CN114777162A - Continuous rotation knocking ramjet engine with radial oil supply and air supply - Google Patents
Continuous rotation knocking ramjet engine with radial oil supply and air supply Download PDFInfo
- Publication number
- CN114777162A CN114777162A CN202210670840.3A CN202210670840A CN114777162A CN 114777162 A CN114777162 A CN 114777162A CN 202210670840 A CN202210670840 A CN 202210670840A CN 114777162 A CN114777162 A CN 114777162A
- Authority
- CN
- China
- Prior art keywords
- fuel
- oxidant
- combustion chamber
- ramjet engine
- pressure stabilizing
- 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.)
- Pending
Links
Images
Classifications
-
- 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
-
- 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
- F02K7/10—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
Abstract
The invention provides a continuous rotary detonation ramjet engine with radial oil and gas supply, which belongs to the technical field of aeroengines and comprises an oxidant injection mandrel, a fuel pressure stabilizing cavity and a combustion chamber, wherein the oxidant injection mandrel is used for oxidant inflow, the fuel pressure stabilizing cavity is used for fuel pressure stabilization, a pressure stabilizing space is arranged in the oxidant injection mandrel, a plurality of first gaps are uniformly distributed on the oxidant injection mandrel, oxidant enters the combustion chamber through the first gaps, and a plurality of second gaps for introducing fuel into the combustion chamber are radially and uniformly distributed on the fuel pressure stabilizing cavity. The ramjet changes the feeding direction of the fuel into the radial direction, so that the fuel and the oxidant generate radial hedging in a combustion chamber, and good mixing is realized; the oxidant and the fuel cavities are provided with pressure stabilizing structures, and the gap flow channels uniformly distributed in 360 degrees can also play a flow equalizing effect; and the self-cooling is carried out on the combustion chamber by adopting the fuel required by the self-cooling device, so that the stable work of the long-time detonation state of the detonation combustion chamber is realized, and the problem of the long-time reliable work of the detonation ramjet is solved.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a continuous rotation knocking ramjet engine with radial oil supply and air supply.
Background
The aerospace field is more and more competitive, and the research on key innovation technology in the aerospace field draws more and more attention from various countries. In recent years, with the continuous and deep research on hypersonic aircrafts and single-stage in-orbit power systems, the technology of novel continuous rotation detonation engines is rapidly developed. Researches show that the propelling technology based on detonation combustion can greatly reduce fuel consumption, greatly improve the specific impulse characteristic of a power device and has important significance for widening the working envelope of the air-breathing aircraft and improving the economy and the operational performance of the conventional weaponry. As a leading technology capable of overtaking at a curve, comprehensive and deep research on the technology is more urgent.
The continuous rotation detonation engine is a power technology utilizing detonation combustion, and is characterized by comprising the following steps: (1) only one time of successful detonation is needed, and the detonation wave can continuously propagate along the circumferential direction of the combustion chamber; (2) the combustion speed is high, the heat release strength is high, the structure of the combustion chamber is compact, and the length of the engine can be shortened; (3) the boosting characteristic is provided, the number of stages of a compressor of the turbine engine can be reduced or the total pressure loss of an air inlet passage of the ramjet engine can be reduced, the design of a propulsion system can be simplified, and the thrust-weight ratio of the engine can be improved; (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 high Mach number supersonic speed. Therefore, the research of the continuous rotation knocking engine gradually draws a great deal of attention in the scientific field. Wherein the knocking combustion chamber is the key object of knocking research. In order to realize engineering, a great deal of research is carried out on the injection form, and at present, the form of axially feeding fuel and oxidant is adopted, but the mixing effect is general, and after a plurality of tests, the obvious improvement is not seen, so the current research and development thought is carried out in the direction of radially feeding fuel at an angle. Meanwhile, a large amount of verification work is carried out on the research of high-temperature coating of the combustion chamber, the research of air film cooling and the research of water cooling. However, both film cooling and water cooling require additional cooling media and piping and accessories, which are contrary to the compact layout and light weight design of engines required by the leading technology.
At present, a lot of achievements and a lot of experiences are obtained and accumulated for research on a continuous rotation detonation engine, but the aperture of a fuel injection hole of a current detonation combustor is not adjustable, the pressure is unstable, the detonation combustor is simply injected by pressure, the working temperature of the detonation combustor is too high and exceeds 1500K, the detonation combustor can not work for a long time by using common stainless steel materials, the aperture of the fuel injection hole is not adjustable, and a plurality of different parts need to be correspondingly processed in different-size injection hole demand scenes.
Disclosure of Invention
In order to solve the above problems, the present invention provides a continuous rotary detonation ramjet engine with radial oil and gas supply, the ramjet engine includes an oxidant injection mandrel for oxidant inflow, a fuel pressure stabilizing cavity for fuel pressure stabilization, and a combustion chamber, a pressure stabilizing space for oxidant pressure stabilization is provided in the oxidant injection mandrel, a plurality of first slits are uniformly distributed on the oxidant injection mandrel, oxidant enters the combustion chamber through the first slits, and a plurality of second slits for fuel introduction into the combustion chamber are radially uniformly distributed on the fuel pressure stabilizing cavity.
The continuous rotation knocking ramjet engine with radial oil and gas supply is also characterized in that the fuel pressure stabilizing cavity comprises a fuel injection end plate, a thrust chamber inner shell arranged outside the combustion chamber, a thrust chamber outer shell arranged outside the thrust chamber inner shell, a fuel gas inlet pipe connected with the fuel injection end plate and a nozzle expansion shell connected with the thrust chamber outer shell, fuel enters the fuel pressure stabilizing cavity through the fuel gas inlet pipe, and the fuel stably circulates while being stabilized in the fuel pressure stabilizing cavity.
The continuous rotation detonation ramjet engine with radial oil and gas supply also has the characteristic that the fuel pressure stabilizing cavity is welded by sequentially welding a fuel injection end plate, a fuel gas inlet pipe, a thrust chamber inner shell, a thrust chamber outer shell and a nozzle expansion outer shell.
The continuous rotating detonation ramjet engine with radial oil and gas supply provided by the invention is also characterized in that the second slits are radially arranged on the thrust chamber inner shell.
The continuous rotating detonation ramjet engine with radial oil and gas supply provided by the invention is also characterized in that the oxidant injection mandrel is fixedly connected with the fuel injection end plate and the thrust chamber shell through welding.
The continuous rotation knocking ramjet engine with radial oil and gas supply also has the characteristic that the width of the second gap is more than or equal to 0.06 mm.
The continuous rotation detonation ramjet engine with radial oil and gas supply provided by the invention is also characterized in that a Laval nozzle is arranged in the combustion chamber.
The continuous rotation detonation ramjet engine with radial oil and gas supply provided by the invention is also characterized in that the oxidant injection mandrel penetrates through the fuel injection end plate, the end part of the oxidant injection mandrel is arranged in the combustion chamber, and the first gap is arranged on the end part of the oxidant injection mandrel, which is positioned in the combustion chamber.
The continuous rotation detonation ramjet engine with radial oil and gas supply provided by the invention is also characterized in that the oxidant injection mandrel and the fuel inlet pipe are arranged on the same side of the fuel injection end plate, and the thrust chamber inner shell and the thrust chamber outer shell are arranged on the other side of the fuel injection end plate.
The continuous rotating detonation ramjet engine with the oil and the gas supplied radially provided by the invention is also characterized in that the first gap and the second gap are oppositely arranged.
Advantageous effects
The continuous rotation knocking ramjet engine with radial oil supply and gas supply changes the feeding direction of fuel into radial direction, so that the fuel and oxidant generate radial opposite impact in a combustion chamber, and good mixing is realized; the oxidant and the fuel cavity are provided with pressure stabilizing structures, and the gap flow channels uniformly distributed at 360 degrees can also play a flow equalizing effect; and the self-cooling is carried out on the combustion chamber by adopting the fuel required by the self-cooling device, so that the stable work of the long-time detonation state of the detonation combustion chamber is realized, and the problem of the long-time reliable work of the detonation ramjet is solved.
Drawings
FIG. 1 is a cross-sectional view of a radial fueled, continuously rotating detonation ramjet engine provided in accordance with an embodiment of the present invention;
FIG. 2 is an external view of a radial fuelled continuous rotation detonation ramjet engine provided in accordance with an embodiment of the present invention;
FIG. 3 is a perspective view of a radial fuelled continuous rotation detonation ramjet engine provided in accordance with an embodiment of the present invention;
FIG. 4 is a profile view of an oxidant injection mandrel provided in accordance with an embodiment of the present invention;
FIG. 5 is a cross-sectional view of an oxidant injection mandrel provided in accordance with an embodiment of the present invention;
FIG. 6 is a cross-sectional view of an inner ring of a thrust chamber provided by an embodiment of the present invention;
FIG. 7 is an outline view of an inner thrust ring provided in accordance with an embodiment of the present invention.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not limited to the invention, and that functional, methodological, or structural equivalents thereof, which are equivalent or substituted by those of ordinary skill in the art, are within the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, "a plurality" means two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may include, for example, fixed connections, removable connections, or integral connections; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
The embodiment of the invention provides a continuous rotation detonation ramjet engine with radial oil supply and gas supply, as shown in fig. 1-7, the ramjet engine comprises an oxidant injection mandrel 1 for oxidant inflow, a fuel pressure stabilizing cavity for fuel pressure stabilization and a combustion chamber, a pressure stabilizing space for oxidant pressure stabilization is arranged in the oxidant injection mandrel 1, a plurality of first gaps 11 are uniformly distributed on the oxidant injection mandrel 1, oxidant enters the combustion chamber through the first gaps 11, and a plurality of second gaps 41 for fuel introduction into the combustion chamber are radially and uniformly distributed on the fuel pressure stabilizing cavity.
The continuous rotating detonation ramjet engine with the radial oil supply and the radial gas supply changes the feeding direction of the fuel into the radial direction, so that the fuel and the oxidant generate radial hedging in the combustion chamber, and good mixing is realized; the oxidant and the fuel cavities are provided with pressure stabilizing structures, and the uniformly distributed gap flow passages can also play a flow equalizing effect; the first gap 11 and the second gap 41 are easy to process, the injection nozzle structure in the traditional structure is replaced, the injection nozzle structure can be integrally formed, the length and the width of the gap can be adjusted according to the test requirement, and the proportion of the oxidant and the fuel can be changed by using the change.
In some embodiments, the fuel pressure stabilizing cavity comprises a fuel injection end plate 2, a thrust chamber inner shell 4 arranged outside the combustion chamber, a thrust chamber outer shell 3 arranged outside the thrust chamber inner shell 4, a fuel inlet pipe 6 connected to the fuel injection end plate 2, and a nozzle expanding outer shell 5 connected with the thrust chamber outer shell 3, wherein fuel enters the fuel pressure stabilizing cavity through the fuel inlet pipe 6, and the fuel stably circulates while stabilizing the pressure in the fuel pressure stabilizing cavity. The fuel realizes self-cooling to the combustion chamber in the stable circulation process in the pressure stabilizing cavity, realizes the stable work of the long-time detonation state of the detonation combustion chamber, solves the problem of long-time reliable work of the detonation ramjet, and simultaneously can be heated to the temperature which is easier to atomize and burn.
In some embodiments, the fuel plenum chamber is welded in the sequence of welding the fuel injection end plate 2, the fuel inlet pipe 6, the thrust chamber inner casing 4, the thrust chamber outer casing 3 and the nozzle expansion casing 5 in sequence.
In some embodiments, the second slits 41 are arranged radially on the thrust housing inner shell 4.
In some embodiments, the oxidant injection mandrel 1 is fixedly attached to the fuel injection end plate 2 and the thrust chamber housing 3 by welding.
In some embodiments, the width of the second slit 41 is greater than or equal to 0.06 mm.
In some embodiments, a laval nozzle is provided within the combustion chamber. The Laval nozzle provided by the embodiment can increase the air injection speed and strengthen the thrust conversion.
In some embodiments, the oxidant injection mandrel 1 passes through the fuel injection end plate 2 with its end placed in the combustion chamber, and the first slit 11 is provided at the end of the oxidant injection mandrel 1 located in the combustion chamber.
In some embodiments, the oxidant injection mandrel 1 and the fuel inlet pipe 6 are disposed on the same side of the fuel injection end plate 2, and the thrust chamber inner casing 4 and the thrust chamber outer casing 3 are disposed on the other side of the fuel injection end plate 2.
In some embodiments, the first slit 11 and the second slit 41 are disposed opposite to each other. The first gap 11 and the second gap 41 are arranged oppositely, so that the fuel and the oxidant can generate opposite impact, and the mixing effect of the fuel and the oxidant under the pressure is better.
The workflow of the above embodiment:
oxidant enters from the oxidant injection mandrel 1, the incoming flow of the oxidant is more stable in a pressure stabilizing space in the mandrel, the oxidant is injected into a combustion chamber through a first gap 11 on the oxidant injection mandrel 1 in a radial 360-degree mode, fuel enters a fuel pressure stabilizing cavity through a fuel inlet pipe 6, enters a second gap 41 after stable circulation of an outer ring of an inner shell 4 of the thrust chamber and is also injected into the combustion chamber in the same radial 360-degree mode, and the fuel and the oxidant are injected in opposite directions, so that better mixing effects are achieved. The ignition device works at the same time, so that a continuously rotating detonation wave is formed in the combustion chamber, and continuously mixed fuel and oxidant are provided for detonation before and after the detonation wave, so that continuous and stable thrust is generated. After the combustion working state is finished, firstly stopping supplying fuel oil, electrifying an inert gas nozzle electromagnetic valve of an external fuel oil pipeline to start working, purging a fuel cavity by gas, cleaning redundant fuel oil, spraying residual fuel from a nozzle at the tail part of the combustion chamber by high-pressure gas, cooling the wall surface of the combustion chamber for a short time, and finishing a complete working cycle.
The above description is intended to be illustrative of the preferred embodiment of the present invention and should not be taken as limiting the invention, but rather, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A continuously rotating detonation ramjet engine fed radially with oil and gas, characterised in that it comprises an oxidant injection mandrel for oxidant inflow, a fuel plenum for fuel stabilisation and a combustion chamber,
a pressure stabilizing space for stabilizing the pressure of the oxidant is arranged in the oxidant injection mandrel, a plurality of first gaps are uniformly distributed on the oxidant injection mandrel, the oxidant enters the combustion chamber through the first gaps,
and a plurality of second gaps for introducing fuel into the combustion chamber are uniformly distributed in the fuel pressure stabilizing cavity in the radial direction.
2. The continuous rotary knocking ramjet engine supplied with air radially according to claim 1, wherein the fuel pressure stabilizing cavity comprises a fuel injection end plate, a thrust chamber inner shell arranged outside the combustion chamber, a thrust chamber outer shell arranged outside the thrust chamber inner shell, a fuel inlet pipe connected to the fuel injection end plate and a nozzle expansion shell connected with the thrust chamber outer shell, the fuel enters the fuel pressure stabilizing cavity through the fuel inlet pipe, and the fuel is stabilized and circulated in the fuel pressure stabilizing cavity.
3. The continuously rotating detonation ramjet engine with radial fuel and air supply according to claim 2, characterised in that the fuel plenum is welded in the sequence of welding the fuel injection end plate, the fuel inlet pipe, the thrust chamber inner casing, the thrust chamber outer casing and the nozzle expansion casing.
4. The continuously rotating detonation ramjet engine with radial oil supply and gas supply of claim 2, characterized in that the second slits are arranged radially on the thrust chamber inner casing.
5. The radially-fed continuous rotary detonation ramjet engine of claim 2, wherein the oxidant injection mandrel is fixedly attached to the fuel injection end plate and the thrust chamber housing by welding.
6. The radially oil-fed and gas-fed continuous rotary detonation ramjet engine according to claim 1, characterized in that the width of the second slot is greater than or equal to 0.06 mm.
7. The continuously rotating detonation ramjet engine with radial oil supply and gas supply of claim 1, characterised in that a laval nozzle is provided inside the combustion chamber.
8. The radially-fed continuous rotary detonation ramjet engine of claim 2, wherein said oxidant injection mandrel passes through said fuel injection end plate with an end disposed within said combustion chamber, said first slot being disposed on the end of said oxidant injection mandrel within the combustion chamber.
9. The radially-fed continuous rotary detonation ramjet engine of claim 2, wherein said oxidant injection mandrel and said fuel intake are disposed on the same side of said fuel injection end plate, and said inner and outer thrust chamber casings are disposed on the other side of said fuel injection end plate.
10. The radially oil fed continuous rotary detonation ramjet engine of claim 1, wherein the first and second slots are oppositely disposed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210670840.3A CN114777162A (en) | 2022-06-15 | 2022-06-15 | Continuous rotation knocking ramjet engine with radial oil supply and air supply |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210670840.3A CN114777162A (en) | 2022-06-15 | 2022-06-15 | Continuous rotation knocking ramjet engine with radial oil supply and air supply |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114777162A true CN114777162A (en) | 2022-07-22 |
Family
ID=82421209
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210670840.3A Pending CN114777162A (en) | 2022-06-15 | 2022-06-15 | Continuous rotation knocking ramjet engine with radial oil supply and air supply |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114777162A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115355543A (en) * | 2022-08-19 | 2022-11-18 | 西北工业大学 | Compound rotatory detonation combustion device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020130201A1 (en) * | 1999-10-28 | 2002-09-19 | Barykin Georgy Yur?Apos;Evich | High frequency pulse rate and high productivity detonation spray gun |
| US20170146244A1 (en) * | 2015-11-20 | 2017-05-25 | University Of Washington | Continuous rotating detonation engines and associated systems and methods |
| CN108757179A (en) * | 2018-05-29 | 2018-11-06 | 中国人民解放军国防科技大学 | Combined cycle engine and hypersonic aircraft |
| CN111520765A (en) * | 2019-02-05 | 2020-08-11 | 通用电气公司 | Rotary detonation combustor with non-circular cross-section |
| CN111927650A (en) * | 2020-07-13 | 2020-11-13 | 西安航天动力研究所 | Back pressure atomization bin structure for high-frequency combustion instability test of liquid rocket engine |
| CN112879178A (en) * | 2021-01-22 | 2021-06-01 | 南京理工大学 | Solid rocket ramjet based on detonation combustion |
-
2022
- 2022-06-15 CN CN202210670840.3A patent/CN114777162A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020130201A1 (en) * | 1999-10-28 | 2002-09-19 | Barykin Georgy Yur?Apos;Evich | High frequency pulse rate and high productivity detonation spray gun |
| US20170146244A1 (en) * | 2015-11-20 | 2017-05-25 | University Of Washington | Continuous rotating detonation engines and associated systems and methods |
| CN108757179A (en) * | 2018-05-29 | 2018-11-06 | 中国人民解放军国防科技大学 | Combined cycle engine and hypersonic aircraft |
| CN111520765A (en) * | 2019-02-05 | 2020-08-11 | 通用电气公司 | Rotary detonation combustor with non-circular cross-section |
| CN111927650A (en) * | 2020-07-13 | 2020-11-13 | 西安航天动力研究所 | Back pressure atomization bin structure for high-frequency combustion instability test of liquid rocket engine |
| CN112879178A (en) * | 2021-01-22 | 2021-06-01 | 南京理工大学 | Solid rocket ramjet based on detonation combustion |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115355543A (en) * | 2022-08-19 | 2022-11-18 | 西北工业大学 | Compound rotatory detonation combustion device |
| CN115355543B (en) * | 2022-08-19 | 2023-10-10 | 西北工业大学 | Composite rotary detonation combustion device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10641169B2 (en) | Hybrid combustor assembly and method of operation | |
| US6244041B1 (en) | Liquid-propellant rocket engine chamber and its casing | |
| CN109028142B (en) | Propulsion system and method of operating the same | |
| CN109028151B (en) | Multi-chamber rotary detonation combustor | |
| CN111664022B (en) | Combustion chamber of rotary detonation ramjet engine with fuel injection | |
| CN106014637A (en) | Air precooling compression aircraft engine and hypersonic velocity aircraft | |
| CN110541773B (en) | Wide-speed-range ramjet engine combustion chamber and working method thereof | |
| US20180231256A1 (en) | Rotating Detonation Combustor | |
| US20150275762A1 (en) | High speed propulsion system with inlet cooling | |
| CN110131074B (en) | Bipropellant air turbine rocket propulsion system | |
| CN109139296B (en) | Rocket-based combined cycle engine | |
| US20180356099A1 (en) | Bulk swirl rotating detonation propulsion system | |
| US20180355792A1 (en) | Annular throats rotating detonation combustor | |
| CN110718843B (en) | Air-breathing type continuous rotation detonation combustion driven premixing type carbon dioxide pneumatic laser | |
| CN109630315B (en) | Solid rocket scramjet engine, arc-shaped gas generator and central injection device | |
| US3469396A (en) | Gas turbine | |
| CN109028150B (en) | Effervescent atomization structure for rotary detonation propulsion system and method of operation | |
| CN114777162A (en) | Continuous rotation knocking ramjet engine with radial oil supply and air supply | |
| US20210140641A1 (en) | Method and system for rotating detonation combustion | |
| CN109899179B (en) | Scramjet engine capable of improving supersonic combustion performance of boron-containing rich-combustion solid propellant | |
| US20180010800A1 (en) | Shock compression based supersonic combustor | |
| US3241310A (en) | Lightweight power plant | |
| CN114877378A (en) | Inner ring detonation combustion chamber | |
| CN114811654B (en) | Pressure-stabilizing flow-equalizing self-cooling continuous rotation detonation ramjet engine with radial oil supply | |
| US20190360695A1 (en) | Rotating Detonation Combustion System |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220722 |
|
| RJ01 | Rejection of invention patent application after publication |