chamber ignition section 7; the combustion chamber initiation section 10 is positioned at the downstream of the combustion chamber ignition section 7, is 400mm long, and is internally provided with a first spiral barrier 11 with the thread pitch of 50mm and the diameter of 8 mm; the combustion chamber detonation section 14 is positioned at the downstream of the combustion chamber detonation section 10, is 600mm long, and is internally provided with a second spiral barrier 13 with the screw pitch of 80mm and the diameter of 8 mm; meanwhile, seven auxiliary nozzles 12 are designed at equal intervals at the axial positions of the combustion chamber detonation section 10 and the combustion chamber detonation section 14, and the distance between the auxiliary nozzles 12 is 120 mm; the tail nozzle 17 is positioned at the downstream of the detonation section of the combustion chamber, the contraction ratio is 1.5, and the convergence angle is 6 degrees; the multistage series-connection boosting structure 18 and the combustion chamber are coaxially arranged at the downstream of the tail nozzle 17, and four multistage series-connection boosting structure support plates 15 and multistage series-connection boosting structure connecting rods 16 which are uniformly arranged in the circumferential direction of the tail of the combustion chamber detonation section 14 form a whole with the pulse detonation combustion chamber 5.
The embodiment can be used for an air-breathing pulse detonation engine and is also suitable for a rocket type pulse detonation engine. The working process of the high-frequency pulse detonation combustion power device comprises the following steps: opening air and fuel pipelines of a main nozzle 3 and auxiliary nozzles 12, quickly filling fuel into a pulse detonation combustor 5, after the fuel is filled, closing the air and fuel pipelines of the main nozzle 3 and the auxiliary nozzles 12, simultaneously igniting combustible mixed gas in the combustor by a spark plug 6, forming a deflagration wave in an ignition section 7 of the combustor, strengthening the deflagration wave by a small-pitch spiral obstacle 11 in an ignition section 10 of the combustor, gradually converting the deflagration wave into a detonation wave, further strengthening the detonation wave by a second spiral obstacle 13 in an ignition section 14 of the combustor, accelerating and discharging the detonation wave from a tail nozzle 17, driving air around the tail nozzle 17 to be sucked into the engine by high-speed jetted detonation gas under the action of airflow viscous force, forming static pressure difference at an arc-shaped air inlet end surface 20 of a primary booster 22, further generating additional thrust, and further driving air at the upstream of the arc-shaped air inlet end surfaces of a secondary booster 27 and a tertiary booster 32 to enter the engine by the high-speed gas after the primary booster 22 The engine generates additional thrust at the arc-shaped air inlet end face of each stage of boosting structure, finally gas is discharged to the atmosphere from an axisymmetric straight nozzle 31 of a three-stage booster 32, after the gas to be detonated is completely discharged out of the engine, a main nozzle air pipeline 1 and an auxiliary nozzle air pipeline 9 of a main nozzle 3 and each auxiliary nozzle 12 are opened, the detonation chamber is filled with blowing-out isolation gas, then a main nozzle fuel pipeline 2 and an auxiliary nozzle fuel pipeline 8 of the main nozzle 3 and each auxiliary nozzle 12 are opened, a new round of fuel filling of the pulse detonation combustion chamber is started, and the operation is repeatedly and circularly performed. Because the 8 fuel nozzles are adopted in the embodiment, the working frequency of the engine can be improved by at least seven times compared with the traditional pulse detonation engine only adopting 1 nozzle at the head part of the combustion chamber.
Claims (6)
1. A high-frequency pulse detonation combustion power device is characterized in that: the device comprises a pulse detonation combustion chamber (5), a tail nozzle (17) and a multi-stage series boosting structure (18) which are sequentially connected from left to right; wherein,
the pulse detonation combustor (5) comprises a combustor head end cover (4), a combustor ignition section (7), a combustor detonation section (10) and a combustor detonation section (14) which are sequentially connected from left to right, and the right end of the combustor detonation section (14) is connected with a tail nozzle (17); a main nozzle (3) is arranged on the head end cover (4) of the combustion chamber, and a main nozzle air pipeline (1) and a main nozzle fuel pipeline (2) are arranged on the main nozzle (3); spark plugs (6) are arranged on the circumferential direction of the ignition section (7) of the combustion chamber; a plurality of auxiliary nozzles (12) are arranged on the circumferential direction of the combustion chamber detonation section (10) and the combustion chamber detonation section (14) at equal intervals along the axial direction, and an auxiliary nozzle air pipeline (9) and an auxiliary nozzle fuel pipeline (8) are arranged on each auxiliary nozzle (12).
2. The high frequency pulse detonation combustion power plant of claim 1, characterized by: the tail nozzle (17) is a convergent nozzle, the contraction ratio is 1.2 to 1.5, and the convergence angle is 6 to 10 degrees.
3. The high frequency pulse detonation combustion power plant of claim 1, characterized by: the multistage series thrust augmentation structure (18) comprises a first-stage thrust augmentation device (22), a second-stage thrust augmentation device (27) and a third-stage thrust augmentation device (32) which are sequentially connected from left to right.
4. The high frequency pulse detonation combustion power plant of claim 3, characterized by: the first-stage thrust booster (22) comprises a first arc-shaped air inlet end face (20) and a first axisymmetric straight nozzle (21), the second-stage thrust booster (27) comprises a second arc-shaped air inlet end face (25) and a second axisymmetric straight nozzle (26), and the third-stage thrust booster (32) comprises a third arc-shaped air inlet end face (30) and a third axisymmetric straight nozzle (31); a plurality of multistage series-connection boosting structure connecting rods (16) are uniformly arranged in the circumferential direction of the first arc-shaped air inlet end face (20), one end of each multistage series-connection boosting structure supporting plate (15) is connected with the corresponding multistage series-connection boosting structure connecting rod (16), and the other end of each multistage series-connection boosting structure supporting plate is connected with the tail of the pulse detonation combustion chamber (5); a plurality of first-stage thrust increaser connecting rods (24) are uniformly arranged in the circumferential direction of the second arc-shaped air inlet end surface (25), one ends of a plurality of first-stage thrust increaser supporting plates (23) are connected with the corresponding first-stage thrust increaser connecting rods (24), and the other ends of the first-stage thrust increaser supporting plates are connected with the first axisymmetric straight spray pipe (21); a plurality of second-stage thrust increaser connecting rods (29) are uniformly arranged in the circumferential direction of the third arc-shaped air inlet end surface (30), one ends of a plurality of second-stage thrust increaser supporting plates (28) are connected with the corresponding second-stage thrust increaser connecting rods (29), and the other ends of the second-stage thrust increaser connecting plates are connected with the second axisymmetric straight spray pipe (26).
5. The high frequency pulse detonation combustion power plant of claim 4, characterized in that: the number of the multistage series thrust augmentation structure support plate (15) and the number of the multistage series thrust augmentation structure connecting rods (16) are both 4, the number of the first-stage thrust augmentation support plate (23) and the first-stage thrust augmentation connecting rods (24) is both 4, and the number of the second-stage thrust augmentation support plate (28) and the second-stage thrust augmentation connecting rods (29) is both 4.
6. The high frequency pulse detonation combustion power plant of any one of claims 1 to 5, characterized by: the inner wall of the combustion chamber detonation section (10) is provided with a first spiral obstacle (11), the inner wall of the combustion chamber detonation section (14) is provided with a second spiral obstacle (13), and the pitch of the first spiral obstacle (11) is smaller than that of the second spiral obstacle (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420293451.4U CN203962199U (en) | 2014-06-04 | 2014-06-04 | A kind of high-frequency pulse pinking combustion-powered apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420293451.4U CN203962199U (en) | 2014-06-04 | 2014-06-04 | A kind of high-frequency pulse pinking combustion-powered apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203962199U true CN203962199U (en) | 2014-11-26 |
Family
ID=51922795
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420293451.4U Expired - Fee Related CN203962199U (en) | 2014-06-04 | 2014-06-04 | A kind of high-frequency pulse pinking combustion-powered apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203962199U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033286A (en) * | 2014-06-04 | 2014-09-10 | 西安热工研究院有限公司 | High-frequency impulse knocking combustion power plant |
| CN113932252A (en) * | 2021-11-19 | 2022-01-14 | 华能国际电力股份有限公司 | Pulse detonation and rotary detonation combined type multi-channel combustion chamber |
| CN114542326A (en) * | 2022-02-28 | 2022-05-27 | 湖北华海节龙燃油设备科技有限公司 | Compressed air deflagration engine and power generation method |
-
2014
- 2014-06-04 CN CN201420293451.4U patent/CN203962199U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033286A (en) * | 2014-06-04 | 2014-09-10 | 西安热工研究院有限公司 | High-frequency impulse knocking combustion power plant |
| CN104033286B (en) * | 2014-06-04 | 2016-01-13 | 西安热工研究院有限公司 | A kind of high-frequency pulse pinking combustion-powered apparatus |
| CN113932252A (en) * | 2021-11-19 | 2022-01-14 | 华能国际电力股份有限公司 | Pulse detonation and rotary detonation combined type multi-channel combustion chamber |
| CN114542326A (en) * | 2022-02-28 | 2022-05-27 | 湖北华海节龙燃油设备科技有限公司 | Compressed air deflagration engine and power generation method |
| CN114542326B (en) * | 2022-02-28 | 2024-05-28 | 湖北华海节龙燃油设备科技有限公司 | Compressed air deflagration engine and power generation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104033286B (en) | A kind of high-frequency pulse pinking combustion-powered apparatus | |
| CN101881238B (en) | Air-breathing pulse detonation engine and detonation method thereof | |
| CN103069142B (en) | Multitube valveless pulse-knocking engine | |
| CN100549399C (en) | A kind of high-frequency pulse pinking engine and controlling method thereof | |
| US8650856B2 (en) | Fluidic deflagration-to-detonation initiation obstacles | |
| CN103899435B (en) | A kind of combined type pulse detonation engine detonation chamber | |
| CN102619643B (en) | Jet ignition device of pulse detonation engine | |
| EP2327867A2 (en) | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation | |
| CN104265506B (en) | Pulse-knocking engine | |
| CN212408731U (en) | Pulse detonation combustion chamber with smooth detonation gas energy distribution structure | |
| CN110131071B (en) | Pulse detonation engine combustion chamber and detonation method thereof | |
| CN201858046U (en) | Pulse detonation engine realizing secondary detonation | |
| CN102003303A (en) | Pulse detonation engine with secondary detonation | |
| CN104500272A (en) | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device | |
| CN109322761B (en) | high-Mach-number in-flight engine annular combustion chamber and spiral oblique detonation combustion method | |
| CN203962199U (en) | A kind of high-frequency pulse pinking combustion-powered apparatus | |
| CN111305972A (en) | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation | |
| CN201696166U (en) | Aspirated impulse knocking engine | |
| CN102606343B (en) | Detonation chamber of pulse detonation engine | |
| CN202578943U (en) | Jet ignition device for pulse detonation engine | |
| CN107476898B (en) | A kind of air-breathing pulse detonation engine inhibits the structure of combustion gas forward pass | |
| CN204099075U (en) | Pulse-knocking engine | |
| RU48368U1 (en) | Pulsating Air-Jet Engine | |
| CN110761898B (en) | Device for generating super-enthalpy detonation by utilizing micro-scale spiral channel | |
| CN110145409B (en) | High-frequency igniter system of multi-tube pulse detonation engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141126 Termination date: 20170604 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |