CN103089445A - Counter pressure preventing structure of air inlet channel of inspiration type impulse knocking engine - Google Patents
Counter pressure preventing structure of air inlet channel of inspiration type impulse knocking engine Download PDFInfo
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- CN103089445A CN103089445A CN2013100280972A CN201310028097A CN103089445A CN 103089445 A CN103089445 A CN 103089445A CN 2013100280972 A CN2013100280972 A CN 2013100280972A CN 201310028097 A CN201310028097 A CN 201310028097A CN 103089445 A CN103089445 A CN 103089445A
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Abstract
The invention provides a counter pressure preventing structure of an air inlet channel of an inspiration type impulse knocking engine. The counter pressure preventing structure comprises an air inlet cone, a cylindrical pipe section, a voltage-stabilizing cavity and an actuation mechanism, wherein the side wall surface of the cylindrical pipe section is provided with two rows of drainage holes which are arranged in an annular manner; the voltage-stabilizing cavity is of a thin wall step column structure with the large diameter centre section and the two small diameter ends, and the wall surface of the centre section of the voltage-stabilizing cavity is provided with an annular pressure relief groove; the actuation mechanism is arranged in the centre section of the voltage-stabilizing cavity, and the actuation mechanism is in axially seal slide; the voltage-stabilizing cavity is sleeved on the outer wall surface of the cylindrical pipe section, and the two end faces of the voltage-stabilizing cavity are coaxially hermetically fixedly connected with the cylindrical pipe section; and two rows of drainage holes on the side wall surface of the cylindrical pipe section are respectively corresponding to small diameter sections of the two ends of the voltage-stabilizing cavity. The counter pressure preventing structure provided by the invention realizes the isolation of high total pressure inflow and external air in air inflow through adopting the conjugation of the voltage-stabilizing cavity and the actuation mechanism, after the knocking is formed, the reflux can play the role of the actuation mechanism, the voltage-stabilizing cavity is communicated with the reflux and the outside, the reflux enters a flow guiding cavity so as to exhaust in a reverse manner, and the purpose that the counter pressure of the air inlet channel is reduced is achieved.
Description
Technical field
The present invention relates to technical field of engines, be specially a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure.
Background technique
Pulse-knocking engine is the power plant of periodic duty.Pulse-knocking engine can be divided into air-breathing pulse detonation engine and rocket type pulse-knocking engine according to whether carrying oxygenant.As oxygenant, its intake duct can not seal air-breathing pulse detonation engine fully due to the periodic air amount of needs.
The detonation wave that forms in the air-breathing pulse detonation engine working procedure can be propagated to the detonation chamber both sides, and the detonation wave of propagating to intake duct is called the passback detonation wave.The passback detonation wave can be decayed into one shock wave and propagated to intake duct under the effect of detonation chamber obstacle, the combustion gas after shock wave also can and then flow into intake duct.Anti-pass shock wave and combustion gas not only make the motor propulsive performance descend, and can affect the normal operation of motor.So mechanical valve or pneumatic valve must be installed between intake duct and detonation chamber.Although existing mechanical valve such as rotary valve can flow and the intake duct isolation counter, high stagnation pressure incoming flow causes very large negative thrust after stagnation on valve body, and has rotary component and control system on rotary valve, has increased system complexity.The requirement of pneumatic valve is that the forward flow resistance is little, thereby the adverse current resistance greatly effectively reduces anti-flowing pressure, reduces the pressure pulsation of intake duct.The taper pneumatic valve forward intake resistance of existing pneumatic valve such as Srnirnov is very big, and the swirler type pneumatic valve configurations is complicated, and blade is subject to the effect easily distortion afterwards of recurrent pulses pressure.In a word, utilize pneumatic valve to reduce the intake duct back-pressure and also need a large amount of research work.
Summary of the invention
The technical problem that solves
The problem that exists for solving prior art, the present invention proposes a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure, this structure can the intensifier pulse detonation engine positive thrust, reduce the back-pressure of intake duct, can also improve the blending of air-flow and fuel oil simultaneously.
Technological scheme
Technological scheme of the present invention is:
Described a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure is characterized in that: comprise inlet cone, cylindrical pipeline section, pressure stabilizing cavity and actuation mechanism; Have the conduction hole of two row's annular layouts on cylindrical pipeline section side wall surface; Inlet cone is coaxial is arranged on cylindrical pipeline section center, and is fixedly connected with cylindrical pipeline section by the fuel gallery on inlet cone, forms the annular pass between inlet cone and cylindrical pipeline section; Described pressure stabilizing cavity is the thin-walled step round column structure of stage casing major diameter, diameter small in ends, and the central through bore diameter of pressure stabilizing cavity both ends of the surface equals cylindrical pipeline section side wall surface external diameter, has annular gas pressure relief slot on the wall of pressure stabilizing cavity stage casing; Described actuation mechanism is comprised of two ring sheets, and ring sheet external diameter equals pressure stabilizing cavity stage casing internal diameter, and ring sheet internal diameter equals cylindrical pipeline section side wall surface external diameter, is fixedly connected with by many axial struts between two ring sheets; Axial distance between two ring sheets is less than the large value of annular gas pressure relief slot and pressure stabilizing cavity stage casing wall both ends of the surface distance, and the axial distance between two ring sheets is greater than the little value of annular gas pressure relief slot and pressure stabilizing cavity stage casing wall both ends of the surface distance; Actuation mechanism is arranged on intersegmental part in pressure stabilizing cavity, and actuation mechanism can be slided in axial seal; Pressure stabilizing cavity is enclosed within cylindrical pipeline section outer wall, and the pressure stabilizing cavity both ends of the surface are fixedly connected with cylindrical pipeline section co-axial seal; On cylindrical pipeline section side wall surface two row conduction hole is corresponding pressure stabilizing cavity diameter section small in ends respectively.
Described a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure is characterized in that: also include diversion cavity, diversion cavity is the thin wall cylindrical structure, and the central through bore diameter of diversion cavity one end face equals pressure stabilizing cavity stage casing external diameter; Diversion cavity end face and pressure stabilizing cavity stage casing co-axial seal are fixed, and annular gas pressure relief slot is in diversion cavity.
Described a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure is characterized in that: also comprise the shock wave reflection device, described shock wave reflection device center is loop configuration, and the internal diameter of loop configuration equals inlet cone cylindrical section external diameter; Loop configuration is extended with some shock wave reflection ends, and the end of each shock wave reflection end is the parabolic profile; The shock wave reflection device is coaxial to be fixed on inlet cone, and the shock wave reflection end is between inlet cone and cylindrical pipeline section and forms in the annular pass, and the parabolic type of shock wave reflection end end is come flow path direction facing to anti-stream.
Described a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure is characterized in that: the inlet cone tail end is the shock wave focus reflecting and concave-cavity of parabolic type.
Described a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure is characterized in that: have the oblique fire discharge orifice of row's annular layout on the shock wave focus reflecting and concave-cavity wall of inlet cone tail end, the conduction hole that the oblique fire discharge orifice is arranged after cylindrical pipeline section.
Beneficial effect
The present invention is by adopting pressure stabilizing cavity and actuation mechanism to coordinate, and when realizing air inlet, high stagnation pressure incoming flow and ambient air are isolated, and high stagnation pressure incoming flow can not flow in atmosphere; And after igniting forms pinking, instead flow the actuation mechanism effect, pressure stabilizing cavity is in communication with the outside anti-stream, and instead flows to oppositely discharge after diversion cavity, reaches the purpose of reduction intake duct back-pressure, strengthens simultaneously the positive thrust of motor.In addition, the present invention has also adopted shock wave reflection device and shock wave focus cavity, reduces the stagnation pressure of anti-stream by reflected shock wave.
Description of drawings
Fig. 1. structural drawing of the present invention
Fig. 2. shock wave reflection installation drawing of the present invention
Fig. 3. cylindrical tube segment structure figure of the present invention
Fig. 4. pressure stabilizing cavity of the present invention and actuation mechanism structural drawing
Fig. 5. a preferred embodiment of the present invention structural drawing
Fig. 6. a kind of oblique fire discharge orifice partial enlarged drawing of preferred version
Fig. 7. the embodiments of the invention schematic diagram
1. inlet cones in figure, 2. shock wave reflection device, 3. cylindrical pipeline section, 4. pressure stabilizing cavity, 5. front limit plane, 6. actuation mechanism, 7. gas pressure relief slot, 8. diversion cavity, 9. rear spacing plane, 10. front conduction hole, 11. fuel galleries, 12 rear conduction holes, 13. the shock wave focus cavity, 14. oblique fire discharge orifices, 15. igniters, 16. the screw type obstacle, 17. detonation chambers.
Embodiment
Below in conjunction with specific embodiment, the present invention is described:
The present embodiment is used for the air inlet of air-breathing pulse detonation engine head construction.With reference to accompanying drawing 1, the air inlet of air-breathing pulse detonation engine back-pressure preventing structure in the present embodiment comprises inlet cone 1, cylindrical pipeline section 3, pressure stabilizing cavity 4 and actuation mechanism 6.
With reference to accompanying drawing 2, cylindrical pipeline section two ends are adpting flange, have the conduction hole of two row's annular layouts on cylindrical pipeline section agent structure side wall surface, are respectively front conduction hole 10 and rear conduction hole 12.With reference to accompanying drawing 1, inlet cone is coaxial is arranged on cylindrical pipeline section center, and inlet cone is fixedly connected with cylindrical pipeline section by fuel gallery 11, forms the annular pass between inlet cone and cylindrical pipeline section.
With reference to accompanying drawing 4, pressure stabilizing cavity 4 is the thin-walled step round column structure of stage casing major diameter, diameter small in ends, forms front limit plane 5 and rear spacing plane 9 between stage casing enlarged diameter section and diameter section small in ends.The central through bore diameter of pressure stabilizing cavity both ends of the surface equals cylindrical pipeline section side wall surface external diameter.Have annular gas pressure relief slot 7 on the wall of pressure stabilizing cavity stage casing.
With reference to accompanying drawing 4, actuation mechanism 6 is comprised of two ring sheets, and ring sheet external diameter equals pressure stabilizing cavity stage casing internal diameter, and ring sheet internal diameter equals cylindrical pipeline section side wall surface external diameter, is fixedly connected with by equally distributed four axial struts between two ring sheets.axial distance between two ring sheets is less than the large value of annular gas pressure relief slot and pressure stabilizing cavity stage casing wall both ends of the surface distance, and the axial distance between two ring sheets is greater than the little value of annular gas pressure relief slot and pressure stabilizing cavity stage casing wall both ends of the surface distance, be in the present embodiment, axial distance between two ring sheets is less than the axial distance between annular gas pressure relief slot and front limit plane 5, and the axial distance between two ring sheets is greater than the axial distance between annular gas pressure relief slot and rear spacing plane 9, to guarantee when actuation mechanism during in the pressure stabilizing cavity slides within, air-flow can flow according to designing requirement.
Actuation mechanism is arranged on intersegmental part in pressure stabilizing cavity, and actuation mechanism can be slided in pressure stabilizing cavity stage casing axial seal under the effect of air-flow differential.Pressure stabilizing cavity is enclosed within cylindrical pipeline section outer wall, and the pressure stabilizing cavity both ends of the surface are fixedly connected with cylindrical pipeline section co-axial seal; And the row of two on cylindrical pipeline section side wall surface conduction hole is corresponding pressure stabilizing cavity diameter section small in ends respectively, and namely front conduction hole 10 is in 5 front sides, front limit plane, and rear conduction hole 12 is in rear spacing plane 9 rear sides.
When air-breathing pulse detonation engine is worked, the incoming flow that stagnation pressure is higher enters motor from inlet cone 1 and the annular pass that cylindrical pipeline section 3 forms, the high stagnation pressure incoming flow of a part first enters pressure stabilizing cavity 4 by front conduction hole 10, promote actuation mechanism 6 along coming flow path direction to move until spacing plane 9, thereby with high stagnation pressure incoming flow and ambient air isolation, high like this stagnation pressure incoming flow can not flow in atmosphere.On the other hand, most of incoming flow through the annular pass after with 11 fuel oils that flow out carry out blending and fill detonation chamber 17 from the fuel gallery, after the detonation chamber filling is complete, igniter 15 begins igniting, light the gas mixture in detonation chamber, form one detonation wave after flame accelerates through screw type obstacle 16 and divide supplementary biography to engine export and intake duct with returning detonation wave.The passback detonation wave decays to one shock wave under the effect of obstacle, the combustion gas after shock wave also and then flows to intake duct.The anti-stream of part enters pressure stabilizing cavity 4 from rear conduction hole 12, promotes actuation mechanism against coming flow path direction until spacing plane 5, and at this moment gas pressure relief slot 7 is with pressure stabilizing cavity 4 and extraneous the connection, and anti-stream is discharged from gas pressure relief slot, reaches the purpose that reduces the intake duct back-pressure.
As further optimized project, also have diversion cavity 8 in the pressure stabilizing cavity outside, diversion cavity is the thin wall cylindrical structure, the central through bore diameter of diversion cavity one end face equals pressure stabilizing cavity stage casing external diameter; Diversion cavity end face and pressure stabilizing cavity stage casing co-axial seal are fixed, and annular gas pressure relief slot is in diversion cavity.When anti-stream enters diversion cavity 8 after gas pressure relief slot 7 is discharged, and discharge along diversion cavity 8 direction opposite with airintake direction, thus reaching reduce the intake duct back-pressure purpose simultaneously, the positive thrust of enhancing motor.
As further optimized project, the shock wave reflection device is installed on inlet cone, with reference to accompanying drawing 2, shock wave reflection device center is loop configuration, the internal diameter of loop configuration equals inlet cone cylindrical section external diameter; Loop configuration is extended with some shock wave reflection ends, and the end of each shock wave reflection end is the parabolic profile; The shock wave reflection device is coaxial to be fixed on inlet cone, and the shock wave reflection end is between inlet cone and cylindrical pipeline section and forms in the annular pass, and the parabolic type of shock wave reflection end end is come flow path direction facing to anti-stream.Adopt the shock wave reflection device, by the annular pass, form the multiple tracks reflected shock waves when the passback shock wave after channel outlet and shock wave reflection device 2 interact, further reduce the stagnation pressure that refluxes, thereby guarantee the normal operation of intake duct.
As further optimized project, the inlet cone tail end is the shock wave focus reflecting and concave-cavity of parabolic type, returns like this shock wave and can reflect very strong together shock wave on the shock wave focus cavity 13 of inlet cone end, reduces the stagnation pressure of backflow combustion gas and produces very large thrust.
As further optimized project, with reference to accompanying drawing 5 and accompanying drawing 6, have the oblique fire discharge orifice 14 of row's annular layout on the shock wave focus reflecting and concave-cavity wall of inlet cone tail end, the conduction hole that the oblique fire discharge orifice is arranged after cylindrical pipeline section.In intake process, high stagnation pressure incoming flow forms multiply oblique fire stream and with 11 fuel oil interacts from the fuel gallery, strengthens the blending of fuel oil and air by the oblique fire discharge orifice.After forming pinking, anti-stream also can flow out from oblique fire discharge orifice 14 and form oblique fire stream, gives anti-stream a component velocity radially after mixing with anti-stream, being conducive to more anti-stream enters in pressure stabilizing cavity by conduction hole 12, and flow into the external world by gas pressure relief slot 7, thereby effectively reduce anti-stream back-pressure, generation positive thrust.
Claims (5)
1. an air inlet of air-breathing pulse detonation engine back-pressure preventing structure, is characterized in that: comprise inlet cone, cylindrical pipeline section, pressure stabilizing cavity and actuation mechanism; Have the conduction hole of two row's annular layouts on cylindrical pipeline section side wall surface; Inlet cone is coaxial is arranged on cylindrical pipeline section center, and is fixedly connected with cylindrical pipeline section by the fuel gallery on inlet cone, forms the annular pass between inlet cone and cylindrical pipeline section; Described pressure stabilizing cavity is the thin-walled step round column structure of stage casing major diameter, diameter small in ends, and the central through bore diameter of pressure stabilizing cavity both ends of the surface equals cylindrical pipeline section side wall surface external diameter, has annular gas pressure relief slot on the wall of pressure stabilizing cavity stage casing; Described actuation mechanism is comprised of two ring sheets, and ring sheet external diameter equals pressure stabilizing cavity stage casing internal diameter, and ring sheet internal diameter equals cylindrical pipeline section side wall surface external diameter, is fixedly connected with by many axial struts between two ring sheets; Axial distance between two ring sheets is less than the large value of annular gas pressure relief slot and pressure stabilizing cavity stage casing wall both ends of the surface distance, and the axial distance between two ring sheets is greater than the little value of annular gas pressure relief slot and pressure stabilizing cavity stage casing wall both ends of the surface distance; Actuation mechanism is arranged on intersegmental part in pressure stabilizing cavity, and actuation mechanism can be slided in axial seal; Pressure stabilizing cavity is enclosed within cylindrical pipeline section outer wall, and the pressure stabilizing cavity both ends of the surface are fixedly connected with cylindrical pipeline section co-axial seal; On cylindrical pipeline section side wall surface two row conduction hole is corresponding pressure stabilizing cavity diameter section small in ends respectively.
2. a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure according to claim 1, it is characterized in that: also include diversion cavity, diversion cavity is the thin wall cylindrical structure, the central through bore diameter of diversion cavity one end face equals pressure stabilizing cavity stage casing external diameter; Diversion cavity end face and pressure stabilizing cavity stage casing co-axial seal are fixed, and annular gas pressure relief slot is in diversion cavity.
3. a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure according to claim 2 is characterized in that: also comprise the shock wave reflection device, described shock wave reflection device center is loop configuration, and the internal diameter of loop configuration equals inlet cone cylindrical section external diameter; Loop configuration is extended with some shock wave reflection ends, and the end of each shock wave reflection end is the parabolic profile; The shock wave reflection device is coaxial to be fixed on inlet cone, and the shock wave reflection end is between inlet cone and cylindrical pipeline section and forms in the annular pass, and the parabolic type of shock wave reflection end end is come flow path direction facing to anti-stream.
4. a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure according to claim 3, it is characterized in that: the inlet cone tail end is the shock wave focus reflecting and concave-cavity of parabolic type.
5. a kind of air inlet of air-breathing pulse detonation engine back-pressure preventing structure according to claim 4, it is characterized in that: have the oblique fire discharge orifice of row's annular layout on the shock wave focus reflecting and concave-cavity wall of inlet cone tail end, the conduction hole that the oblique fire discharge orifice is arranged after cylindrical pipeline section.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310028097.2A CN103089445B (en) | 2013-01-25 | 2013-01-25 | Counter pressure preventing structure of air inlet channel of inspiration type impulse knocking engine |
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| CN201310028097.2A CN103089445B (en) | 2013-01-25 | 2013-01-25 | Counter pressure preventing structure of air inlet channel of inspiration type impulse knocking engine |
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| CN103089445A true CN103089445A (en) | 2013-05-08 |
| CN103089445B CN103089445B (en) | 2015-04-22 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103953461A (en) * | 2014-04-01 | 2014-07-30 | 西北工业大学 | Mechanical valve for reducing reverse pressure of air inlet passage of air-breathing pulse detonation engine |
| CN107476898A (en) * | 2017-09-13 | 2017-12-15 | 西北工业大学 | A kind of air-breathing pulse detonation engine suppresses the structure of combustion gas forward pass |
| CN109882315A (en) * | 2019-03-21 | 2019-06-14 | 中国航发湖南动力机械研究所 | Pulse-knocking engine |
| CN111520767A (en) * | 2020-06-03 | 2020-08-11 | 西安热工研究院有限公司 | Pulse detonation combustion chamber capable of adjusting energy distribution of outlet gas |
| CN112833425A (en) * | 2021-01-05 | 2021-05-25 | 南京理工大学 | Forward shock wave suppression structure for air-breathing rotary detonation combustion chamber |
| CN113295374A (en) * | 2021-05-17 | 2021-08-24 | 中国人民解放军国防科技大学 | Air inlet channel back pressure device and method for forming back pressure distribution in air inlet channel |
| CN117688697A (en) * | 2024-02-02 | 2024-03-12 | 中国人民解放军空军工程大学 | Design method of rotary detonation engine air inlet channel |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201614995U (en) * | 2010-02-04 | 2010-10-27 | 西北工业大学 | Anti-reverse flow mechanism of suction type pulse detonation engine |
| CN201696166U (en) * | 2010-06-10 | 2011-01-05 | 西北工业大学 | Aspirated impulse knocking engine |
| CN101956631A (en) * | 2010-09-30 | 2011-01-26 | 西北工业大学 | Air inlet channel of air-breathing type pulse detonation engine |
| CN102003302A (en) * | 2010-11-18 | 2011-04-06 | 西北工业大学 | Air intake cone of air-breathing pulse detonation engine |
| CN202578944U (en) * | 2012-03-31 | 2012-12-05 | 西北工业大学 | Back pressure reducing device for aspirating pulse knock air inlet channel |
-
2013
- 2013-01-25 CN CN201310028097.2A patent/CN103089445B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201614995U (en) * | 2010-02-04 | 2010-10-27 | 西北工业大学 | Anti-reverse flow mechanism of suction type pulse detonation engine |
| CN201696166U (en) * | 2010-06-10 | 2011-01-05 | 西北工业大学 | Aspirated impulse knocking engine |
| CN101956631A (en) * | 2010-09-30 | 2011-01-26 | 西北工业大学 | Air inlet channel of air-breathing type pulse detonation engine |
| CN102003302A (en) * | 2010-11-18 | 2011-04-06 | 西北工业大学 | Air intake cone of air-breathing pulse detonation engine |
| CN202578944U (en) * | 2012-03-31 | 2012-12-05 | 西北工业大学 | Back pressure reducing device for aspirating pulse knock air inlet channel |
Non-Patent Citations (2)
| Title |
|---|
| 严传俊: "《脉冲爆震发动机原理及关键技术》", 31 October 2005, 西北工业大学出版社 * |
| 范育新等: ""脉冲爆震发动机气动阀性能分析"", 《航空动力学报》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103953461A (en) * | 2014-04-01 | 2014-07-30 | 西北工业大学 | Mechanical valve for reducing reverse pressure of air inlet passage of air-breathing pulse detonation engine |
| CN107476898A (en) * | 2017-09-13 | 2017-12-15 | 西北工业大学 | A kind of air-breathing pulse detonation engine suppresses the structure of combustion gas forward pass |
| CN109882315A (en) * | 2019-03-21 | 2019-06-14 | 中国航发湖南动力机械研究所 | Pulse-knocking engine |
| CN109882315B (en) * | 2019-03-21 | 2020-07-03 | 中国航发湖南动力机械研究所 | Pulse detonation engine |
| CN111520767A (en) * | 2020-06-03 | 2020-08-11 | 西安热工研究院有限公司 | Pulse detonation combustion chamber capable of adjusting energy distribution of outlet gas |
| CN111520767B (en) * | 2020-06-03 | 2023-07-25 | 西安热工研究院有限公司 | Pulse detonation combustor capable of adjusting outlet gas energy distribution |
| CN112833425A (en) * | 2021-01-05 | 2021-05-25 | 南京理工大学 | Forward shock wave suppression structure for air-breathing rotary detonation combustion chamber |
| CN113295374A (en) * | 2021-05-17 | 2021-08-24 | 中国人民解放军国防科技大学 | Air inlet channel back pressure device and method for forming back pressure distribution in air inlet channel |
| CN113295374B (en) * | 2021-05-17 | 2022-08-23 | 中国人民解放军国防科技大学 | Air inlet channel back pressure device and method for forming back pressure distribution in air inlet channel |
| CN117688697A (en) * | 2024-02-02 | 2024-03-12 | 中国人民解放军空军工程大学 | Design method of rotary detonation engine air inlet channel |
| CN117688697B (en) * | 2024-02-02 | 2024-04-26 | 中国人民解放军空军工程大学 | Design method of rotary detonation engine air inlet channel |
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