CN110425045B - Continuous rotation detonation engine - Google Patents
Continuous rotation detonation engine Download PDFInfo
- Publication number
- CN110425045B CN110425045B CN201910744032.5A CN201910744032A CN110425045B CN 110425045 B CN110425045 B CN 110425045B CN 201910744032 A CN201910744032 A CN 201910744032A CN 110425045 B CN110425045 B CN 110425045B
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- insulating sleeve
- ignition core
- insulating
- detonation engine
- combustion chamber
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- 238000005474 detonation Methods 0.000 title claims abstract description 49
- 238000002485 combustion reaction Methods 0.000 claims abstract description 52
- 239000000446 fuel Substances 0.000 claims description 16
- 230000013011 mating Effects 0.000 claims description 6
- 239000013543 active substance Substances 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 6
- 239000002360 explosive Substances 0.000 abstract description 5
- 239000000203 mixture Substances 0.000 abstract description 5
- 238000006243 chemical reaction Methods 0.000 abstract description 3
- 230000007704 transition Effects 0.000 description 7
- 230000015572 biosynthetic process Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
- 239000004810 polytetrafluoroethylene Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spark Plugs (AREA)
Abstract
The invention provides a continuous rotary detonation engine, which comprises an inner shell, an outer shell, an insulating sleeve, an ignition core and an insulating connecting piece. The outer housing includes a front portion and a rear portion, the front portion and the inner housing together forming an annular airflow channel, the rear portion being electrically connected to a low voltage end of the high voltage power supply. The insulating sleeve forms an annular combustion chamber with the rear portion. The ignition core is electrically connected with the high-voltage end of the high-voltage power supply. When connected with a high-voltage power supply, the interior of the annular combustion chamber generates a high-volume, high-concentration low-temperature plasma discharge stream. Further, when the voltage difference between the low voltage end and the high voltage end of the high voltage power supply is sufficiently large, the low temperature plasma discharge current in the annular combustion chamber is converted into a large number of discharge current filaments and a large amount of active substances are generated, at this time, the explosive mixture in the annular combustion chamber is broken down and rotated to knock and burn, and the ignition effect is enhanced due to the fact that the active substances accelerate the chemical reaction rate, so that the time for knocking to knocking is shortened.
Description
Technical Field
The invention relates to the technical field of aerospace equipment, in particular to a continuous rotary detonation engine.
Background
In recent years, with the continuous and intensive research on hypersonic aircrafts and single-stage in-orbit power systems, novel continuous rotary detonation engine technology has been rapidly developed. Research shows that the propulsion technology based on detonation combustion can greatly reduce fuel consumption, greatly improve the specific impulse characteristic of the power device, and has important significance for widening the work envelope of the air suction type aircraft and improving the economical efficiency and operational performance of the existing weaponry.
The continuous rotation detonation engine is a power technology utilizing detonation combustion, and is characterized in that: (1) The detonation wave can be continuously transmitted along the circumferential direction of the combustion chamber only by one-time successful detonation; (2) The combustion speed is high, the heat release intensity is high, the combustion chamber has a compact structure, and the length of the engine can be shortened; (3) The device has supercharging property, can reduce the number of compressor stages of a turbine engine or reduce the total pressure loss of an inlet channel of a ramjet engine, is beneficial to simplifying the design of a propulsion system and improving the thrust-weight ratio of the engine; (4) The device can work in an air suction mode or a rocket mode, and the working range can be changed from subsonic speed to supersonic speed with high Mach number. Therefore, research into continuously rotating knock engines has been attracting considerable attention in the scientific community.
However, since detonation combustion is a process of gradually changing from detonation to detonation, and the change between detonation and detonation requires a certain time and is not easy to control, detonation combustion still has the defects of high triggering difficulty and poor controllability compared with the traditional isobaric combustion, which is also a main reason for restricting the detonation combustion to be used for a power propulsion device.
Disclosure of Invention
In view of the problems in the background art, an object of the present invention is to provide a continuous rotary detonation engine that intensifies the ignition effect in an annular combustion chamber, and improves the rapid formation and stable propagation of rotary detonation waves in the annular combustion chamber, thereby shortening the time for the detonation transition to detonation.
In order to achieve the above object, the present invention provides a continuously rotating detonation engine for electrical connection to a high voltage power source. The continuously rotating detonation engine includes an inner housing, an outer housing, an insulating sleeve, an ignition core, and an insulating connector. The inner housing is provided with a fuel supply passage. The outer housing includes a front portion and a rear portion in an axial direction, the front portion of the outer housing and the inner housing together forming an annular air flow passage, the rear portion of the outer housing axially protruding from the inner housing and being for electrical connection with a low voltage end of a high voltage power supply. The insulating sleeve is axially located downstream of and fixed to the inner housing, and the insulating sleeve and the rear portion of the outer housing are formed with annular combustion chambers that communicate with the fuel supply passage and the annular air flow passage. The ignition core is located in the axial downstream of the inner shell and is arranged at intervals with the inner shell, and the ignition core is fixedly arranged on the inner side of the insulating sleeve and is used for being electrically connected with the high-voltage end of the high-voltage power supply. The insulating connecting piece is arranged between the inner shell and the ignition core in the axial direction, and the insulating connecting piece is fixedly connected with the insulating sleeve and the ignition core.
One end of the insulating sleeve in the axial direction is fixed to the inner shell, and the other end is flush with the rear part of the outer shell and the ignition core. Alternatively, one end of the insulating sleeve in the axial direction is fixed to the inner case, and the other end axially protrudes from the rear portion of the outer case and the ignition core.
The insulating sleeve is formed into a hollow cylindrical structure.
The ignition core has first connecting portion and second connecting portion, and first connecting portion fixed connection is in insulating sleeve and insulating connecting piece, and the second connecting portion is located between first connecting portion and the insulating connecting piece in radial and is used for being connected with high-voltage power supply's high-voltage terminal electricity.
The cross section of the ignition core is formed in a fan-shaped structure.
The second connecting portion of the ignition core is formed in a cylindrical structure.
The insulating connecting piece is provided with a first extending part and a second extending part, wherein the first extending part is connected with the inner shell, and the second extending part protrudes out of the first extending part in the circumferential direction and is connected with the insulating sleeve and the ignition core.
The second extension is provided with a mating slot that receives a portion of the ignition core and is connected to the portion of the ignition core.
The annular airflow channel is provided with an air inlet section and a connecting section, wherein the air inlet section extends along the radial direction, and the connecting section extends along the axial direction and is communicated with the air inlet section and the annular combustion chamber.
The connecting section of the annular airflow channel comprises a pressurizing part, and the pressurizing part is a channel which is tapered first and then expanded.
The beneficial effects of the invention are as follows:
when the rear part of the outer shell is electrically connected with the low-voltage end of the high-voltage power supply and the ignition core is electrically connected with the high-voltage end of the high-voltage power supply, the insulating sleeve and the inside of the annular combustion chamber formed at the rear part of the outer shell can generate a large-volume and high-concentration low-temperature plasma discharge stream. Further, when the voltage difference between the low voltage end and the high voltage end of the high voltage power supply is sufficiently large, the low temperature plasma discharge current in the annular combustion chamber is converted into a large amount of discharge current filaments and generates a large amount of active substances, at this time, the explosive mixture in the annular combustion chamber is broken down by the low temperature plasma discharge current filaments and starts rotary detonation combustion, and the active substances accelerate the chemical reaction rate in the rotary detonation combustion, so that the ignition effect in the annular combustion chamber is enhanced, the rapid formation and stable propagation of rotary detonation waves in the annular combustion chamber are improved, and the time for converting the detonation into the detonation is shortened. And, because the insulating sleeve is arranged between the rear part of the outer shell and the ignition core, the discharge phenomenon is concentrated on the part of the annular combustion chamber corresponding to the ignition core, so that full-field discharge is avoided, and the ignition effect in the annular combustion chamber is further enhanced.
Drawings
Fig. 1 is a schematic structural view of a continuously rotating knock engine of the present invention.
FIG. 2 is a cross-sectional view of the continuously rotating detonation engine of FIG. 1 taken along line A-A.
Fig. 3 is a cross-sectional view of the insulated connector of fig. 1 taken along line A-A.
Wherein reference numerals are as follows:
1 inner housing 521 mating groove
2 outer shell S annular airflow channel
2A front S1 air intake section
2B rear S2 connecting section
3 insulating sleeve S21 booster
4 ignition core S22 first transition section
41 first connecting portion S23 second transition portion
42 second connection portion T fuel supply passage
5 insulating connecting piece F annular combustion chamber
51 first extension C axial direction
52 second extension D radial direction
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application will be further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the present application.
In the description of the present application, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance unless explicitly specified or limited otherwise; the term "plurality" refers to more than two (including two); unless specified or indicated otherwise, the terms "connected," "fixed," and the like are to be construed broadly and are, for example, capable of being fixedly connected, detachably connected, or integrally connected, electrically connected, or signally connected; "coupled" may be directly coupled or indirectly coupled through intermediaries. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be. The present application is described in further detail below by way of specific embodiments and with reference to the accompanying drawings.
The continuously rotating detonation engine of the present application is adapted for electrical connection to a high voltage power source (not shown) that includes a high voltage end and a low voltage end. When the continuously rotating detonation engine is connected with the high voltage power supply, it utilizes a discharge phenomenon between the high voltage end and the low voltage end of the high voltage power supply to perform ignition.
Specifically, referring to fig. 1 to 3, a continuously rotating detonation engine may include an inner housing 1, an outer housing 2, an insulating sleeve 3, an ignition core 4, and an insulating connector 5.
The inner housing 1 is provided with a fuel supply passage T that communicates with a fuel supply tank (not shown) and supplies fuel to the annular combustion chamber F. Specifically, the inner case 1 may be formed in a cylindrical structure.
The outer casing 2 comprises a front part 2A and a rear part 2B in the axial direction C, the front part 2A of the outer casing 2 together with the inner casing 1 forming an annular air flow channel S, the rear part 2B of the outer casing 2 protruding in the axial direction C from the inner casing 1 and being adapted to be electrically connected to the low voltage side of the high voltage power supply, the annular air flow channel S being in communication with the outside atmosphere. Wherein the outer casing 2 is sleeved on the inner casing 1 and forms a supporting structure of the continuous rotary detonation engine together with the inner casing 1. Specifically, the outer case 2 may be formed in a hollow cylindrical structure.
It should be noted that the front portion 2A and the rear portion 2B of the outer case 2 may be integrally formed, and the division of the front portion 2A and the rear portion 2B is specifically defined by the connection position of the insulating sleeve 3 and the inner case 1.
The insulating sleeve 3 is located downstream of the inner housing 1 in the axial direction C and can be fixed to the inner housing 1 by bolting, and the insulating sleeve 3 and the rear portion 2B of the outer housing 2 are formed with an annular combustion chamber F which communicates with the fuel supply passage T and the annular air flow passage S to receive fuel and air, respectively, and the fuel and air are mixed in the annular combustion chamber F to form an explosive mixture. Of course, the insulating sleeve 3 and the inner housing 1 can also be fixedly connected by providing corresponding clamping structures.
Specifically, the insulating sleeve 3 may be formed in a hollow cylindrical structure, and the insulating sleeve 3 may be made of a ceramic material.
The ignition core 4 is located downstream of the inner housing 1 in the axial direction C and is disposed at a distance from the inner housing 1, and the ignition core 4 is fixedly disposed inside the insulating sleeve 3 and is used for being electrically connected to the high-voltage end of the high-voltage power supply.
An insulating connector 5 is provided between the inner housing 1 and the ignition core 4 in the axial direction C, and the insulating connector 5 fixedly connects the insulating sleeve 3 and the ignition core 4 and is used for insulating isolation between the inner housing 1 and the ignition core 4. In particular, the insulating connector 5 may be made of an insulating material, such as polytetrafluoroethylene.
When the rear portion 2B of the outer case 2 is electrically connected to the low voltage end of the high voltage power supply and the ignition core 4 is electrically connected to the high voltage end of the high voltage power supply, a large volume, high concentration low temperature plasma discharge streamer (in which case the portion of the annular combustion chamber F corresponding to the ignition core 4 is a discharge region) can be generated inside the annular combustion chamber F formed by the insulating sleeve 3 and the rear portion 2B of the outer case 2. Further, when the voltage difference between the low voltage end and the high voltage end of the high voltage power supply is sufficiently large, the low temperature plasma discharge current in the annular combustion chamber F is converted into a large amount of discharge current filaments and generates a large amount of active substances, at this time, the explosive mixture in the annular combustion chamber F is broken down by the low temperature plasma discharge current filaments and starts rotary detonation combustion, and the active substances accelerate the chemical reaction rate in the rotary detonation combustion, so that the ignition effect in the annular combustion chamber F is enhanced, and the rapid formation and stable propagation of rotary detonation waves in the annular combustion chamber are improved, so that the time for converting the detonation into the detonation is shortened. And, since the insulating sleeve 3 is provided between the rear portion 2B of the outer case 2 and the ignition core 4, the discharge phenomenon is concentrated at the portion of the annular combustion chamber F corresponding to the ignition core 4 (i.e., the required discharge area), so that the full-field discharge is avoided, thereby further enhancing the ignition effect inside the annular combustion chamber F.
Referring to fig. 3, one end of the insulating sleeve 3 in the axial direction C is fixed to the inner case 1, and the other end may protrude in the axial direction C from the rear portion 2B of the outer case 2 and the ignition core 4. Alternatively, one end of the insulating sleeve 3 in the axial direction C is fixed to the inner housing 1, the other end may also be flush with the rear portion 2B of the outer housing 2 and the ignition core 4 (i.e., the other end of the insulating sleeve 3 is coplanar in the radial direction D with the corresponding end of the ignition core 4).
Referring to fig. 2, the ignition core 4 may have a first connection portion 41 and a second connection portion 42. The first connection portion 41 is fixedly connected to the insulating sleeve 3 and the insulating connector 5, the second connection portion 42 is located between the first connection portion 41 and the insulating connector 5 in the radial direction D and is used for being electrically connected to the high voltage end of the high voltage power source, and the second connection portion 42 may be formed in a cylindrical structure.
Preferably, the cross section of the ignition core 4 may be formed in a fan shape (as shown in fig. 3), in which case a portion of the annular combustion chamber F corresponding to the arc-shaped face of the ignition core 4 is a discharge region. Specifically, the angle of the fan-shaped ignition core 4 may be set according to the size of the area where discharge is required.
Referring to fig. 1, the insulating connector 5 may have a first extension 51 and a second extension 52, the first extension 51 may be connected to the inner case 1 by screw connection, and the second extension 52 protrudes from the first extension 51 in the circumferential direction and is connected to the insulating sleeve 3 and the ignition core 4.
Referring to fig. 3, the second extension 52 of the insulating connector 5 may be provided with a mating groove 521, the mating groove 521 receiving a portion of the ignition core 4 and being connectable with said portion of the ignition core 4 by a threaded connection.
Referring to fig. 1, the annular gas flow passage S may have an inlet section S1 extending in a radial direction D and directly communicable with the outside atmosphere, and a connecting section S2 extending in an axial direction C and communicable with the inlet section S1 and the annular combustion chamber F.
Further, the connecting section S2 may include a pressurizing portion S21. The pressurizing portion S21 is formed as a tapered-before-expanding passage, thereby increasing the pressure of air when it enters the annular combustion chamber F, thereby contributing to an improvement in the combustion efficiency of the rotary knock combustion of the explosive mixture in the annular combustion chamber F, and further enabling the continuous rotary knock engine to generate more power.
Referring to fig. 1, the fuel supply passage T may be provided at a portion of the inner housing 1 forming the pressurizing portion S21 of the connection section S2, and at this time, the fuel supply passage T is directly connected to the pressurizing portion S21 of the connection section S2, thereby facilitating rapid mixing of fuel supplied from the fuel supply passage T to the annular combustion chamber F and air supplied from the pressurizing portion S21 to the annular combustion chamber F.
The connecting section S2 may further include a first transition portion S22 and a second transition portion S23, the first transition portion S22 being communicated with the intake section S1 and the supercharging portion S21, and the second transition portion S23 being communicated with the supercharging portion S21 and the annular combustion chamber F.
Claims (10)
1. A continuously rotating detonation engine for electrical connection with a high voltage power source, characterized in that the continuously rotating detonation engine comprises an inner housing (1), an outer housing (2), an insulating sleeve (3), an ignition core (4) and an insulating connection (5);
the inner housing (1) is provided with a fuel supply passage (T);
the outer shell (2) comprises a front part (2A) and a rear part (2B) in the axial direction (C), the front part (2A) of the outer shell (2) and the inner shell (1) form an annular air flow channel (S), and the rear part (2B) of the outer shell (2) protrudes from the inner shell (1) along the axial direction (C) and is used for being electrically connected with the low-voltage end of the high-voltage power supply;
the insulating sleeve (3) is positioned at the downstream of the inner shell (1) in the axial direction (C) and is fixed on the inner shell (1), an annular combustion chamber (F) is formed at the rear part (2B) of the insulating sleeve (3) and the outer shell (2), and the annular combustion chamber (F) is communicated with the fuel supply channel (T) and the annular airflow channel (S);
the ignition core (4) is positioned at the downstream of the inner shell (1) in the axial direction (C) and is arranged at intervals with the inner shell (1), and the ignition core (4) is fixedly arranged at the inner side of the insulating sleeve (3) and is used for being electrically connected with the high-voltage end of the high-voltage power supply;
the insulating connecting piece (5) is arranged between the inner shell (1) and the ignition core (4) in the axial direction (C), and the insulating connecting piece (5) is fixedly connected with the insulating sleeve (3) and the ignition core (4).
2. The continuously rotating detonation engine of claim 1, wherein,
one end of the insulating sleeve (3) in the axial direction (C) is fixed on the inner shell (1), and the other end of the insulating sleeve is flush with the rear part (2B) of the outer shell (2) and the ignition core (4); or alternatively
One end of the insulating sleeve (3) in the axial direction (C) is fixed on the inner shell (1), and the other end of the insulating sleeve protrudes out of the rear part (2B) of the outer shell (2) and the ignition core (4) along the axial direction (C).
3. A continuously rotating detonation engine as claimed in claim 1, characterized in that the insulating sleeve (3) is formed as a hollow cylindrical structure.
4. The continuously rotating detonation engine of claim 1, characterized in that the ignition core (4) has a first connection portion (41) and a second connection portion (42), the first connection portion (41) being fixedly connected to the insulating sleeve (3) and the insulating connection member (5), the second connection portion (42) being located between the first connection portion (41) and the insulating connection member (5) in the radial direction (D) and being for electrical connection with the high voltage end of the high voltage power supply.
5. The continuously rotating detonation engine as claimed in claim 4, characterized in that the ignition core (4) is formed in a sector-shaped structure in cross section.
6. The continuously rotating detonation engine as claimed in claim 4, characterized in that the second connecting portion (42) of the ignition core (4) is formed in a cylindrical structure.
7. The continuous rotary detonation engine of claim 1, characterized in that the insulating connection (5) has a first extension (51) and a second extension (52), the first extension (51) being connected to the inner housing (1), the second extension (52) protruding in the circumferential direction from the first extension (51) and being connected to the insulating sleeve (3) and the ignition core (4).
8. The continuously rotating detonation engine of claim 7, characterized in that the second extension (52) is provided with a mating groove (521), the mating groove (521) receiving a portion of the ignition core (4) and being connected to said portion of the ignition core (4).
9. The continuous rotary detonation engine of claim 1 wherein the annular air flow channel (S) has an air intake section (S1) and a connecting section (S2), the air intake section (S1) extending in a radial direction (D), the connecting section (S2) extending in an axial direction (C) and communicating with the air intake section (S1) and the annular combustion chamber (F).
10. The continuously rotating detonation engine of claim 9, characterized in that the connecting segment (S2) includes a supercharging portion (S21), and the supercharging portion (S21) is a tapered-before-expanding passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910744032.5A CN110425045B (en) | 2019-08-13 | 2019-08-13 | Continuous rotation detonation engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910744032.5A CN110425045B (en) | 2019-08-13 | 2019-08-13 | Continuous rotation detonation engine |
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| CN110425045A CN110425045A (en) | 2019-11-08 |
| CN110425045B true CN110425045B (en) | 2024-02-06 |
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| CN201910744032.5A Active CN110425045B (en) | 2019-08-13 | 2019-08-13 | Continuous rotation detonation engine |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113153578A (en) * | 2021-04-23 | 2021-07-23 | 中国人民解放军国防科技大学 | Coaxial injection continuous rotation detonation test device |
| CN113464311B (en) * | 2021-08-11 | 2022-05-03 | 北京理工大学 | Rotating detonation engine with adjustable detonation wave propagation mode and application method |
| CN114001376B (en) * | 2021-11-23 | 2023-03-14 | 中国人民解放军空军工程大学 | Gas collection cavity plasma activation explosion-assisted rotary detonation combustion chamber |
| CN115355543B (en) * | 2022-08-19 | 2023-10-10 | 西北工业大学 | Composite rotary detonation combustion device |
| CN116557169B (en) * | 2023-07-10 | 2023-09-19 | 中国人民解放军空军工程大学 | Device and method for regulating and controlling working mode of rotary detonation engine by using plasma |
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| EP1980790A2 (en) * | 2007-04-12 | 2008-10-15 | General Electric Company | Electro-dynamic swirler, combustion apparatus and methods using the same |
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| CN108869094A (en) * | 2018-07-27 | 2018-11-23 | 清华大学 | Rotate detonation engine |
| CN210919249U (en) * | 2019-08-13 | 2020-07-03 | 清华大学 | Continuous rotation detonation engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7937945B2 (en) * | 2006-10-27 | 2011-05-10 | Kinde Sr Ronald August | Combining a series of more efficient engines into a unit, or modular units |
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| EP1980790A2 (en) * | 2007-04-12 | 2008-10-15 | General Electric Company | Electro-dynamic swirler, combustion apparatus and methods using the same |
| CN101285590A (en) * | 2007-04-12 | 2008-10-15 | 通用电气公司 | Electro-dynamic swirler, combustion apparatus and methods using the same |
| CN107218155A (en) * | 2017-06-06 | 2017-09-29 | 陈蜀乔 | A kind of pulse in advance ignite can steady operation detonation engine |
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